Supersonic compressor rotor.

(54) Title: SUPERSONIC COMPRESSOR ROTOR. (54) Title: SUPERSONIC COMPRESSOR ROTOR.

(57) Summary

The present invention provides a supersonic compressor comprising a supersonic compressor rotor (100) comprising a engageable rotor disc that allows restriction or opening of portions of a fluid flow channel of the rotor in order to improve the performance of the rotor during different operational stages, for example, rotor ignition or steady state. The supersonic compressor rotor (100) comprises a first rotor disk (101), a second rotor disk (102), and a third rotor disk (103), which share a common axis of rotation. The first and second rotor discs (101,102) are rotatably coupled, and the third rotor disc (103) is disposed between them. The third rotor disc (103) is independently rotatable relative to said first and second discs (101, 102), and comprises an upright surface structure (110) to restrict or open a portion of the flow channel defined by the discs of rotor (101,102, 103) and at least two blades (150). The flow channel comprises a supersonic compression ramp (120) and encompasses the upright surface structure (110).

(57) Abstract

The present invention provides a supersonic compressor comprising a supersonic compressor rotor (100) comprising a dockable rotor disk allowing restriction or opening of portions of a fluid flow channel of the rotor in order to enhance performance of the rotor during different operational stages, for example rotor start-up or steady state. The supersonic compressor rotor (100) comprises a first rotor disk (101), a second rotor disk (102) and a third rotor disk (103) which share a common axis of rotation. The first and second rotor disks (101,102) are rotatably coupled, and the third rotor disk (103) is disposed between them. The third rotor disk (103) is independently rotatable relative to said first and second disks (101, 102), and comprises a raised surface structure (110) for restricting or opening a portion of the flow channel defined by the rotor disks (101,102,103) and at least two vanes (150). The flow channel comprises a supersonic compression ramp (120) and encompasses the raised surface structure (110).

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of the

PATENT TITLE NO. 338178 _SE_

SYCMTM OI ECONOMY

Institute

Mexican

Property

Industrial

Owner (s): GENERAL ELECTRIC COMPANY

Address: 1 River Road, Schenectady, New York, 12345, USA

Name: SUPERSONIC COMPRESSION ROTOR Classification: lnt.CI.8: F04D17 / 12; F04D19 / 00; F04D21 / 00

Inventor (s): DOUGLAS CARL HOFER; ZACHARY WILLIAM NAGEL

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The person «reference you

This form with the articulate conlijtla from the right roof subscribes the present tflBo does it on the basis'

VÍ0

Industrial Property (Diano 0 aal de la ederactón (DOF) 26/0 2004, 16O6 / 2C05, 25/0 '&gt; 006, 06 / (J / 2009,06 / 01/2010, 18. incisa a), 4 ° and 12th fractions and III of and of the

In istrial.

impror gables, ites bis 2 of the l

I, 12/26/1997, 17 5/1999, _ 12); artfeutos 1 ·, 3 · fi xión V of the Instituto MexjanPHMMMMMHMBStosl (DOF 14/12/1999, challenge side on 01/0 * 2002,15 / 07/2004, 28/07 * 004 and 7 / Λ / 2007); Articles 1, 3 *. 4 °, 5 * fraction V, subsection aj, 16 fractions I and III and 30 of the Statute of the Inter-organic age; 1st, 3rd and 5th paragraph a) of the Agreement that delegates powers to the Deputy Directors General, Coordinator, Divisional Directors, Holders of Regional Offices, Divisional Deputy Directors, Departmental Coordinators and other subordinates of the Mexican Institute of Industrial Property. (DOF 12/15/1999, amended on 02/04/2000, 07/29/2004, 08/04/2004 and 09/13/2007).

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Sand! No. 550 .. Floor 1,

Pueblo Santa María Tepepan Xochimiico, ZIP 16020.

Mexico City

Tel. (55) 53 34 07 00 www.tmpi.gob.mx

Issue Date: April 6, 2016

DIVISIONAL DIRECTOR ^ OF PATENTS

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NAHANNY CANAL REYES

III

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MX / 2016/26031

SUPERSONIC COMPRESSION ROTOR

ΜίαΙ 12.) ÓO ^ óD

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Related Requests

This application relates to the United States Patent Applications

United States of America, Serial Numbers 12 / 342,278 and 12 / 491,602, filed on December 23, 2008, and June 25, 2009, respectively, and which is incorporated herein by reference in its entirety.

Field of Invention

The present invention relates to compressors and systems comprising compressors. In particular, the present invention relates to supersonic compressors comprising supersonic compression rotors and systems comprising the same.

Background of the Invention

Conventional compressor systems are widely used to compress gases and find application in many currently used technologies ranging from refrigeration units to jet engines. The basic purpose of a compressor is to transport and compress the gas. To do this, a compressor typically applies mechanical energy to a gas at a low ambient pressure and transports the gas and compresses the gas into a high ambient pressure from which the compressed gas can be used to carry out tasks or as the

inlet for a downstream process that uses a high pressure gas. Gas compression technologies are well established and range from centrifugal machines to mixed flow machines, to axial flow machines. Conventional compressor systems, although widely used, are limited in that the proportion of pressure that can be reached by a single stage of the compressor is relatively low. When a generally high pressure ratio is required, conventional compressor systems comprising multiple stages of compression can be used. However, conventional compressor systems comprising multiple stages of compression can be large, complex, and expensive.

More recently, compressor systems comprising a supersonic compression rotor have been discovered. Such compressor systems, sometimes referred to as supersonic compressors, transport and compress gases by contacting the inlet gas with a movable rotor that has rotor edge surface structures that transport and compress the inlet gas from the low side. supersonic compression rotor pressure to the high pressure side of the supersonic compression rotor. Although higher single stage proportions of pressure can be achieved with a supersonic compressor compared to a conventional compressor, other improvements are highly desirable.

As detailed herein, the present invention provides novel supersonic compression rotors and supersonic compressors that provide improvements in compressor performance relative to

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known supersonic compressors.

Brief Description of the Invention

In a first aspect, the present invention provides a supersonic compression rotor comprising (a) a first rotor disk; (b) a second rotor disc; and (c) a third rotor disc, the first, second and third rotor discs share a common axis of rotation, the first and second rotor discs are rotatably coupled, the third rotor disc is disposed between the first and the second rotor discs, the third rotor disc can rotate independently relative to the first and second rotor discs, the third rotor disc comprises a raised surface structure, the first, second and third rotor discs together with at least two fins define a flow channel spanning the raised surface structure of the third rotor disc, the flow channel comprising a supersonic compression ramp.

In a second aspect, the present invention provides a supersonic compression rotor comprising: (a) a first rotor disk, (b) a second rotor disk; (c) a third rotor disc and (d) a rotor support plate, the first and second rotor discs define an internal cylindrical cavity and an outer edge of the rotor, the first, second and third rotor discs share a common axis of rotation, the first and second rotor discs are rotatably coupled, the third rotor disc is arranged between the first and second rotor discs, the third rotor disc can rotate independently relative to the

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First and second rotor discs, the third rotor disc comprises a raised surface structure, the first, second and third rotor discs together with two fins and a rotor support plate define a radial flow channel spanning the structure with a high surface area of ​​the third rotor disc, the radial flow channel comprises a supersonic compression ramp, The radial flow channel allows radial fluid communication between the inner cylindrical cavity and the outer edge of the rotor.

In a third aspect, the present invention provides a supersonic compression rotor comprising: (a) a first rotor disk; (b) a second rotor disc and (c) a third rotor disc, the first, second and third rotor discs define an external surface of the supersonic compression rotor, the first, second and third rotor discs share a common axis of rotation, the first and second discs are rotatably coupled, the third rotor disc is arranged between the first and second rotor discs, the third rotor disc can rotate independently relative to the first and second rotor discs; the third rotor disc comprises a raised surface structure, the first, second and third rotor discs together with at least two fins define an axial flow channel spanning the raised surface structure of the third rotor disc, the channel of axial flow comprises a supersonic compression ramp, the axial flow channel allows fluid communication axially along the outer surface of the supersonic compression rotor.

In a fourth aspect, the present invention provides a

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supersonic compressor comprising: (a) a fluid inlet; (b) a fluid outlet and (c) at least one supersonic compression rotor, the supersonic compression rotor comprises (i) a first rotor disk; (ii) a second rotor disc and (iii) a third rotor disc, the first, second and third rotor discs share a common axis of rotation, the first and second discs are rotatably coupled, the third disc of rotor is arranged between the first and second rotor discs, the third rotor disc can rotate independently relative to the first and second rotor discs, the third rotor disc comprises a raised surface structure, the first, second and third rotor discs together with at least two fins define an axial flow channel spanning the raised surface structure of the third rotor disc, the axial flow channel comprising a supersonic compression ramp.

In a fifth aspect, the present invention provides a method of compressing a fluid comprising (a) introducing a fluid through a low pressure gas inlet into a gas line within the supersonic compressor; and (b) removing the gas through a high pressure gas outlet from the supersonic compressor, the supersonic compressor comprises a supersonic compression rotor arranged between the gas inlet and the gas outlet, the supersonic compression rotor comprises;

(i) a first rotor disc; (ii) a second rotor disc and (iii) a third rotor disc, the first, second and third rotor discs share a common axis of rotation, the first and second discs are rotatably coupled, the third disc rotor is arranged between the first and second rotor discs, the third rotor disc can rotate

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Independent from the first and second rotor discs, the third rotor disc comprises a raised surface structure, the first, second, and third rotor discs together with at least two fins define an axial flow channel spanning the structure With a raised surface of the third rotor disc, the axial flow channel comprises a supersonic compression ramp.

In a sixth aspect, the present invention provides a method of starting a supersonic compressor, the method comprising (a) providing a supersonic compressor comprising a supersonic compression rotor disposed within a fluid line of the supersonic compressor; The rotor of the supersonic compressor comprises: (i) a first rotor disk; (ii) a second rotor disc and (iii) a third rotor disc, the first, second and third rotor discs share a common axis of rotation, the first and second discs are rotatably coupled, the third disc rotor is arranged between the first and second rotor discs, the third rotor disc can rotate independently relative to the first and second rotor discs, the third rotor disc comprises a raised surface structure, the first, second and third rotor discs together with at least two fins define an axial flow channel spanning the raised surface structure of the third rotor disc, the axial flow channel comprising a supersonic compression ramp; (b) placing the raised surface structure of the third rotor disc within the flow channel so that a throat area of ​​the flow channel becomes less restricted as the rotor of the supersonic compressor is rotated at sub-sonic speeds, and (c)

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relocating the raised surface structure of the third rotor disc into the flow channel, so that the throat area of ​​the flow channel becomes relatively more restricted as the supersonic compression rotor is rotated at supersonic speeds.

Brief Description of Drawings

These and other features, aspects and advantages of the present invention will be better understood upon reading the following detailed description with reference to the accompanying drawings, in which the same numbers represent the same parts throughout the drawings, wherein:

Figure 1 illustrates a radial supersonic compression rotor provided by the present invention.

Figure 2 illustrates a sectional view of a radial supersonic compression rotor provided by the present invention.

Figure 3 illustrates an exploded view of the supersonic compression rotor provided by the present invention.

Figure 4 illustrates the supersonic compressor provided by the present invention.

Figure 5 illustrates a sectional view of a supersonic compression rotor 20 provided by the present invention.

Figure 6 illustrates a supersonic compression rotor provided by the present invention.

Figure 7 illustrates a supersonic compression rotor provided by the present invention.

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In the drawings provided here, the characters s represent equal parts. Unless otherwise indicated, the drawings provided herein are intended to illustrate the inventive features of the invention. The key Inventive features are believed to be applicable in a wide variety of systems comprising one or more embodiments of the invention. As such, the drawings are not intended to include all of the conventional features known to those of skill in the art required to practice the invention.

Detailed description of the invention

In the following specification and in the following claims, various terms are referred to, which must be defined to have the following meaning.

The singular forms "a", "one", "one", "the" and "the" include plural referents unless the context clearly dictates otherwise.

"Optional" or "optionally" means that the subsequent event or circumstance may or may not occur, and that the description includes cases where the event occurs and cases where the event does not occur.

Approximation language, as used throughout the specification and claims, can be applied to modify any quantitative representation that may vary without resulting in a change in the basic function to which it relates. Accordingly, a value modified by the term or terms such as "approximately" is not limited to the specific value. In some cases, the approximation language may correspond to the precision of an instrument to measure the value. Throughout the specification and claims, range limitations can be combined and / or interchanged, such ranges are identified and include all sub-ranges contained therein unless context or language indicates otherwise.

As used herein, the term "supersonic compression rotor" refers to a compressor rotor comprising a supersonic compression ramp disposed within a fluid flow channel of the supersonic compression rotor, the supersonic compression rotor being configured from so that during operation, the velocity of the fluid that meets the fluid outlet of the fluid flow channel of the moving rotor is supersonic.

As used herein, the term "supersonic compressor" refers to a compressor that comprises a supersonic compression rotor.

Known supersonic compressors, which may comprise one or more supersonic compression rotors, are configured to compress a fluid between an inlet edge of the supersonic compression rotor and the inner wall of the fluid conduit where the supersonic compression rotor is arranged . In such supersonic compressors, fluid is transported through the outer edge of the supersonic compression rotor rotor from the low pressure side of the fluid line to the high pressure side of the fluid line. The fins (sometimes called "vanes") arranged on the outer edge of the rotor provide an axial flow channel through which fluid moves from one side of the supersonic compression rotor to the other. Supersonic compressors comprising supersonic compression rotors are described in detail, for example, in U.S. Patent Nos. 7,334,990 and 7,293,955, filed March 28, 2005 and March 23, 2005, respectively, and the Application. of United States of America Patent 2009/0196731, filed on January 16, 2009.

The present invention is characterized by novel supersonic compression rotors where the transport of fluid from the low pressure side of the fluid line to the high pressure side of the fluid line occurs through a radial flow channel or a flow channel. axial flow and therefore includes supersonic compression rotors that have radial flow characteristics or axial flow characteristics. The supersonic compression rotors provided by the present invention have radial flow supersonic compression characteristics that comprise a radial flow channel that is connected to an internal cylindrical cavity of the supersonic compression rotor with the outer edge of the rotor. The supersonic compression rotors provided by the present invention have supersonic axial flow compression features that comprise an axial flow channel that links the first side or face of the supersonic compression rotor to a second side or face of the supersonic compression rotor. Regardless of whether the supersonic compression rotor provided by the present invention has the characteristics of supersonic axial flow compression or the characteristics of radial flow supersonic compression, Each of the supersonic compression rotors provided by the present invention comprises a third "rotating" rotor disk comprising a raised surface structure that can be used to expand or restrict free volume within a given portion of the flow channel of fluid. By the term "rotary" is meant that the third rotor disc can rotate independently relative to the first rotor disc or the second rotor disc that are components of a supersonic compression rotor. This allows a limited range of movement of the raised surface structure within the fluid flow channel in order to expand or restrict the free volume of a given portion of the fluid flow channel. The novel supersonic compression characteristics of the design of the supersonic compression rotors provided by the present invention are expected to improve the performance of the supersonic compressors comprising them, and to provide greater versatility in systems comprising such novel supersonic compressors. In various embodiments, the supersonic compression rotors having the supersonic radial flow compression characteristics provided by the present invention may be configured for internal-external compression or external-internal compression. A supersonic compression rotor that has radial flow supersonic compression characteristics is configured for internal-external compression when during operation, as the rotor rotates, fluid moves from the internal cylindrical cavity through the radial flow channel toward the outer edge of the rotor. The supersonic compression rotor is configured for external-internal compression when during operation, as the rotor rotates, fluid moves from the outer edge of the rotor through the radial flow channel into the internal cylindrical cavity. Whether or not the supersonic compression rotor that has radial flow supersonic compression characteristics is configured for internal-external or external-internal compression can be determined by the location of the supersonic compression ramp within the flow channel. radial and the configuration of the fins at the fluid inlet of the radial flow channel, or simply by the direction in which the supersonic compression rotor rotates. In several examples illustrated in the Figures, supersonic compression rotors that have radial flow supersonic compression characteristics are shown configured for internal-external compression.

As mentioned, in one embodiment, the present invention provides a supersonic compression rotor comprising a first rotor disc, a second rotor disc and a third rotor disc, the discs share a common axis of rotation. The discs are arranged in such a way that the third rotor disc is arranged between the first rotor disc and the second rotor disc. The first rotor disc and the second rotor disc are rotatably coupled to each other, for example, by a common drive shaft (see Figure 7), or by one or more fins, so that when the first disc of the The rotor engages with the drive shaft and the drive shaft adjusts in motion, both the first rotor disc and the second rotor disc causing disputes on the surface of the discs and defining a fluid flow channel. In the case of supersonic compression rotors configured for radial fluid flow, the fins can be configured as a spiral through the surface created by the first rotor disc and the second rotor disc (see Figure 1). In the case of supersonic compression rotors configured for axial fluid flow, the fins may be configured as a screw through the surface created by the first rotor disc and the second rotor disc (see Figure 6).

The third rotor disc is disposed between the first and second rotor discs and is typically not in contact with the fins. In various embodiments, it is desirable that the clearance between the third rotor disc and the fins be as small as possible. The clearance between the third rotor disc and the fins need not be identical or constant, but is typically within the order of a fraction of a millimeter to a few millimeters. In one embodiment, the clearance between the third rotor disc and the fins is in the range of about 0.01 millimeters to about 1 millimeter.

The third rotor disc comprises at least one raised surface structure. This raised surface structure has dimensions such that the height of the raised surface structure is greater than the clearance between the surface of the third rotor disc and the fins. As such, the third rotor disc must be configured so that when the first and second rotor discs co-rotate, the third rotor disc must also rotate and generally co-rotate with the first rotor disc and the second rotor disc. This can be achieved by allowing contact between the surfaces of the third rotor disc with one of the surfaces of the first rotor disc and one of the surfaces of the second rotor disc. This friction coupling between the discs allows the three discs to co-rotate when, for example, the first rotor disc engages with the rotating drive shaft. Because the fins traverse the surface of the third rotor disc without contacting it, and because of the dimensions of the raised surface structure, they are such that the raised surface structure may not pass under the fins, the surface structure elevated is confined to a space between two fins, the fins and the surface of the disks that define the flow channel.

Although the third rotor disc co-rotates with the first and second rotor discs, the third rotor disc can rotate independently so that the position of the raised surface structure can vary within the limits established by the fins. In certain embodiments, the variation in the position of the raised surface structure within the limits defined by the fins can be seen as potential locations of the raised surface structure (see, for example, item 111 in Figure 1). A variety of schemes can be used to independently rotate or "rotate" the third rotor disc relative to the first and second rotor discs. In one schematic, an additional force (beyond the force that causes the third rotor disc to collide with the first and second rotor discs) is applied independently to the third disc of the rotor. rotor in order to momentarily decrease or increase its rotational speed relative to the first and second co-rotating rotor discs. In an alternative scheme, the force applied to the third rotor disc by one or both of the first rotor disc and the second rotor disc is momentarily decreased, causing the third rotor disc to change the rotational speed relative to the co-rotation speed of the first rotor disc and the second rotor disc. Those of skill in the art will appreciate that during operation, a supersonic compression rotor typically operates at very high rotational speeds, for example 10,000 rpm. Thus, the momentary increase or decrease in the speed of rotation of the third rotor disc relative to the first and second rotor discs will be of very short duration (eg fractions of seconds).

Thus, the position of the raised surface structure within the flow channel can vary. This allows placement of the raised surface structure in one or more first portions of the flow channel during start-up of the supersonic compression rotor, and placing the raised surface structure in one or more second positions during, for example, the operation of steady state of supersonic compression rotor. It is believed that during start-up, the fluid inlet (see for example Figure 2, item 10) of the supersonic compression rotor should be less, rather than restricted, and that during steady-state operation of the supersonic compression rotor the Advantages of supersonic compression rotor performance are achieved by restricting fluid entry. Rotating the third rotor disk allows the raised surface structure to be removed from or inserted into the portion of the flow channel closest to the fluid inlet in order to "open" or restrict the fluid inlet.

As mentioned, the fins and surfaces of the first rotor disc, the second rotor disc, and the third rotor disc define the flow channel of the supersonic compression rotor. As will be appreciated by those skilled in the art, in order for the flow channel to be useful, it must be limited by at least one additional surface. In certain embodiments, the at least one additional surface is integrated with the supersonic compression rotor itself. For example, in the embodiment shown in Figure 3, the supersonic compression rotor comprises a rotor support plate (see item 105) which supplies this at least additional surface. In an alternative embodiment, the at least one additional surface is not integrated with the supersonic compression rotor, as in, for example, a supersonic compression rotor of the type illustrated in Figure 6, wherein when the supersonic compression rotor is arranged Within a supersonic compressor, the at least one additional surface is provided by an internal surface of the fluid conduit within which the supersonic compression rotor is disposed.

The fluid flow channel is believed to comprise at least one supersonic compression ramp, which during operation provides for the creation of an impact wave within the fluid flow channel. This supersonic compression ramp can be located in any of the structures that define the fluid flow channel. Thus, the supersonic compression ramp can be located on one or more of the fins, on a surface of the disc, or on at least one additional surface described above. Figures 1, 2, 3, 5, 6 and 7 illustrate some of the possible locations of the supersonic compression ramp within the fluid flow channel.

As noted, the supersonic compression rotor provided by the present invention can be configured for radial compression, for example, as in the embodiment shown in Figures 1, 2, 3 and 4. In such configurations, the flow channels of Fluid are referred to as radial flow channels. Alternatively, the supersonic compression rotor provided by the present invention can be configured for axial compression, for example, as in the embodiments shown in Figures 5, 6, and 7. In such configurations, the fluid flow channels are referred to as axial flow channels. In a typical embodiment, the number of fluid flow channels is determined by the number of fins and is equal to the number of fins. Thus, in the embodiment shown in Figure 1, the supersonic compression rotor comprises two fins and two radial flow channels. In the embodiment shown in Figure 3, the supersonic compression rotor comprises six fins and six radial flow channels. In the embodiments shown in Figure 5, Figure 6 and Figure 7, the supersonic compression rotor comprises two fins and two axial flow channels.

In one embodiment, the present invention provides a supersonic compression rotor comprising at least three axial flow channels. In an alternative embodiment, the present invention provides a supersonic compression rotor comprising at least three radial flow channels.

The raised surface structure can have a variety of shapes and sizes. For example, the raised surface structure may have a wedge, a ramp, a raised diamond, a raised polygon (for example, a raised pentagon, a raised hexagon, or a raised heptagon), a cone, a half cone, a half ellipse , a fractional portion of an ellipse that is not a half ellipse, a pyramid, a cylinder, a half cylinder, a fractional portion of a cylinder that is not a half cylinder, a half sphere, a fractional portion of a sphere that is not a half sphere or some combination thereof. In addition to the aforementioned well-known geometric shapes, the raised surface structure may, in certain embodiments, have an irregular shape. In one embodiment, the raised surface structure is a wedge-shaped structure. In an alternative embodiment, the raised surface structure is a ramp-shaped structure. Because the raised surface structure is positioned on the outer surface of the third rotor disc, the portion of the raised surface structure in contact with the third rotor disc will conform to the contour of the third rotor disc. As such, the portion of the raised surface structure is in contact with the third rotor disc in a supersonic compression rotor that has supersonic axial flow compression characteristics (see

Figures 5 to 7) strictly speaking, it is not a horizontal surface (with respect to a real or hypothetical reference plane) but for convenience, it will be described as a horizontal surface. Thus, even in modalities where the raised surface structure is a well-known geometric shape, such as a wedge or a half sphere, its shape will be somewhat irregular (i.e. it was due to an ideal geometric shape) when that portion of the raised surface structure in contact with the third rotor disc conforms to the contour of the disk surface and a counterpart surface of the raised surface structure is not (for example, a wedge-shaped raised surface structure where the first horizontal surface conforms to the contour of the third rotor disc and the second horizontal surface does not).

In order that the meaning of the term "raised surface structure" may be better understood with structures that constitute potential raised surface structures that are described in detail herein. A raised surface structure that is a wedge is defined herein as a five-sided structure that has two horizontal surfaces (typically an upper surface and a lower surface) of equal dimensions, two vertical surfaces that have equal dimensions, and a third vertical surface . A raised surface structure that is a ramp is defined here as a wedge as a structure with five sides that have only one horizontal surface, three vertical surfaces, and a surface that is neither horizontal nor vertical. An elevated diamond is defined as a six-sided structure that has two horizontal diamond-shaped surfaces and four vertical surfaces. Similarly, a raised hexagon is defined as an eight-sided structure that has two horizontal hexagonal shaped surfaces and six vertical surfaces.

The raised surface structure typically has dimensions that are not wider than the width of the third rotor disc and are not higher than the fins defining the flow channel where the raised surface structure is arranged. Typically, the raised surface structure is a solid structure having a displacement volume that represents from about 0.1 percent to about 25 percent of the volume of the fluid flow channel where the raised surface structure is disposed. Fluid flow channel volume is defined as the surface area of ​​the rotor discs between the fins defining the fluid flow channel multiplied by the maximum height of the fins defining the fluid flow channel. In one embodiment, the raised surface structure is a solid structure having a displacement volume representing approximately 1 percent to approximately 15 percent of the volume of the fluid flow channel in which the raised surface structure is disposed. . In an alternative embodiment, the raised surface structure is a solid structure that has a displacement volume that represents from about 5 percent to about 10 percent of the volume of the fluid flow channel volume where the raised surface.

The supersonic compression rotors provided by the present invention are useful as components of supersonic compressors. Thus, in one aspect, the present invention provides a supersonic compressor comprising a supersonic compression rotor of the present invention. The supersonic compressors provided by the present invention may comprise one or more additional features of additional supersonic compression rotors such as a conventional centrifugal compressor rotor (see for example, Figure 4). In certain embodiments, the supersonic compressor provided by the present invention may comprise a plurality of supersonic compression rotors of the invention. Thus, in one embodiment, the present invention provides a supersonic compressor comprising at least two supersonic compression rotors of the invention.

The supersonic compressors provided by the present invention can be used in a variety of applications. Thus, in one embodiment, the present invention provides a gas turbine comprising a supersonic compressor of the present invention.

In one aspect, the present invention provides a method of compressing a fluid. The fluid can be any fluid susceptible to supersonic compression, for example, carbon dioxide, natural gas, or a mixture comprising carbon dioxide and natural gas. Other suitable fluids that can be compressed in accordance with the method provided by the present invention, include hydrocarbons, low molecular weight allenes, such as methane and ethylene, and natural gas mixtures comprising natural gas, carbon dioxide, water vapor and hydrogen sulfide. Thus, in accordance with one embodiment, a process fluid, for example, a methane-C0 mixture₂, is introduced through the low pressure gas inlet into a gas line of a supersonic compressor and fed into the inlet side (low pressure side) of a rotating supersonic compression rotor of the present invention, the which rotates at a high speed, for example 10,000 rpm. A portion of the process fluid that encounters the low pressure side of the supersonic compression rotor passes into the flow channel of the supersonic compression rotor where the fluid is compressed. A portion of the compressed fluid exits the supersonic compression rotor on the high pressure side of the rotor and is removed from the supersonic compressor through the high pressure gas outlet.

In one embodiment, the method of the present invention employs a supersonic compression rotor that comprises two or more fluid flow channels. In an alternative embodiment, the method of the present invention employs a supersonic compression rotor that comprises at least three fluid flow channels. In one embodiment, the fluid flow channels are radial flow channels. In an alternative embodiment, the fluid flow channels are axial flow channels.

In one embodiment, the method of the present invention employs a supersonic compressor comprising a plurality of supersonic compression rotors, for example, two counter-rotating supersonic compression rotors of the invention arranged in series within a fluid line of the supersonic compressor . In one embodiment, the method of the present invention employs a supersonic compressor comprising at least one conventional centrifugal compressor rotor in addition to the at least one supersonic compression rotor of the invention.

Referring now to Figure 1, the Figure illustrates a supersonic compression rotor 100 of the present invention, the rotor comprising a first rotor disc 101, a second rotor disc 102 and a third rotor disc 103. The discs of the rotor 101-103 share a common axis of rotation. The first rotor disc 101 and the second rotor disc 102 are rotatably coupled by two fins 150. The third rotor disc 103 is disposed between the first rotor disc and the second rotor disc and can rotate independently relative to the first and second rotor discs. The third rotor disk 103 comprises on its surface a raised surface structure 110 that can rotate relative to the first rotor disk 101 and the second rotor disk 102 along a series of potential locations, shown as dotted line 111 and between the fins 150. The first rotor disk 101 is coupled to the drive shaft 300 through rotor support posts 160, which transfer mechanical energy from the drive shaft to the first rotor disk 101, which in turn engages rotatably with the second rotor disc 102 through the fins 150. The rotor discs 101-103 and the fins 150 together define a radial flow channel 108 that comprises the supersonic compression ramp 120 and provides fluid communication between the inner cylindrical cavity 104 and the outer edge (the outer edge of the rotor, refer to I element 112 of Figure 4) of the supersonic compression rotor.

During operation, the fluid entering the radial flow channel 108 from the internal cylindrical cavity 104 meets the supersonic compression ramp 120 at a supersonic speed adjusting an oblique impact wave 125 that is reflected back from the surface adjacent fin, which forms a reflected oblique impact void 127 and normal impact wave 109. The raised surface structures 110 can be placed anywhere along path 111 and between fins 150.

Referring now to Figure 2, the Figure illustrates an elongated portion of the supersonic compression rotor 100 of the present invention. The raised surface structure 110 is shown as a raised diamond-shaped structure ("raised diamond") coupled with the surface of the third disk of the rotor 103. The raised surface structure 110 is shown in this embodiment, as located between the fins 150 closer to fluid outlet 20 than fluid inlet 10. Figure 2 shows the supersonic compression rotor operating at supersonic speeds and indicates the location of the supersonic compression ramp 120, the oblique impact wave 125 formed as the fluid entering the radial flow channel 108 meets the ramp. of supersonic compressor. Figure 2 also indicates the presence of reflected impact wave 127, normal impact wave 129 and sub-sonic diffusion zone 121.

Referring now to Figure 3, the Figure shows an exploded view of an illustrative supersonic compression rotor 100 of the present invention. The Figure shows the third rotor disk 103 arranged between the first rotor disk 101 and the second rotor disk.

102. A set of six fins 150 rotatably couples the first rotor disc 101 to the second rotor disc 102. The rotor discs 101103 and fins 150 together define a set of six radial flow channels 108 (see Figures 1 and 2) defining a fluid inlet 10 and a fluid outlet 20. In Figure 3, each fin comprises a single supersonic compressor ramp 120 and the fins are arranged such that the supersonic compression ramp 120 is within the channel *

108 of radial flow adjacent to fluid inlet 10. On the surface of the third rotor disk 103 is arranged at regular intervals, a set of six raised surface structures 110 are comprised within each of the radial flow channels 108, respectively. The rotor support plate 105 is fixed with the fins 150 and also defines the radial flow channels 108. The rotor as a whole can be rotated at supersonic speed by rotating the drive shaft 300 which is mechanically coupled with the first rotor disc 101 through the rotor support posts 160. Drive shaft 300 passes through rotor support plate 105 through opening 303. The third rotor disk 103 can rotate independently through the drive shaft 301 which is connected to the third rotor disk 103 through the rotor support posts 163. In the embodiment shown, drive shaft 301 is not directly coupled to either the first or second rotor discs. By applying force to the drive shaft 301, the positions of the raised surface structures 110 within each of the radial flow channels can be varied to restrict or open a given portion of the radial flow channel 108.

With reference to Figure 4, the Figure illustrates an embodiment of the present invention and some basic attributes of its operation. The Figure illustrates a supersonic compressor 500 shown in an exploded view comprising a supersonic compression rotor 100 of the present invention and a conventional centrifugal compressor rotor 405 housed within compressor housing 510. Supersonic compression rotor 100 and conventional centrifugal compressor rotor 405 are said to be arranged within a fluid conduit of the supersonic compressor, the fluid conduit being defined at least in part by the compressor housing, the Fluid line comprises a low pressure side 520 and a high pressure side 522, referred to as the low pressure side of fluid line 520 and the high pressure side of fluid line 522, respectively. The view shown in Figure 4 is "exploded" in the sense that the conventional centrifugal compressor rotor 405 is shown as spaced from and over the internal cylindrical cavity 104 of the supersonic compression rotor 100. In various embodiments, the rotor 405 A conventional centrifugal compressor is actually disposed within the internal cylindrical cavity 104. Supersonic compression rotor 100 is driven by a combined drive shaft 300/301 in direction 310. Conventional centrifugal compressor rotor 405 is driven by drive shaft 320 in direction 330. As shown, the compression rotor Supersonic 100 and Conventional Centrifugal Compressor Rotor 405 are configured for counter-rotating motion. Fluid (not shown) introduced through the compressor inlet (not shown) enters the low-pressure side of fluid conduit 520 and finds the fins 406 of conventional centrifugal compressor rotor 405 rotating in direction 330. The Fluid flow direction 30 is changed as the fluid encounters the rotating conventional centrifugal compressor rotor. Fluid is directed radially outward from conventional centrifugal compressor rotor 405 disposed within internal cylindrical cavity 104 of supersonic compression rotor 100. The supersonic compression rotor 100 defines an internal cylindrical cavity 104 and an external edge 112 of the rotor and at least two radial flow channels 108 (not shown) that allow fluid communication between the internal cylindrical cavity 104 and the external edge 112 From the rotor, the radial flow channel comprises a supersonic compression ramp (not shown). In the embodiment shown in Figure 4, the supersonic compression rotor 100 comprises a rotor support plate 105 (rotor plate) and three rotor discs (not shown), a first rotor disc, a second rotor disc and a third rotor disc which together with the fins 150 and the rotor support plate 105 define at least two radial flow channels. The rotor support plate 105 defines an opening through which the conventional centrifugal compressor rotor 405 can be inserted into the internal cylindrical cavity 104. In the embodiment shown, supersonic compression rotor 100 is mechanically coupled with drive shaft 300/301 which provides rotation of the rotor as a whole, but also to rotate the third rotor disk 103 (not shown) relative to the first rotor disc 101 (not shown) and the second rotor disc 102 (not shown). In one embodiment, the drive shaft 300/301 comprises two concentric drive shafts, an inner shaft (not shown) that is mechanically coupled with the first rotor disc 101 (not shown) through the rotor support posts 160 (not shown) such as in Figure 1, and an external drive shaft that is mechanically coupled to the third rotor disc 103 (not shown) through the rotor support posts 163 (not shown) as for example in Figure 3. Fluid moving outward radially meets fluid inlet 10 (not shown) of rotating supersonic compression rotor 100 and is directed into radial flow channel 108 (not shown) which compresses passing fluid. from the inner cylindrical cavity 104 to the outer edge 112 of the supersonic compression rotor rotor. Radial flow channel 108 (not shown) comprises a supersonic compression ramp 120 (not shown) that compresses the radial flow channel and directs the compressed fluid toward fluid outlet 20. Fluid exiting fluid outlet 20 entering high pressure side of fluid line 522. The compressed fluid within the high pressure side of the fluid line 522 can be used for operation or can be used for some other purpose.

Referring to Figure 5, the Figure illustrates a supersonic compression rotor 100 of the present invention having supersonic axial flow compression characteristics. The supersonic compression rotor comprises a first rotor disk 101, a second rotor disk 102, and a third rotor disk 103 disposed therebetween. The three rotor discs together form an outer surface 117 of the supersonic compression rotor and share a common axis of rotation 116. The first and second rotor discs 101 and 102 are rotatably coupled through the fins 150, which together with the rotor discs 101-103 define two axial flow channels 109, the axial flow channels comprise an inlet 10 of fluid and a fluid outlet 20. The third rotor disc 103 can rotate, independently (rotate) relative to the first and second rotor discs, and comprises a raised surface structure 110. The fins 150 comprise a supersonic compression ramp 120 that forms part of the axial flow channel.

Figure 5a shows the supersonic compression rotor in operation under conditions where the raised surface structure is located downstream of the throat area of ​​the axial flow channel, the throat area is defined by the supersonic compression ramps 120 opposite each other. the other on the surface of the fins 150. The fluid encounters the rotating supersonic compression rotor through the fluid inlet 10 and is conducted along a spiral path (axial flow channel) through the outer surface of the supersonic compression rotor 117 until it meets the supersonic compression ramps 120 and is compressed and ejected through fluid outlet 20. The configuration shown in Figure 5a is appropriate for use during rotor startup.

Figure 5b illustrates the supersonic compression rotor in operation under conditions where the raised surface structure is located within the throat area of ​​the axial flow channel. The configuration shown in Figure 5b is suitable for use during steady state operation of the rotor. The direction of travel of the raised surface structure relative to its position in Figure 5a is shown as arrow 115 in Figure 5b.

Referring to Figure 6, the Figure also illustrates the supersonic compression rotor 100 illustrated in Figure 5, and provides additional detail. In the Figure, the drive shaft 300 is mechanically coupled with the first rotor disc 101 which is rotatably coupled with the second rotor disc 102 by two fins 150. A drive shaft 301 allows independent rotation of the third rotor disc 103 relative to the first and second rotor discs 101 and 102, allowing the position of the raised surface structure 110 within the axial flow channel 109 to be varied. During application, the supersonic compression rotor 100 shown in Figure 6 is typically disposed within the supersonic compressor housing (not shown). In Figure 6 (and Figure 7), the first rotor disc 101 and the third rotor disc 103 are shown separated by a gap 106 which is exaggerated and not to scale in order to distinguish the first rotor disc 101 of the third rotor disk 103. Similarly, the second rotor disk 102 is shown in the Figure, separated from the third rotor disk 103 by a gap 107. Again, this gap is exaggerated and not to scale to distinguish the second rotor disk 102 from the third rotor disk 103 in the Figure. As mentioned, the third rotor disc 103 is typically mounted in contact with both of the first rotor disc 101 and the second rotor disc 102.

Referring to Figure 7, Figure illustrates the supersonic compression rotor 100 of the present invention that does not rely on fins 150 to rotatably couple the first rotor disc 101 to the second rotor disc 102. Rather , the first and second rotor discs 101 and 102 are rotatably coupled by drive shaft 300 passing through the third rotor disc 103 through opening 303. The rotor discs 101-103 share a common axis of rotation (indicated by the axis of the drive arrow 300 in Figure 7). The drive shaft 300 is not in direct contact with the third rotor disk 103. In the embodiment shown in

Figure 7, the mechanical coupling between the first rotor disc 101 and the drive shaft 300 is made by the rotor support posts 160. The second rotor disc 102 is directly coupled (coupling not shown) with the drive shaft 300. The Figure shows the third rotor disk 103 arranged between the first rotor disk 101 and the second rotor disk 102. Rotor discs 101-103 and fins 150 together define two axial flow channels 109 defining fluid inlet 10 and fluid outlet 20. In Figure 7, each fin comprises at least one supersonic compression ramp 120 and the fins are arranged such that the supersonic compression ramps 120 are arranged within the axial flow channel 109 adjacent to the fluid inlet 10. Arranged on the outer surface of the third rotor disk 103 is a set of raised surface structures 110 that are comprised within each of the axial flow channels 109, respectively. The position of the raised surface structures 110 can be adjusted by independently applying a force to co-rotate the concentric drive shaft 301. Drive shaft 301 is coupled to third rotor disc 103 through rotor support posts 163. The rotor as a whole can be rotated at supersonic speed by co-rotating the drive arrows 300 and 301. The third rotor disc 103 is believed to be able to rotate independently of the first rotor disc 101 and the second rotor disc 102, via drive shaft 301. In the embodiment shown, drive shaft 301 is not directly coupled to either the first or second rotor discs. By applying force to the drive shaft 301 the positions of the raised surface structures 110 within each of the radial flow channels can be varied to restrict or open a given portion of the axial flow channel 109. Those skilled in the art will appreciate that the drive shaft 301 co-rotates with the drive shaft 300 to prevent contact between the rotor support posts 160 and the rotor support posts 163, and that the positions of the Rotor support posts 163 can be varied within an arc limited by rotor support posts 160, and this corresponds to the potential locations of the raised surface structures 110 within the axial flow channels 109. In the supersonic compression rotor illustrated in Figure 7 the fins 150 are coupled to the surface of the first rotor disk 101 but are not coupled to the second rotor disk 102. The fins 150 are separated from the surface of the second rotor disc by a gap (not shown) which in embodiments, where the first rotor disc and the second rotor disc are not rotatably coupled to the fins 150, typically is within the order of a fraction of a millimeter to a few millimeters. In one embodiment, the clearance between the second rotor disc and the fins is within the range of about 0.01 millimeters to about 1 millimeter.

In another embodiment, the present invention provides a method of starting a supersonic compressor. The method comprised (a) providing a supersonic compressor comprising a supersonic compression rotor disposed within a fluid line of the supersonic compressor, for example, a resting supersonic compression rotor. The supersonic compressor comprises a supersonic compression rotor of the present invention, for example, the supersonic compression rotor illustrated in Figure 6. The supersonic compression rotor comprises (i) a first rotor disc 101, (ii) a second rotor disc 102 and (iii) a third rotor disc 103, the first, second and third rotor discs share a common axis of rotation. Typically, the common axis of rotation corresponds to the axis of rotation of one or more drive arrows (see Figure 6, drive arrows 300 and 301) used to drive the supersonic compression rotor. The first and second rotor discs are rotatably coupled. Mechanical coupling causes the first rotor disc and the second rotor disc to rotate as a unit and can be effected by means of two or more fins 150 mounted on the external surfaces of the first rotor disc and the second rotor disc. Alternatively, mechanical coupling of the first rotor disc and the second rotor disc can be accomplished by other means, for example by having the first rotor disc and the second rotor disc coupled with a common drive shaft 300 (see , for example, Figure 7). In some embodiments, the first rotor disc and the second rotor disc are mechanically coupled by a combination of means, for example, by a common drive shaft 300 and fins 150. The third rotor disc is disposed between the first and the second rotor discs and can rotate independently relative to the first and second rotor discs. The third rotor disc comprises a raised surface structure 110 located on an external surface of the third rotor disc. The raised surface structure resides within a radial or axial flow channel defined by the first, second, and third rotor discs along with at least two fins. The flow channel comprises a supersonic compression ramp on one or more surfaces that define the flow channel. Using the means to independently rotate the third rotor disc relative to the first rotor disc and the second rotor disc, for example, the drive shaft 301 coupled with the rotor support posts 163 (see Figure 7 ), the raised surface structure is positioned within the flow channel, so that the throat area of ​​the radial flow channel is relatively less restricted. The throat area of ​​the flow channel is the portion of the flow channel restricted by the supersonic compression ramp 120 d and is illustrated by the space between the supersonic compression ramp and a surface of the flow channel opposite the supersonic compression ramp (See for example, Figure 5, where the throat area of ​​the flow channel is shown as the space between the opposing supersonic compression ramps 120). At low speeds, eg, sub-sonic speeds, it is desirable that the throat area of ​​the flow channel be less restricted than at higher speeds. Figure 5a illustrates this placement of the raised surface structure within the flow channel, so that the throat area of ​​the flow channel is relatively less restricted relative to Figure 5b, which illustrates the placement of the surface structure 110 elevated within flow channel 109, so that the throat area is relatively less restricted than the configuration shown in Figure 5a. Thus, Figure 5a illustrates the convenient placement of the raised surface surface 110 during startup when the supersonic compression rotor is rotated at subsonic speeds, and Figure 5b illustrates the convenient placement of the raised surface structure 110 during ia steady state operation when the supersonic compression rotor is rotated at supersonic speeds. As the speed of the supersonic compression rotor changes from a sub-sonic regime to a supersonic regime, the elevated surface structure can be relocated from a first position within the flow channel to a second position within the flow channel by the application of a force on the third rotor disc through, for example, the drive shaft 301 and the rotor support posts 163. Those skilled in the art will appreciate that the throat area of ​​the flow channel is relatively more restricted in the configuration shown in Figure 5b than it is in the configuration shown in Figure 5a. This ability to open the throat area of ​​the supersonic compression rotor at lower speeds and restrict the throat area of ​​the supersonic compression rotor at higher speeds, allows a unique and efficient means of starting the supersonic compressor.

This written description uses examples to describe the invention, including the best mode, and also to enable persons skilled in the art to practice the invention, including making and using any device or system, and carrying out any incorporated method. The patentable scope of the invention is defined by the claims and may include other examples contemplated by those skilled in the art. Such other examples are intended to be within the scope of the claims when they have structural elements that do not differ from the literal language of the claims or when they include equivalent structural elements with substantial differences from the literal language of the claims.