Exhaust system of the a gas turbine section

Description of the invention

The present invention relates to a gas turbine system, and more particularly to an exhaust section of a gas turbine.

A turbine engine burns a mixture of fuel and compressed air to produce hot exhaust gas that propels the turbine blades to rotate. The rotation of the turbine blades causes rotation of the shaft supported by the bearings. The rotation of the shaft generates a significant amount of heat in the bearings, and the hot exhaust gas escaping through the exhaust section of the turbine transfers the heat to the components of the exhaust section of the turbine. Unfortunately, this heat can damage turbine components in the absence of adequate cooling in the exhaust section of the turbine.

From publication US 6578363 a turbine system is known comprising a system for cooling an exhaust section comprising an outer shell structure, an outer exhaust wall positioned along the exhaust flow channel, and an outer cavity positioned between the outer exhaust wall and the outer shell. The exhaust turbine section also includes an internal structure having an internal exhaust wall located along the exhaust flow passage, an internal cavity located between the internal exhaust wall and the internal housing, and a bearing cavity located between the internal housing and the bearing housing. According to this embodiment, the exhaust section of the turbine comprises a cooling air inlet located at the end of the exhaust cover of the section and an outlet of cooling air situated in the flow direction of the exhaust cover of the section at the beginning. The cooling air enters at the end of the section and exits at the beginning of the section into the cavity of the last stage of the turbine. In this solution, the cooling air washes only the cover of the exhaust section and only lowers the temperature of this part.

There is a need to provide a more perfect cooling system for the exhaust section of the gas turbine.

According to one aspect of the invention, a gas turbine system comprising an exhaust turbine section that includes an exhaust flow conduit; an outer structure having an outer shell, an outer exhaust wall located along the exhaust flow channel, and an outer cavity located between the outer exhaust wall and the outer skirt; and includes an internal structure having an internal exhaust wall located along the exhaust flow channel, an internal cavity located between the internal exhaust wall and the internal housing, and a bearing cavity located between the internal housing and the bearing housing, characterized in that it comprises a spacer extending between the external structure and the internal structure. , the spacer includes a first flow passage configured to guide fluid from the inner cavity to the outer cavity.

Preferably, the spacer comprises an inner body and an outer body, the first flow passage being disposed between the inner body and the outer body.

Preferably, the inner body comprises a load bearing structural support and the outer body is not a load bearing.

Preferably, the inner body is a solid body.

Preferably, the spacer comprises a second flow channel disposed between the inner body and the outer body, the first flow channel configured to guide fluid from the first portion of the inner cavity to the outer cavity, and the second flow channel configured to guide fluid from the second portion of the inner cavity to the outer cavity. recess.

Preferably, the turbine system comprises a second flow conduit located downstream of an end portion of the exhaust section of the turbine, the second flow conduit configured to guide fluid into the inner cavity.

Preferably, the second flow passage is located within the hatch of the exhaust section of the turbine.

Preferably, the inner cavity includes at least one opening in the inner housing, the at least one opening configured to guide fluid from the bearing cavity into the first flow channel.

Preferably, the opening is positioned upstream of the first flow passage.

Preferably, the opening is located downstream of the first flow passage.

PL 220 729 B1

Preferably, the outer exhaust wall has a plurality of openings configured to guide fluid from the outer cavity into the exhaust flow channel, each of the plurality of openings including a removable insert.

According to a further aspect of the invention, a gas turbine system comprising an exhaust turbine section that includes an exhaust flow passage; an outer structure having an outer shell, an outer exhaust wall located along the exhaust flow channel, and an outer cavity located between the outer exhaust wall and the outer skirt; an inner structure including an inner exhaust wall positioned along the exhaust flow channel, and an inner cavity positioned between the inner exhaust wall and the inner shell and a bearing cavity between the inner shell and the bearing housing, characterized in that it comprises a spacer extending between the outer structure and the inner structure , the strut comprises a first flow passage configured to guide fluid from the inner cavity to the outer cavity and a second flow passage located downstream of an end portion of a turbine exhaust system, the second flow passage configured to guide fluid into the inner cavity.

Preferably, the bearing cavity includes at least one opening in the baffle wall, the at least one opening configured to guide fluid from the bearing cavity to the exhaust cavity.

Preferably, the second flow passage is located within the hatch of the exhaust section of the turbine.

Preferably, the spacer comprises an inner body and an outer body, the first flow passage being disposed between the inner body and the outer body.

Preferably, the inner body is a solid body.

Preferably, the inner body is a load bearing structural support and the outer body is not a load bearing.

According to yet another aspect of the invention, a gas turbine system comprising an exhaust turbine section that includes an exhaust flow passage; an outer structure having an outer shell, an outer exhaust wall located along the exhaust flow channel (56), and an outer cavity located between the outer exhaust wall and the outer skirt; and includes an internal structure including an internal exhaust wall located along the exhaust flow passage, an internal cavity located between the internal exhaust wall and the internal housing, and a bearing cavity located between the internal housing and the bearing housing; characterized in that it comprises a spacer extending between the outer structure and the inner structure, the spacer including a first flow channel configured to guide fluid into the inner cavity and a second flow channel configured to guide fluid from the inner cavity to the outer cavity.

Preferably, the spacer comprises an inner body and an outer body, the first flow passage is provided in the inner body and the second flow passage is provided between the inner body and the outer body.

Preferably, the inner body is a load bearing structural support and the outer body is not a load bearing.

The technical effects of the invention include the ability to cool multiple components of the exhaust turbine section with a single blower. In particular, the invention allows the struts, bearings and other parts of the internal structure of the exhaust turbine section to be cooled by a single blower. For example, struts may be configured with one or more channels to direct the air flow both inside and outside the inner structure to simultaneously cool the struts, bearings, etc. In one embodiment, each strut includes at least two channels to direct the flows. air in opposite directions to the inside and outside of the internal structure. In another embodiment, one strut may include at least one passage to direct air out of the inner structure. In this embodiment, air may be introduced at or near the strut, viewed in the flow direction.

The subject matter of the present invention is shown in the exemplary embodiments of the drawing, in which like reference numerals represent like parts throughout the figures, and wherein: Fig. 1 is a simplified flow diagram of an embodiment of a turbine system having a gas turbine engine that can use exhaust section cooling; Fig. 2 is a sectional side view

A transverse embodiment of the gas turbine engine of FIG. 1 taken through a longitudinal axis, illustrating an embodiment of an exhaust section cooling system; Fig. 3 is a cross-sectional side view of the embodiment of the gas turbine engine of Fig. 2, included within line 3-3 of Fig. 2, illustrating the cooling of the exhaust section by the exhaust cooling system of Fig. 2; Fig. 4 is a cross-sectional view of the embodiment of the strut of Fig. 3 along line 4-4; Fig. 5 is a cross-sectional view of the embodiment of the strut of Fig. 3 taken along line 4-4; Fig. 6 is a cross-sectional view of the embodiment of the strut of Fig. 3 taken along line 4-4; Fig. 7 is a section view of the strut and the outer exhaust wall of Fig. 3 taken along line 7-7; fig. 8 is a cross-sectional view of an embodiment of removable inserts that may be inserted into one or more outer exhaust wall openings of Figure 7 taken along line 8-8; Fig. 9 is a cross-sectional side view of the embodiment of the gas turbine engine of Fig. 1 taken along a longitudinal axis illustrating an embodiment of the cooling system of the exhaust section ; fig. 10 is a cross-sectional side view of the embodiment of the combustion turbo engine of Fig. 9, contained within line 10-10, illustrating the cooling of the exhaust section by the cooling system of the exhaust section of Fig. 9; Fig. 11 is a cross-sectional view of the embodiment of the spacer of Fig. 10 taken along line 11-11; and Fig. 12 is a cross-sectional view of the embodiment of the strut of Fig. 10 taken along line 11-11.

Some examples falling within the claimed scope of the invention are presented below. These embodiments are not intended to limit the scope of the claimed invention, but rather merely provide an illustration of possible embodiments of the invention. In fact, the invention may encompass many different forms which may be similar to or different from the embodiments shown below.

In order to provide a concise description of these embodiments, not all features of an actual implementation may be described in the specification. It should be noted that in the course of developing any such actual implementation, as in any engineering or construction project, numerous implementation-specific decisions must be made by contractors in order to achieve the stated intent, such as compliance with layout constraints and area of ​​operation. which may vary depending on implementation. Moreover, it should be noted that such a development effort may be complex and time consuming, but would nevertheless be a routine undertaking to design, fabricate and manufacture for those of average skill using this disclosure.

The elements of various embodiments of the present invention when presented in the singular are intended to mean that there are one or more elements. The terms "comprising", "including" and "having" are intended to be inclusive and mean that there may be additional elements other than the listed elements.

As described in more detail below, the disclosed embodiments allow the cooling and cleaning of various components (e.g., bearings, struts, outer exhaust, inner structure, etc.) in the exhaust section of a gasoline engine. For example, some embodiments include a spacer operable to direct cooling fluid (e.g., air) from the internal structure of a gas turbine engine to an external structure of the gasoline engine. In certain example embodiments, cooling fluid may be supplied to the internal structure of the gasoline engine at or near a location (e.g., through a hatch) located downstream of the gas turbine engine. The coolant directed through the inner structure to the outer structure cools the bearings and other components of the exhaust section of the gas turbine engine. Other embodiments may include a bi-directional strut which allows cooling fluid to be blown through the first strut flow channel into the inner structure and back through the second strut flow channel from the inner structure to the outer structure.

As such, the coolant can remove heat (e.g., cool) from the bearings, inner exhaust wall, rear of the inner structure, etc. while adjusting the temperature of the outer structure (e.g., outer exhaust wall). In some embodiments, cooling fluid may drain into the exhaust flow conduit. Moreover, in certain example embodiments, a plurality of different inserts may be selectively seated into openings in the inner structure or outer structure to control the outgoing amount. For example, some of the inserts may completely block the flow of coolant, while others reduce the amount of coolant flow to the exhaust flow channel. Additionally, in certain example embodiments, multiple tuning regions may be used to regulate the flow of cooling fluid from the inner structure to the strut and / or between recesses of the inner structure.

Figure 1 shows a simplified flow diagram of an embodiment of a turbine system 10 including a gas turbine engine 12 which may use an exhaust section with a cooling system according to the invention. For example, system 10 may include exhaust section cooling system 11 having one or more cooling flow channels in the exhaust section spacer. In some embodiments, the turbine system 10 can be an aircraft, locomotive, or a combination of power generating systems. The illustrated gasoline engine 12 includes an air intake section 16, a compressor 18, a combustion chamber section 20, a turbine 22, and an exhaust section 24. The turbine 22 is connected to a compressor 18 via a shaft 26. As indicated by the arrows, air may enter the gasoline engine 12 through intake section 16 and flow to a compressor 18 which compresses air before entering the combustor section 20. The illustrated combustor section 20 includes a combustor housing 28 located concentrically or annularly around the shaft 26 between compressor 18 and turbine 22. Compressed air from compressor 18 enters combustion chambers 30 where compressed air can mix and burn with fuel within combustion chambers 30 to drive turbine 22. Hot exhaust gas flows from combustion chamber section 20 through turbine 22, driving compressor 18 through shaft 26. For example, the exhaust gas may exert driving forces on the turbine rotor blades inside the turbine 22 to rotate the shaft 26. After passing through turbine 22, hot exhaust gas may exit the turbo engine 12 through exhaust section 24. As described below, exhaust section 24 may include a plurality of struts each having one or more cooling flow channels for cooling 11 of the exhaust section.

Figure 2 is a cross-sectional side view of the embodiment of the gas turbine engine 12 of Fig. 1 taken through a longitudinal axis, illustrating an embodiment of the cooling system 11 of the exhaust section. As described above with reference to Fig. 1, air may enter the gasoline engine 12 through the air intake section 16 and may be compressed by the compressor 18. Compressed air from compressor 18 may then be directed to combustion chamber section 20 where the compressed air may be mixed with fuel. Combustion chamber section 20 includes one or more combustion chambers 30. In certain example embodiments, gasoline engine 12 may include a plurality of combustion chambers 30 arranged in a ring pattern. Moreover, each combustion chamber 30 may include a plurality of fuel nozzles 32 connected to or near the front end of each combustion chamber 30 in an annular or other arrangement. In operation, the fuel nozzles 32 can inject the fuel-air mixture into the combustion chambers 30 in the correct proportion to ensure optimal combustion, emissions, fuel consumption and power output. Within the combustion chamber section 20, the fuel-air mixture may be combusted to produce hot pressurized exhaust gas. After combustion, the hot pressurized exhaust gas may escape from combustion chamber section 20 and flow through transition portion 34 to turbine 22. Inside the turbine 22, the pressurized exhaust gas can rotate vanes 36 that extend radially inside the turbine 22 to rotate the shaft 26 before exiting the exhaust section 24 as exhaust gas.

The exhaust section 24 may include an inner structure 38, at least one strut 40, and an outer structure 42. Spacer 40 provides support between the outer structure 42 and the inner structure 38. As hot exhaust gas escapes, turbines 22 and shaft 26 rotate, exhaust section 24 may be subjected to high temperature conditions. More specifically, the high temperature conditions can cause thermal stress, wear, and / or damage to the strut 40, inner structure 38, and outer structure 42. Accordingly, in the illustrated embodiment, the cooling system 11 of the exhaust section includes a blower 44 connected to a control device 46 that controls the flow of cooling air through the inner structure 38, strut 40, and outer structure 42 to reduce thermal stress and wear of these components and parts in placed them.

In the embodiment illustrated in FIG. 2, the spacer 40 defines the outer body 48 and the inner body 50. The inner body 50 defines one flow channel 52 (e.g., the inner flow channel), and the outer body 48 defines a second flow channel 53 (e.g., the outer flow channel). ) of the cooling system 11 of the exhaust section. As described more

In detail below, in the embodiment illustrated in FIG. 2, the first and second flow channels 52 and 53 are spaced apart to allow two-way flow of cooling fluid (e.g., air) through the strut 40. Although the illustrated strut 40 includes with only two separate flow channels 52 and 53, the spacer 40 may include any number of separate flow channels to direct a cooling fluid (e.g. air) to and from various portions of inner structure 38, outer structure 42, and strut 40. As illustrated, blower 44 (controlled by control 46) blows cooling air 58 through outer structure 42 through strut 40 (i.e., first flow passage 52). inner casing 50) and inner structure 38. The source of cooling air 58 may be a compressor 18 of a gasoline engine 12 or some other source of external air. Cooling air 58 circulates through inner structure 38 and then exits through outer body 48 of strut 40. After flowing through strut 40 into and from inner structure 38, cooling air 58 enters outer structure 42 to exit into outer flow channel 56. As described in more detail below, the exhaust section cooling system 11 allows a single blower 44 to cool the strut 40 while removing heat from the bearing cavity of the inner structure 38.

Moreover, in certain example embodiments, the inner body 50 of strut 40 is a load bearing structural support configured to transmit significant mechanical loads between the inner 38 and outer 42 structures of exhaust section 24, while outer body 48 of strut 40 is not a load bearing structural support. For example, outer body 48 may be included to protect inner body 50 by blocking heat from inner body 50. In particular, outer body 48 may be designed to guide cooling air externally along inner body 50 to provide a thermal barrier between inner body 50 and hot exhaust gases in exhaust section 24. The outer body 48 may also have a higher thermal resistance compared to the inner body 50. For example, the inner body 50 may have a lower temperature limit than the outer body 48. In some embodiments, the inner body 50 may have a lower temperature limit than the temperature of the hot exhaust gas. while the outer body 48 may have a temperature limit well above the temperature of the hot exhaust gas. In this way, the outer body 48 thermally protects the inner body 50 so that the inner body 50 is able to efficiently transmit mechanical loads between the inner and outer structures 38 and 42 of the exhaust section 24.

Figure 3 is a cross-sectional side view of an embodiment of the gas turbine engine 12 of Fig. 2 contained within line 3-3, illustrating the cooling of the exhaust section by the cooling system 11 of the exhaust section of Fig. 2. The structure of the strut 40 allows cooling of the strut 40, the outer structure 42 and internal structure 38 by a single blower 44. As illustrated in Fig. 3, the internal structure 38 defines an internal exhaust wall 80, a bearing cavity 82, a bearing assembly 84 housed in a bearing housing 85, a grease (e.g., oil) passage 86, a first baffle (e.g., sleeve) 88, a second baffle (e.g., a disc) 90. , a bearing support wall 92 (e.g., to which reference is also referred to herein as the inner shell), and rear rotor shaft recess 94. As illustrated, the inner structure 38 includes an inner cavity 91 between the inner exhaust wall 80 and the inner shell 92, and a bearing cavity 82 between the inner shell 92 and the bearing housing 85.

As described above, the blower 44 blows cooling air 58 through the inner body 50 of the strut 40. The cooling air 58 convectionally cools the first flow passage 52 in the inner body 50, thereby reducing the likelihood of thermal stress failure in the strut 40. After passing through the strut 40 the cooling air 58 enters the inner structure 38. More specifically, cooling air 58 passes through the bearing support wall 92 and into bearing cavity 82 where it cools the bearing assembly 84. The bearing assembly 84 generates a significant amount of heat as its bearings rotate as the shaft 26 rotates. Accordingly, the flow of cooling air convection cools the bearing assembly 84 to reduce premature wear or damage caused by heat.

Upon contacting the bearing assembly 84, the cooling air 58 is split into two air flows 100 and 102 in opposite axial directions as indicated by arrows 96 and 98. Airflow 100 moving in the axial direction 96 with the current contacts the second baffle (e.g. a disc) 90 that directs the air flow 100 radially towards the first

The baffles (e.g., sleeves) 88. A first baffle (e.g., sleeve) 88 directs the air flow 100 axially along the lubricant channel 86. As illustrated, the baffles 88 and 90 concentrate and restrict (e.g., creating a funnel) the flow of air 100 along the lubricant channel 86 thereby improving convection cooling of the lubricant channel 86. After the first partition comes out (e.g. sleeve) 88, the air flow 1 passes along the inner exhaust wall 80 at the downstream end 81 of the inner structure 38, thus cooling the end portion 81 and entering the exhaust recess 95 of the inner structure 38. Again, the baffles 88 and 90 they can force air flow to pass along inner shell 92, thereby improving convective cooling of inner shell 92. Upon reaching the strut 40, the airflow 100 then travels through the second flow passage 53 of the outer body 48 and into the outer structure 42.

Unlike airflow 100, airflow 102 travels in the opposite axial direction (i.e., upstream) as shown by arrow 98. While moving upstream along arrow 98, airflow 102 passes through bearing assembly 84, and then it enters the rear turbine rotor space 94. The airflow 102 then travels towards the inner exhalation wall 80, where a portion of the airflow 102 exits through the slot 104 into the exhaust passage 56. The remainder of the airflow 102 returns to the strut 40 where it enters the outer body 48 and travels through the other. flow channel 53 to outer structure 42.

The outer structure 42 includes an outer exhaust wall 106 and an outer skirt 108 that define an intermediate outer cavity 110 (e.g., an annular space). As air 100 and 102 exits the strut 40, it enters the outer cavity 110 to regulate the temperature of the outer structure and 42 before flowing into the exhaust flow channel 56. For example, air 100 and 102 drains into the exhaust flow channel 56 through openings 112 in the outer exhaust wall 106. In some embodiments, the inner exhaust wall 80 may also include openings 112 for draining air flow into the exhaust flow channel 56. As illustrated, the outer structure 42 includes both a cooled air flow 58 and a heated air flow 100 and 102 that are separate from each other. The two airflows can be adjusted to control the temperature in the outer structure 42. For example, the ratio of the two airflows can be adjusted by varying the sizes of the first and second flow channels 52 and 53, the number and sizes of openings 112 in the inner and outer exhaust walls. 80 and 106 etc.

Figure 4 is a cross-sectional view of the embodiment of the strut 40 of Figure 3 taken along line 4-4. As described above, the spacer 40 shown in Fig. 4 includes an outer body 48 disposed around inner body 50. As shown, outer body 48 defines a second flow passage 53, a leading edge 54 and a trailing edge 55, while inner body 50 comprises a first flow passage. 52. In this embodiment, the outer body 48 has an oval shape (e.g., the shape of a carrier panel), while the inner body 50 has a rectangular shape. In other embodiments, the inner and outer bodies 50 and 48 may have other shapes such as a rectangle in a rectangle, a carrier sheet in a carrier sheet, an oval in an oval, etc. Regardless of the particular shapes, the inner and outer bodies 50 and 48 are arranged one inside each other. (e.g. coaxial). The two flow channels 52 and 53 provide bidirectional airflow between the inner and outer structures 38 and 42. For example, the first flow conduit 52 may direct the air flow internally from the outer structure 42 to the inner structure 38, while the second flow conduit 53 directs the air flow away from the outer structure 38 and 42. inner structure 38 to outer structure 42, or vice versa. In some embodiments, each flow conduit 52 and 53 may be configured to direct air into a specific zone of inner structure 38. In each embodiment, first and second flow conduits 52 and 53 in strut 40 allow cooling of strut 40, inner structure 38, and outer structure 42. by a single blower 44. In the internal structure 38, airflow can be directed to different zones to improve convection cooling before draining to exhale.

Figure 5 is a cross-sectional view of the embodiment of the strut 40 of Figure 3 taken along line 4-4. The spacer 40 illustrated in Figure 5 includes an outer body 140 disposed around the inner body 142 (e.g., coaxial). The outer body 140 defines

Flow channel 143, leading edge 144, and trailing edge 145. The outer body 140 may define any number of shapes, such as oval, carrier lobe, teardrop, rectangular, square, circular, or generally elongated. An outer body 140 is disposed around an inner body 142 that is dimensioned smaller than the outer body 140 to define a flow channel 143. As illustrated, flow channel 143 is divided by walls 150 to define flow channels 146 and 148. In other embodiments, flow channel 143 may be further subdivided by walls 150 to define any number of flow channels (e.g., 1, 2, 3). , 4, 5, 6, 7, 8, 9, 10 or more flow channels). Similar to the outer body 140, the inner body 142 can define any number of shapes, such as oval, flap, teardrop, rectangular, square circular, or generally elongated. Although the illustrated inner body 142 includes a single flow channel 152, the inner body 142 may include any number of flow channels (e.g., 1, 2, 3, 4, 5, 6, 7, 8, 3, 10 or more flow channels). As described above, the flow channels 146, 148 and 152 allow a single blower 44 to blow cooling air 58 which cools the strut 40, outer structure 42 and inner structure 38 while clearing the bearing cavity 82 of heated air. In addition, the plurality of flow channels may allow dedicated coolant flows (e.g., air flows) to and / or from specific zones of the internal structure 38 of the exhaust section 24. For example, dedicated air flows may be directed to / from the bearing assembly 84, end portion 81 of inner structure 38, exhaust cavity 95 of inner structure 38, rear turbine rotor cavity 94, etc.

Figure 6 is a cross sectional view of the embodiment of the strut 40 of Figure 3 taken along line 4-4. The spacer 40 illustrated in FIG. 6 includes an outer body 170 disposed around an inner body 172. The outer body 170 defines a flow channel 173, a leading edge 174, and a trailing edge 175. Outer body 170 can define any number of shapes, including oval, flap, teardrop, rectangular, square, circular, or generally elongate, and includes a flow channel 173. Outer body 170 is disposed around inner body 172. As illustrated, inner body 172 it defines two flow channels 176 and 178 separated by a wall 180. In other embodiments, more walls 180 may define additional flow channels in the inner body 172 (e.g., 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, or more flow channels). Similar to the outer body 170, the inner body 172 can define any number of shapes, such as oval, flap, teardrop, rectangular, square, circular, or generally elongated. As described above, the flow channels 174, 176, and 178 allow one blower 44 to blow cooling air 58 which cools strut 40 and inner cavity 38 while clearing bearing cavity 82 of heated air. In addition, the plurality of flow channels may allow dedicated coolant flows (e.g., air flows) to and / or from specific zones of the internal structure 38 of the exhaust section 24. For example, dedicated air flows may be directed to / from the bearing assembly 84, end portion 81 of inner structure 38, exhaust cavity 95 of inner structure 38, rear turbine rotor space 34, etc.

Figure 7 is a sectional view of a strut 40 and outer exhaust wall 106 illustrating the drain holes 112 taken along line 7-7 of Figure 3. As explained above, cooling air 58 sweeps through the bearing cavity 82 where it flows through the second flow passage 53 in the strut. 40 to the outer structure 42 having an outer exhaust wall 106. In outer structure 42, airflow passes through outer cavity 110 and then drains into exhalation flow channel 56 through openings 112 in outer exhaust wall 106. As shown in Fig. 7, openings 112 can form a variety of shapes (e.g. oval, elongated, polygonal or cross-shaped) and may be arranged in other patterns (e.g., staggered, circular, rectangular or irregular). In addition, the sizes of the openings 112 may vary depending on their location. For example, the diameter of the holes 112 may gradually vary with the distance from the strut 40. In some embodiments, the holes 112 may be arranged in groups (e.g., from 1 to 100 holes 112) that are spaced apart from each other. In addition, the openings 112 may be approximately 0-180 degrees with respect to the axis of rotation of the gasoline engine 12. For example, the holes 112 may be at an angle of 15, 30, 45, 60, 75, 90, 105, 120, 135, 150, or 165 degrees from the axis.

Figure 8 is a cross-sectional view of an embodiment of removable inserts 202, 204, and 206 that may be inserted into one or more holes 112 of Figure 7, taken along

PL 220 729 B1 along line 8-8. As shown in Fig. 8, each opening 112 can selectively accommodate a plurality of different inserts, such as inserts 202, 204, and 206. Inserts 202, 204 and 206 can assist in controlling the amount of air entering the exhalation flow channel 56 of Fig. 3 through the openings. 112 of outer exhaust wall 106. For example, each insert 202, 204, and 206 may provide a different amount of restriction to opening 112. Thus, a plurality of different inserts 202, 204, and 26 may be attached to openings 112 to control the flow distribution through the outer exhaust wall 106, thereby controlling the temperature distribution in the outer exhaust wall 106.

As illustrated, insert 202 includes a body portion 208, a protrusion portion 210, and an opening 212. A body portion 208 fits into opening 112, while a portion of protrusion 210 abuts the inner surface 214 or outer surface 216 of the outer exhaust wall 106. The body portion 208 may fit into the opening 112. be connected to the outer exhaust wall 106 by an interference fit, threads, weld, bolts, or other fitting. As illustrated, opening 212 defines a diameter 218 which is smaller than the diameter 220 of opening 112. Accordingly, when inserted, the insert 202 will reduce the size of the opening 112, which then restricts air flow into the exhaust flow channel 56. Similar to insert 202, insert 204 includes a body portion. 222 and part of the projection 224. A portion of the body 222 fits into the opening 220, while a portion of the projection 224 contacts the inner surface 214 or outer surface 216 of the outer exhaust wall 106. As illustrated, the insert 204 does not include an opening and therefore fills the entire opening 112 thereby blocking cooling air. before draining into exhalation flow channel 56. Insert 206 similarly includes a body portion 226, a projection portion 228, and an opening 230. A portion of the body 226 fits into the opening 112, while the protrusion 228 abuts the inner surface 214 or outer surface 216 of the outer exhaust wall 106. As shown, the opening 230 defines a diameter 232 that is smaller than the diameter 220 of the opening 112 but larger than the diameter. 218 inserts 202. Accordingly, once inserted, the liner 206 reduces the size of the opening 112, which then restricts air flow into the exhalation flow channel 56 by a smaller amount than the liner 202.

Although the illustrated embodiment only includes three inserts 202, 204, and 206, any number of inserts with different restriction holes may be used in the gasoline engine 12. These inserts 202, 204 and 206 control the amount and distribution of air flow through the outer exhalation wall 106 and into the exhalation flow channel 56. For example, inserts 202, 204, and 206 may be used in the various openings 112 to control cooling of the outer structure 42 in a more uniform manner. As a result, the selective use of these inserts 202, 204 and 206 can reduce temperature gradients and thermal stresses in the outer structure 42.

The embodiments described above with reference to Figs. 2-8 include a bi-directional spacer (e.g., spacer 40 shown in Fig. 2) that allows the bearing assembly 84 and other components of the exhaust section of the gasoline engine 12 to be cooled by a single blower 44. cooling air. In particular, in the embodiment illustrated in Fig. 2 and 3, the bi-directional spacer 40 includes a first flow passage 52 within the inner body 50 and a second flow passage 53 between the outer body 48 and the inner body 50. As described above, cooling air 58 may be blown through the first flow passage 52 into the inner structure 38 and thereafter back through second flow channel 53 to outer structure 42 and then drain into exhalation flow channel 56.

However, in other embodiments, the spacer may include only one flow channel or only one flow direction (e.g., with one or more flow channels) while still being able to direct cooling air from the inner structure 38 through the spacer. For example, Fig. 9 is a cross-sectional side view of the embodiment of the gas turbine engine 12 of Fig. 1 guided through a longitudinal axis, illustrating an embodiment of the cooling system 11 of the exhaust section. In the embodiment illustrated in Figs. 9, the exhaust section 24 includes at least one strut 290 that provides support between the outer structure 42 and the inner structure 38. Similar to the strut 40 illustrated in Figs. 2 and 3, the strut 290 illustrated in Fig. 9 defines outer body 292 and inner body 294. However, unlike the hollow inner body 50 of the strut 40 illustrated in Figures 2 and 3, the inner body 294 of the strut 290 illustrated in Figure 9 is a solid body that does not.

No flow channel is defined within it. As such, the area between the outer body 292 and the solid inner body 294 only defines a flow passage 296 in the strut 290 for the cooling system 11 of the exhaust section illustrated in Fig. 9.

As shown in Fig. 9, a blower 298 (e.g., similar to the blower 44 shown in Figs. 2 and 3) may be controlled by a controller 300 (e.g., similar to the controller 46 of Figs. 2 and 3) to blow air. cooling 302 (e.g., similar to cooling air 58 of Figs. 2 and 3) first through the inner structure 38 and then through the outer structure 42. For example, as illustrated in Fig. 9, in certain example embodiments, blower 298 may be configured to blow cooling air 302 through the interior volume of manhole 304 of exhaust section 24 (e.g., in the rear diffuser zone). The source of cooling air 302 may be the compressor 18 of the gasoline engine 12 or some other source of outside air. Regardless of the precise location where the cooling air 302 is supplied to the inner structure 38, the cooling air 302 is supplied at or near the location downstream of the exhaust section 24. In other words, a portion of the cooling air 302 is supplied to the inner structure 38 as viewed at flow direction, spacer 290, and bearing assembly 84, among other components of exhaust section 24. A portion of the cooling air 302 blown into the inner structure 38 circulates through the inner structure 38 (e.g., through the bearing assembly 84) and then exits through the flow channel 296 of the strut 290 and into the outer structure 42 to drain into the exhaust duct 56. As with the examples, 2 and 3, the exhaust cooling system 11 shown in FIG. 9 allows a single blower 298 to cool the spacer 290, and simultaneously clean the bearing cavity 82 and remove heat from the internal structure (e.g., bearing assembly 84).

The solid inner body 294 of the strut 230 shown in Fig. 3 can provide structural support to bear slightly greater loads than the hollow inner body 50 of the strut 40 shown in Figs. 2 and 3, while the outer body 292 of the strut 290 is not a load bearing structural support. In certain example embodiments, the inner body 294 may have a temperature limit lower than the temperature of the hot exhaust gas, while the outer body 292 may have a temperature limit well above the temperature of the hot exhaust gas. In this way, the outer body 292 thermally protects the inner body 294 so that the inner body 294 is able to efficiently transmit mechanical loads between the inner and outer structures 38 and 42 of the exhaust section 24. Additionally, as described in more detail below, in some embodiments, the exhaust section cooling system 11 may include tunable areas 306, 308, 310 for controlling the flow of cooling air through the bearing zone (e.g., bearing cavity 82), inner cavity 91, strut flow passage 296. 290 etc.

Figure 10 is a cross-sectional side view of the embodiment of the gasoline turbine engine 12 of Fig. 9 taken within line 10-10, illustrating the cooling of the exhaust section by the cooling system 11 of the exhaust section of Fig. 9. As described above, blower 298 blows cooling air 302 through manhole 204 or other component connected to internal structure 38 downstream from strut 290 and bearing assembly 84. As illustrated by arrow 312, some cooling air 302 then flows in an axial direction 98 upstream between the first baffle (e.g., sleeve) 88 and a lubricant passage 86 that is connected to bearing assembly 84 to supply lubricating oil to bearing assembly 84. Then, as shown by arrows 314 and 316, some cooling air flows into and through the bearing cavity 82 where it cools the bearing assembly 84. As described above, bearing assembly 84 generates significant amounts of heat while its bearing rotates as shaft 26 rotates. Accordingly, the flow of cooling air convection cools the bearing assembly 84 to reduce premature wear or damage caused by heat.

Upon contacting the bearing assembly 84, some cooling air enters recess 94 of the turbine rear rotor as shown by arrow 318. This cooling air then travels towards the inner exhaust wall 80, where some cooling air exits through slot 104 into the exhaust duct. 56. Cooling air that does not escape through slit 104 flows back towards flow channel 296 of strut 290 in axial direction 96 with the current as shown by arrow 320. Upon reaching strut 290, some cooling air then moves through flow channel 296 between outer PL 220 729 B1 to the solid body 292 and the solid inner body 294 and to the outer structure 42, as illustrated by arrows 322. As described above, when cooling air exits into strut 290, it enters outer cavity 110 to control the temperature of outer structure 42 before draining into exhaust flow conduit 56. For example, some cooling air flows into exhaust flow channel 56 through openings 112 in outer exhaust wall 106. In some embodiments, the inner exhaust wall 80 may also include openings 112 for draining air flow into the exhaust flow channel 56.

As described above, the cooling system 11 of the exhaust section illustrated in Fig. 10 also includes three tunable regions 306, 308, 310 for controlling the flow of cooling air within the inner structure 38 and through the flow channel 296 of the struts and 290. More specifically, tunable regions 306, 308 , 310 are used to control the distribution (e.g., percentage) of cooling air to flow to the various zones of the internal structure 38. Although they are shown as three tuneable regions 306, 308, 310, any number of tunable regions may be used in other embodiments, such as 1, 2, 3, 4, 5, 6, 7, 8, 3, 10 or more. to divide the cooling air flow to any desired percentage of the cooling air. In addition, the percentage division between each tunable area may vary and may be independently and actively controlled by, for example, adjusting the tunable areas by a control device (e.g., controller 300). In addition, tunable regions 306, 308, 310 may also passively control the flow of cooling air as tunable regions 306, 308, 310 may include variously sized and shaped openings that may be selected when designing the cooling system 11 of the exhaust section.

As illustrated, the first and second tuneable regions 306 and 308 may be used to tune the amount of cooling air that can flow from bearing cavity 82 through inner cavity 91 and into flow channel 296 of strut 290. More specifically, the first tunable region 306 may be configured to allow an amount of air to flow from within the bearing cavity 82 through the interior cavity 91 and into the flow channel 296 through the wall 92 supporting the bearing at a location downstream of spacer 290. Similarly, the second tunable region 308 may be configured to allow an amount of cooling air to flow from inside bearing cavity 82 through interior cavity 91 and into flow channel 296 through wall 92 supporting the bearing at a location downstream of spacer 290. In addition, the third tunable region 310 may be configured to allow an amount of cooling air to exit the bearing cavity 82 in an axial direction 96 downstream through the second baffle (e.g., target) 90 and into the exhaust cavity 95. In certain example embodiments cooling air that is allowed to flow into the exhaust cavity 95 can be actively controlled. In other words, the control device (e.g. control device 300) can actively control the third tunable area 310 to regulate the amount of cooling air that flows from bearing cavity 82 to exhaust cavity 95 during operation of the gas turbine engine 12. In some embodiments, cooling air flowing into exhaust cavity 95 may be directed outward. from the exhaust recess 95 at a position rearward in the direction of flow, such as through an exhaust flow passage inside manhole 304 (e.g. separated from the inlet flow channel through which the cooling air 302 is received). Additionally, although they are shown blocked or separated from the spacer 290, in some embodiments cooling air of exhaust cavity 95 may be allowed to flow into spacer 290 as the wall 311 illustrated between exhaust cavity 95 and spacer 290 may either be removed or have the through holes (or, in fact, separate tunable areas) within them.

All tunable regions 306, 308, and 310 may be adjusted using inserts similar to the inserts (e.g., the inserts 202, 204, and 206) described above with reference to Fig. 8. In other words, in certain example embodiments, the tuneable regions 306, 308, and 310 may include holes similar to the holes 112 described above with reference to Figs. 7 and 8. As described above, by controlling the cooling air distribution through the tunable regions 306, 308, and 310, the temperature distribution within and throughout the internal structure 38 and in the flow channel 296 of the strut 290 can be controlled. More specifically, e.g. and the second tunable regions 306 and 308 make it easy to tune the amount of cooling air distributed in front of looking towards

And downstream of strut 290. As such, more or less cooling air may be directed toward the leading edge or trailing edge of strut 290 as desired. As described above, in certain example embodiments, the distribution of cooling air through the first and second tunable regions 306 and 308 may be actively controlled. In other words, the control device (e.g. control device 300) can actively control the first and second tunable regions 306 and 308 to regulate the distribution of cooling air that flows from bearing cavity 82 through inner cavity 91 and into flow channel 296 during operation of gasoline engine 12.

Figure 11 is a cross-sectional view of the embodiment of the strut 290 of Fig. 10 taken along line 11-11. As described above, the strut 290 shown in Figure 11 includes an outer body 292 disposed around a solid inner body 294. As shown, a passageway 296 is defined by the area between the outer body 292 and the solid inner body 294. Additionally, the outer body 292 defines a leading edge. 324 and trailing edge 326. In the present embodiment, the outer body 292 has an oval shape (e.g., the shape of a carrier panel), while the inner body 294 has a rectangular shape. In other embodiments, the inner and outer bodies 294 and 292 may have other shapes such as a rectangle in a rectangle, a flap in a support sheet, an oval in an oval, etc. In fact, both the inner and outer bodies 294 and 292 can form any number of shapes, such as oval, flap, teardrop, rectangular, square, circular, or generally elongated. Regardless of the particular shapes, the inner and outer bodies 294 and 292 are disposed inside each other so that the flow passage 296 is the volume between the inner and outer bodies 294 and 292.

Figure 12 is a cross sectional view of the embodiment of the strut 290 of Fig. 10 taken along line 11-11. As shown in Fig. 12, flow channel 296 is further divided by walls 328 to form flow channels 330 and 332. In other embodiments, flow channel 296 may be further subdivided by walls 328 to define any number of flow channels (e.g. 1, 2, 3, 4, 5, 6, 7, 8, 9, 10 or more flow channels). In the embodiment illustrated in Fig. 12, the first flow channel 330 may at least partially include cooling air that flows through the first tunable area 306, while the second flow channel 332 may at least partially include cooling air that flows through the second tunable area 308. As such, since these flows can be actively and / or passively controlled as described above, more cooling can be provided at the hot spots of strut 290 (e.g., higher rates of cooling air flow along the leading edge of strut 290).

As described above, the controls 46, 300 illustrated in Figures 2, 3, 9 and 10 may be configured to actively control the operation of the blowers 44 and 238, the tunable regions 306, 308 and 310, and other components of the cooling system 11 of the exhaust section. The controller devices 46, 300 may each include a processor that can read from and write to a memory, such as computer-readable fixed assets (e.g. a hard disk, USB flash drive, random access memory (RAM), compact disks (CD), etc.) having encoded computer commands that are configured to perform an active control operation described herein. More specifically, controls 46, 300 may be configured to receive signals relating to the operating parameters of the exhaust section cooling system 11 (e.g. temperature signals at and around struts 40, 290, flow channels 52, 53, 296, bearing assembly 84, inner cavity 91, exhaust cavity 95, etc.) and for generating and transmitting control signals for blowers 44 and 298, tunable regions 306. 308 and 310 and other components of the cooling system 11 of the exhaust section.

This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems, and carrying out any methods contained herein. The patentable scope of the invention is defined by the claims and may include other examples that will occur to those skilled in the art. Such other examples are intended to fall within the scope of the claims if they have constructional features that do not differ from the literal claim language, or if they contain equivalent constructional features with slight differences from the literal claim language.