Untitled record

Full description and background of the invention

Development of this invention is supported in part by the US Department of Energy, Advanced Turbine Development Program, Contract No. DE-FC26-05NT42644. Therefore, the United States Government may have certain rights in this invention.

<p dir="rtl">5 The present invention relates generally to turbine blades, and more particularly to airfoil tips of turbine blades.</p>

Typically, gas turbine engines include a compressor to compress air, a combustor to mix compressed air with fuel and ignite the mixture, and a turbine blade assembly to produce 10 power. Combustors often operate at high temperatures, which can exceed 2,600 degrees Fahrenheit. Typical turbine combustor designs exhibit turbine blade assemblies for these high temperatures. As a result, turbine blades must be made of materials capable of withstanding these high temperatures.

<p dir="rtl">15 Typically, terpene blades are formed from a root portion at one end and an elongated portion that forms a feather extending out from the platform coupled to the root portion at one end opposite the turbine blade. The feather usually consists of a tip corresponding to the root segment</p>

section, leading edge, and trailing edge. Often for ars

The turbine vane has an ars tip feature to reduce the size of the gap between ring segments

<p dir="rtl">20 segments and vanes in the turbine's gas path to prevent flow leakage</p>

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Leakage from the turbine blades, which reduces the amount of torque generated by the turbine blades. Tip features are often referred to as squealer tips and are frequently used on vane tips to help reduce performance loss between turbine stages. These features are designed to reduce leakage between the blade tip and ring segment.

General description of the invention

A firing arm is disclosed consisting of a pressure unit wall side tip extending diagonally and a suction side tip wall extending diagonally outward from the turbine blade wall formed by a pressure tip side extending axially. The side wall of the compression unit and the suction unit can be located extending diagonally along the side wall of the pressure unit

10 pressure sidewall and suction sidewall of the turbine blade, respectively. The side wall of the pressure unit extending diagonally may include a flange

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Chamfered leading edge with one or more film cooling holes with exhaust outlets placed therein. An axially extending bed wall may be formed by at least two external horizontal surfaces joined together at an intersection to form a concave axially extending bed wall. The axially extending wall of the ars can include a convex inner surface

To the cavity radially outer end forms a convex inner surface

An internal cavity forms a cooling system. The cooling system may include one or more thin layer cooling holes in the wall of the axis extending axially close to the side wall of the unit.

Absorption, which promotes increased cooling at the side walls of the compression unit and the absorption unit.

20 A turbine blade can be formed from an elongated airfoil, generally having a leading edge, a trailing edge, and a root at one end, and a root associated with the feather at generally the opposite end.

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For the first party to support the plectrum and compare the plectrum to a disc. The turbine blade may also be composed of a pressure unit sidewall extending from the leading edge to the trailing edge and an absorber sidewall extending from the leading edge to the trailing edge and positioned on a side opposite the generally elongated airfoil from the pressure unit sidewall. One or more cavities may be included

5 cavities that form the internal cooling system in the turbine blade.

Launching grounds can be placed at the first end. The firing ground may be formed from an axially extended pressure unit side wall with an outer surface that is flush with an outer surface of the pressure unit side wall, an absorption unit side wall extending diagonally with an outer surface that is flush with an outer surface of the absorption unit side wall, an axially extended anchor wall extending between Aras wall

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The side wall of the pressure unit and the side wall of the absorption unit. An axially extended bed wall can be formed from two or more external horizontal surfaces joined together at an intersection to form a concave axially extended bed wall. The intersection at which the two outer horizontal surfaces forming the bed wall extending axially and diagonally inward are connected by the intersection of an inner surface of the side wall of a pressure unit extending diagonally and a first outer surface of the bed wall extending axially and diagonally inward from the intersection of an inner surface of the side wall of a pressure unit extending diagonally and extending diagonally and a second outer surface of the axially extending wall of the ars.

The side wall of the axially extended pressure unit may include a chamfered surface

Surface is placed at an acute angle with respect to the outer surface of the elongated airfoil

General problem of the side wall of the pressure unit. It can only extend the beveled surface of a wall

20 The side wall of a pressure unit extending diagonally for a portion of the total length of the side wall of the unit

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Diagonally extended pressure. The side wall of the compression unit can extend diagonally from the front edge and can terminate at the trailing edge. The turbine blade may also include one or more thin film cooling holes disposed in the side wall of the radially extended pressure unit with an outlet on an outer surface in the side wall of the radially extended pressure unit and an inlet.

5 The film cooling hole forms the cavity of the internal cooling system. The thin film cooling hole outlet can be located in the beveled surface of the side wall of the diagonally extending pressure unit.

The side wall of the absorber unit can extend diagonally from the back edge toward the edge

The leading edge of an elongated airfoil, in general, ends at the leading edge and may be coupled to the landing wall.

10 The side of the pressure unit extending diagonally. One or more thin film cooling holes may be located in an outer horizontal surface of the axially extended bed wall contacting the radially extended bed side wall of the absorber. The thin film cooling hole may include an outlet in the axially extended arc wall and an inlet through which the thin layer cooling hole connects to the cavity forming the internal cooling system. The inner surface of the arse wall can have an axially extended form that forms an outer boundary

15 Boundary Diagonally, the cavity formed for the internal cooling system is a convex surface with external points diagonally specific to the convex surface at intersections with the side walls of the pressure unit and the unit.

Absorption. The cavity formed for the intercooling system may include a diagonally extending midregion rib that divides the intercooling system into compression unit and absorption unit sides.

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The advantage of this invention is that the convex inner surface of the axially extended bed wall improves cooling when the bed rotates close to the side walls of the compression unit and the absorption unit, which are exposed to the path of high-temperature hot gas.

Another advantage of this invention is that the concave outer surface 5 forming the firing pins forms a deep outer pinning cavity that functions to restore constant pressure and reduce the pinion leakage flow.

These and other models are described in detail below.

Brief explanation of the drawings

The accompanying drawings, which are used and form part of this specification, illustrate embodiments of the invention 10 presently described and, together with the description, disclose the principles of the invention.

Figure 1 is a perspective view of a turbine blade at all angles.

Figure 2 is a partial perspective detail of the firing pins at the leading edge of the turbine blade shown in Figure 1.

Figure 3 is an overhead view of the launching pads shown in Figure 1.

15 Figure 4 is a cross-sectional view of a turbine blade taken at sector line 4-4 in Figure 1.

Figure 5 is a schematic diagram of the cooling system shown in Figure 4.

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Figure 6 is a partial cross-sectional view of the launch grounds taken at sector line 6-6 in Figure 4.

Figure 7 is a partial cross-section view of another model of the launch grounds taken at sector line 7-7 in Figure 4.

5 Figure 8 is a partial cross-section view of another model of the launch grounds taken at sector line 8-8 in Figure 4.

Figure 9 is a partial cross-sectional view of another model of the launch grounds taken at sector line 9-9 in Figure 4.

Detailed description:

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As shown in Figures 1-9, a firing arm 10 is disclosed consisting of a diagonally extending compression unit side wall 12 and a diagonally extending absorption unit side wall 14 extending diagonally outward from the setting 16 of a turbine blade 18 consisting of an axially extending firing unit side wall 30 The side walls of the pressure unit and the suction unit can be located diagonally extended 12, 14 along.

A sidewall of a compression unit 20 and a sidewall of an absorption unit 22 of a turbine blade 18, respectively. The side wall of the diagonally extending pressure unit can include 12 leading edges

Beveled 24 with one or more thin layer cooling holes 26 having exhaust 28 outlets disposed therein. The axially extended bed wall 30 may be formed from at least two external horizontal surfaces 32, 34 joined together at the intersection 36 to form a concave axially extended bed wall. The axially extending wall of the ars 30 may include a convex inner surface 33 forming an outer extremity

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diagonally into an internal cavity 38 forming a cooling system 40. The cooling system 38 may include one or more thin layer cooling holes 42 in the axially extending bed wall 30 near the side wall of the absorption unit 22, promoting increased cooling at the side walls of the absorption units Compression and absorption 20, 22.

5 As shown in Figure 1, the turbine vane 18 may be formed from a generally elongated airfoil 44 having a leading edge 46 and a trailing edge 48. The generally elongated airfoil 44 may include an ars 16 at a first end 50 and a root 52 coupled to a vane 44 at a second end. 4 in general, compared to the first party 0 to support the vane 44 and compare the vane 44 to a disc. The internal cooling system 40, as shown in Figures 4-9, may be formed from at least one cavity 38 disposed in the airfoil

10 Generally elongated 44. The cooling system 40 may be designed as shown in Fig. or may have any design suitable for cooling the turbine blade 18 during use in a gas turbine engine in operation. The 18th grade vane and its related components described above may be formed from any suitable material already known in the art or to be discovered or identified.

As shown in Figure 1, the turbine blade 18 may also include a sidewall of a compression unit 15 20 extending from the leading edge 46 to the trailing edge 48 and a sidewall of an absorption unit

22 It extends from the leading edge 46 to the trailing edge 48 and is positioned on a side opposite the generally elongated airfoil 44 from the side wall of the pressure unit 20 and the cavity 38 formed for the internal cooling system 40.

The firing pin 10 may be positioned at the first end 50 and may be formed from a firing pin wall

20 Lateral to a diagonally extended pressure unit 12 with an outer surface 56 that is flush with the outer surface 58

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For the side wall of the compression unit 20. The side wall of the pressure unit extending diagonally 12 and the side wall of the absorption unit extending diagonally 14 may be of any suitable height and width.

In at least one embodiment, as shown in Figures 6-9, the pressure unit side wall extending diagonally 12 or the absorption unit side wall extending diagonally 12 can have

14, or both, a height-to-width ratio between about 2:1 and 1:2, and in at least one embodiment, can be about 1:1. The launch bed 10 can also include a side wall of an absorber extending diagonally 14 with an outer surface 60 which is flush with the outer surface 62 of the side wall of the absorption unit 22. The axially extended bed wall 30 can extend between the bed wall

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The side wall of the pressure unit 12 and the side wall of the suction unit 14. The axially extending bed wall 30 may be formed from at least two external horizontal surfaces 32, 34 joined together

At the intersection 36 which forms the axially extended bracket wall 30. The intersection 36 can be located at which the two outer horizontal surfaces 32, 34 forming the axially extended bracket wall 30 are connected diagonally inward from the intersection 64 of the inner surface 66 of the diagonally extended pressure unit side wall. 12 and the first outer surface 68 of the arcade wall extending axially 30 and diagonally inward from the intersection 70

15 The inner surface 72 of the side wall of the absorption unit extending diagonally 14 and the second outer surface 74 of the side wall of the bed extending axially 30.

As shown in Figures 1-3, 8, and 9, the diagonally extended airfoil sidewall 12 may include a beveled surface 76 positioned at acute angles with respect to the outer surface 58 of the generally elongated airfoil 44 that forms the sidewall of the pressure unit 20. extends

20 The beveled surface 76 of the side wall of the pressure unit extending diagonally 12 for part of the length

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The total length of the side wall of the pressure unit extending diagonally 12. In another embodiment, the chamfered surface 76 of the side wall of the pressure unit extending diagonally 12 can extend to the total length of the side wall of the pressure unit extending diagonally 12. The side wall of the pressure unit extending diagonally 12 can extend The side wall of the compression unit extends diagonally 12 from the front edge 46 and can terminate at the trailing edge 48. The side wall of the absorption unit extends diagonally 14 from

The trailing edge 48 is towards the leading edge 46 of the generally elongated airfoil 44, terminating at the leading edge 46 and may be coupled to the sidewall of the diagonally extended pressure unit 12.

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As shown in Figures 1-3, 8, and 9, one or more thin layer cooling holes 26 may be located in the side wall of the extended compression unit diagonally 12 with an outlet 28 at the outer surface 56 in the side wall of the extended pressure unit Diagonally 12 and entrance 82 which

The thin layer cooling hole 26 is coupled to the cavity 38 forming the internal cooling system 40.

The outlet 28 of the thin film cooling hole 26 may be located in the beveled surface 76 of the side wall of the diagonally extended compression unit 12. The thin film cooling holes 26 disposed in the side wall of the diagonally extended pressure unit 12 can extend at acute angles relative to the outer surface. 56 The side wall of the pressure unit extending diagonally 12. In addition, the thin layer cooling hole 26 can extend to the side wall of the diagonally extended pressure unit 12 at sharp angles relative to the beveled surface 76 of the side wall of the diagonally extended pressure unit 12. In another embodiment, the thin layer cooling hole can extend 26 to the diagonally extended pressure unit side wall 12 generally perpendicular to the beveled surface 76 of the diagonally extended pressure unit side wall 12.

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The launch bed 10 may also include one or more thin film cooling holes 42 disposed in the outer horizontal surface 34 of the axially extended launch bed wall 30 in contact with the diagonally extended bed side wall of the absorber 14. The launch bed cooling hole 42 can include an outlet 86 In the axially extended arc wall 30 and inlet 88 couple a thin layer cooling hole 42

5 With the cavity 38 formed for the internal cooling system 40.

The inner surface 33 of the axially extended bracket wall 30 that forms a diagonal outer limit of the cavity 38 formed for the internal cooling system 40 has a convex surface with diagonally external points 90, 92 of the convex surface 33 at the intersection 94, 96 with the side walls of the compression unit and the absorption unit 20, 22. The cavity 38 forming the internal cooling system 40 may include a diagonally extending intermediate zone rib 98,

10 As shown in Figures 6, 7 and 9, with the intercooling system 40 divided into compression unit and absorption unit sides 100, 102.

During use, cooling fluids are passed through the internal cooling system 40. Cooling fluids can flow through the cooling system 40 and increase the temperature as the cooling fluids reduce the temperature of the materials forming the turbine blade 18. Cooling fluids can flow in External points

15 Diagonally 90, 92 of the convex surface 33 at the intersections 94, 96 with the side walls of the compression and suction units 20, 22 where at least a portion of the fluid can be exhausted from the cooling system 40 through the film cooling holes 26, 42 in the RS 16 of the vane. The turbine 18. Cooling fluids may cool the beds 16 by convection and may cool the sides of the firing beds 10 by exhausting them through the film cooling holes 26 and 42. Gas intervention

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The flowing hot gases pass through the side wall of the pressure unit extending diagonally 12 to the outer gas cavity 104, which provides constant pressure recovery and reduced pressure leakage flow.

The foregoing is provided for the purposes of illustrating, explaining, and describing embodiments of this invention. Modifications and transformations of these models will be obvious to those skilled in the art and can be made without departing from the content.

<p dir="rtl">5 The scope of this invention.</p>

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