US20140096538A1 - Platform cooling of a turbine blade assembly - Google Patents
Platform cooling of a turbine blade assembly Download PDFInfo
- Publication number
- US20140096538A1 US20140096538A1 US13/646,023 US201213646023A US2014096538A1 US 20140096538 A1 US20140096538 A1 US 20140096538A1 US 201213646023 A US201213646023 A US 201213646023A US 2014096538 A1 US2014096538 A1 US 2014096538A1
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- United States
- Prior art keywords
- platform
- pressure side
- cooling circuit
- turbine blade
- suction side
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
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- 238000001816 cooling Methods 0.000 title claims abstract description 89
- 239000002826 coolant Substances 0.000 claims abstract description 33
- 239000012530 fluid Substances 0.000 claims abstract description 24
- 238000004891 communication Methods 0.000 claims description 9
- 239000007789 gas Substances 0.000 description 15
- 238000000034 method Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- WYTGDNHDOZPMIW-RCBQFDQVSA-N alstonine Natural products C1=CC2=C3C=CC=CC3=NC2=C2N1C[C@H]1[C@H](C)OC=C(C(=O)OC)[C@H]1C2 WYTGDNHDOZPMIW-RCBQFDQVSA-N 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000037361 pathway Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A turbine blade generally includes a platform having a pressure side, a suction side, a leading edge, a trailing edge, a pressure side slash face and a suction side slash face. A platform cooling circuit extends within the platform. The platform cooling circuit may extend from the suction side of the platform to the pressure side of the platform. The platform cooling circuit generally defines a fluid flow path that directs a cooling medium from the platform suction side to the platform pressure side.
Description
- The present invention generally involves cooling a platform of a turbine blade. More specifically, the invention involves a platform cooling circuit that defines a fluid flow path from a suction side of the platform to a pressure side of the platform.
- Turbines are widely used in fields such as power generation. A conventional gas turbine may generally include a compressor, a combustor, and a turbine. During operation, various components within the gas turbine are subjected to high temperature flows, which can cause the components to fail. Since higher temperature flows generally result in increased performance, efficiency, and power output of the gas turbine, the components that are subjected to high temperature flows must be cooled to allow the gas turbine to operate at increased temperatures.
- Various strategies are known in the art for cooling various gas turbine components. For example, a cooling medium may be routed from the compressor and provided to various components. Other methods may include routing an alternate cooling medium such as steam through the various components within the gas turbine. In the compressor and turbine sections of the system, the cooling medium may be utilized to cool various compressor and turbine components.
- Turbine blades are one example of a hot gas path component that must be cooled. For example, various parts of the turbine blade, such as the airfoil, the platform, the shank, and the dovetail, are disposed in a hot gas path and exposed to relatively high temperatures, and thus require cooling. Various cooling passages and cooling circuits may be defined in the various parts of the turbine blade, and cooling medium may be flowed through the various cooling passages and cooling circuits to cool the turbine blade.
- In many known turbine blades, portions of the turbine blades may reach higher temperatures than other portions of the turbine blade. One specific area that is of particular concern in known turbine blades is the suction side of the platform that is generally adjacent to the suction side slash face and that extends across the trailing edge of the platform. In addition or in the alternative, the cooling medium may flow from the pressure side of the platform to an exhaust port or passage on the suction side of the platform. However, as the cooling medium flows from the pressure side, heat energy is transferred to the cooling medium, thereby reducing the cooling effect of the cooling medium as it flows through and/or across the platform. Thus, cooling of the suction side may be reduced.
- Accordingly, an improved turbine blade for a turbine system is desired in the art. Specifically, a turbine blade with improved cooling features would be advantageous.
- Aspects and advantages of the invention are set forth below in the following description, or may be obvious from the description, or may be learned through practice of the invention.
- One embodiment of the present invention is a turbine blade. The turbine blade generally includes a platform having a pressure side, a suction side, a leading edge, a trailing edge, a pressure side slash face and a suction side slash face. A platform cooling circuit extends within the platform. The platform cooling circuit may extend from the suction side of the platform to the pressure side of the platform. The platform cooling circuit generally defines a fluid flow path that directs a cooling medium from the platform suction side to the platform pressure side.
- Another embodiment of the present invention is a turbine blade having a main body that defines a primary cooling circuit within the main body. A platform at least partially surrounds the main body. The main body includes a platform having a pressure side, a suction side, a leading edge, a trailing edge, a pressure side slash face and a suction side slash face. A platform cooling circuit extends within the platform and is in fluid communication with the primary cooling circuit of the main body. The platform cooling circuit extends within the platform from the suction of the platform to the pressure side of the platform. The platform cooling circuit defines a fluid flow path that directs a cooling medium from the primary cooling circuit of the main body, across the platform trailing edge to the platform pressure side.
- The present invention may also include a gas turbine having a compressor, a combustor downstream form the compressor and a turbine downstream from the combustor, the turbine having at least one turbine blade. A platform at least partially surrounds the turbine blade, the platform having a leading edge, a trailing edge, a pressure side slash face, a suction side slash face, and a top surface, the top surface having a pressure side and a suction side. The platform defines one or more outlet ports that extend through at least one of the pressure side slash face, the suction side slash face or the top surface of the platform. A platform cooling circuit extends within the platform and is in fluid communication with the at least one outlet port. The platform cooling circuit extends beneath the top surface of the platform from a point generally adjacent to the suction side slash face, along the trailing edge and to the pressure side of the platform. The platform cooling circuit defines a fluid flow path that directs a cooling medium from the platform suction side to the platform pressure side and exhaust the cooling medium through the at least one outlet port.
- Those of ordinary skill in the art will better appreciate the features and aspects of such embodiments, and others, upon review of the specification.
- A full and enabling disclosure of the present invention, including the best mode thereof to one skilled in the art, is set forth more particularly in the remainder of the specification, including reference to the accompanying figures, in which:
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FIG. 1 is a schematic illustration of a gas turbine system according to one embodiment of the present disclosure; -
FIG. 2 is a perspective view of a turbine blade according to one embodiment of the present disclosure; -
FIG. 3 is a side view illustrating the internal components of a turbine blade according to one embodiment of the present disclosure; -
FIG. 4 is a top view of a turbine blade according to at least one embodiment of the present disclosure; -
FIG. 5 is a side view of a turbine blade according to at least one embodiment of the present disclosure; -
FIG. 6 is a top view of a turbine blade according to at least one embodiment of the present disclosure; and -
FIG. 7 is a top view of a turbine blade according to at least one embodiment of the present disclosure. - Reference will now be made in detail to present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the invention. As used herein, the terms “first”, “second”, and “third” may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components. In addition, the terms “upstream” and “downstream” refer to the relative location of components in a fluid pathway. For example, component A is upstream from component B if a fluid flows from component A to component B. Conversely, component B is downstream from component A if component B receives a fluid flow from component A.
- Each example is provided by way of explanation of the invention, not limitation of the invention. In fact, it will be apparent to those skilled in the art that modifications and variations can be made in the present invention without departing from the scope or spirit thereof. For instance, features illustrated or described as part of one embodiment may be used on another embodiment to yield a still further embodiment. Thus, it is intended that the present invention covers such modifications and variations as come within the scope of the appended claims and their equivalents.
- Various embodiments of the present invention include a platform cooling circuit that extends beneath a top surface of a turbine blade platform. The platform cooling circuit generally extends from a suction side of the platform to a pressure side of the platform. The platform cooling circuit at least partially defines a fluid flow path for a cooling medium to flow through the platform cooling circuit. One or more outlet ports may provide fluid communication from the platform cooling circuit into a hot gas path of the turbine. In the alternative, at least one outlet port may direct the cooling medium through a slash face of the turbine blade. The suction side of the platform near a trailing edge of the platform is an area of high temperatures that may potentially limit the mechanical life of the turbine blades. Current methods to cool the turbine blade flow the cooling medium along the pressure side only or direct the cooling medium from the pressure side to the suction side. However, it has been shown that the cooling medium is less effective at cooling the suction side once it flows through the high temperature portions of the pressure side of the platform. Therefore, by flowing the cooling medium along the suction side and along the trailing edge of the platform before flowing it to the pressure side of the platform may improve the cooling effectiveness of the cooling medium across the suction side while having a minimal impact on the cooling effectiveness of the cooling medium across the pressure side of the platform.
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FIG. 1 is a schematic diagram of agas turbine 10. Thegas turbine 10 may generally include acompressor 12, acombustor 14, and aturbine 16. Thecompressor 12 andturbine 16 may be coupled by ashaft 18. Theshaft 18 may be a single shaft or may include a plurality of shaft segments coupled together to form theshaft 18. - The
turbine 16 may include at least one stage of airfoils (not shown). Each stage of the at least one stage of airfoils may generally include a row of stationary blades and a row of rotating turbine blades adjacent to and downstream from the row of stationary blades. The stator blades may be disposed and fixed circumferentially about theshaft 18. The turbine blades may be spaced circumferentially around a rotor disk that is connected to theshaft 18. The rotor disk may include one or more cooling passages that provide fluid communication to the turbine blades. The various stages of theturbine 16 may at least partially define a hot gas path (not shown) that directs hot gases from thecombustor 14 through theturbine 16. It should be understood that theturbine 16 is not limited to three stages. For example, theturbine 16 may have two, three, four or more stages. Similarly, thecompressor 12 may include a plurality of compressor stages (not shown). Each stage of thecompressor 12 may include a plurality of circumferentially spaced compressor stator blades and a plurality of rotating compressor blades. -
FIG. 2 illustrates a perspective view of a turbine blade, andFIG. 3 provides a side view illustrating the internal components of a turbine blade. As shown in FIG. 2, theturbine blade 30 may include amain body 32 and aplatform 34. Themain body 32 typically includes anairfoil 36 and ashank 38. Theairfoil 36 may be positioned radially outward from theplatform 34 and/or theshank 38. Theshank 38 may include aroot 40, which may be configured to attach with the rotor disk (not shown) which is attached and/or surrounds theshaft 18. Theairfoil 36 generally includes apressure side 42 andsuction side 44, a leadingedge 46 and a trailingedge 48. In addition, theairfoil 36 generally includes aroot 50 and atip 52. Theairfoil 36root 50 generally intersects with theplatform 34. Thetip 52 is generally distal from theroot 50 in a radial direction. - As shown in
FIG. 2 , theplatform 34 may at least partially surround themain body 32. Atypical platform 34 may be positioned at an intersection or transition between theairfoil 36root 50 and theshank 38 of themain body 32. Theplatform 34 may extend generally axially and tangentially outward from themain body 32. It should be understood, however, that a platform according to the present disclosure may have any suitable position relative to themain body 32 and/or theairfoil 36 of theturbine blade 30. Theplatform 34 may further include aleading edge 60, a trailingedge 62, a pressureside slash face 64 and a suctionside slash face 66. Atop surface 68 of theplatform 34 may extend at least partially between theleading edge 60, trailingedge 62, pressureside slash face 64 and suctionside slash face 66 of theplatform 34. - The
platform 34 may be generally divided into apressure side 70 and asuction side 72. In particular embodiments, theplatform 34top surface 68 may at least partially define theplatform 34pressure side 70 and thesuction side 72. Theairfoil 36 may at least partially separate theplatform 34pressure side 70 from theplatform 34suction side 72. For example, thepressure side 70 of theplatform 34 may be at least partially defined between thepressure side 42 of theairfoil 36 and at least a portion of the pressureside slash face 64 of theplatform 34. Thesuction side 72 of theplatform 34 may be at least partially defined between thesuction side 44 of theairfoil 36, at least a portion of the leadingedge 60 of the platform, at least a portion of the trailingedge 62 of theplatform 34 and the suctionside slash face 66 of theplatform 34. - As shown in
FIG. 3 , one or more internalmain cooling circuits 80 may extend through themain body 32 shown inFIG. 3 . Themain cooling circuits 80 may extend through various portions of themain body 32 to provide one or more fluid flow paths to flow a cooling medium such as compressed air or steam to cool themain body 32 and/or theairfoil 36 during operation. For example, in some embodiments as shown inFIG. 3 , themain body 32 may define a forward main coolingcircuit 82 and an aftmain cooling circuit 84. Themain cooling circuits 80 may have any suitable shape and may extend along any suitable path within themain body 32 and/or theairfoil 36. For example, eachmain cooling circuit 80 may have various branches and serpentine portions and, as shown inFIG. 3 , may extend through the various portions of themain body 32, such as through theairfoil 36 andshank 38. The cooling medium may enter themain cooling circuits 80 through theroot 40 portion of theshank 38. -
FIG. 4 provides a top view of the turbine blade,FIG. 5 provides a side view of the turbine blade, andFIGS. 6 and 7 provide top views of the turbine blade according to various embodiments of the present disclosure. As shown inFIGS. 4 through 7 , one or moreplatform cooling circuits 90 may be defined in theplatform 34 and/or themain body 32 of theturbine blade 30. As shown inFIGS. 5 , 6 and 7 theplatform cooling circuit 90 may be defined at least partially within theplatform 34. For example, in exemplary embodiments, a portion of theplatform cooling circuit 90 is defined in theplatform 34, and extends through theplatform 34 to cool it. As shown, theplatform cooling circuit 90 generally extends beneath thetop surface 68 of theplatform 34. Other portions of theplatform cooling circuit 90 may extend into themain body 32 and/or into theairfoil 36. - In at least one embodiment, as shown in
FIG. 4 , theplatform cooling circuit 90 may include aninlet 92, asuction side portion 94 and apressure side portion 96. Theinlet 92 may be fluidly connected to at least one of themain cooling circuits 80 that extend through themain body 32 and/or through theairfoil 36. For example, theinlet 92 may be fluidly connected to either or both of the forward or the aft main cooling circuits, 82 and 84 respectfully. In particular embodiments, theinlet 92 may be disposed beneath thetop surface 68 of theplatform 34 at least partially on thesuction side 66 of theplatform 34. For example, theinlet 92 may be disposed within theplatform 34 between thesuction side 44 of theairfoil 36 and the suctionside slash face 66 and the trailingedge 62 of theplatform 34. - The
suction side portion 94 of theplatform cooling circuit 90 generally extends from theinlet 92 across thesuction side 66 of theplatform 34. In particular embodiments, as shown inFIG. 4 , thesuction side 66 of theplatform cooling circuit 90 may generally extend from theinlet 92 towards and/or at least partially adjacent to at least a portion of the suctionside slash face 66. Thesuction side portion 94 may then extend from the suctionside slash face 66 across the trailingedge 62 of theplatform 34 and towards the pressureside slash face 64 of theplatform 34. Thesuction side portion 94 may extend generally parallel to the trailingedge 62 of theplatform 34. In addition or in the alternative, thesuction side portion 66 may reverse directions one or more times across thesuction side 66 of theplatform 34. Thesuction side portion 94 of theplatform cooling circuit 90 generally transitions into thepressure side portion 96 as theplatform cooling circuit 90 crosses underneath and/or around the of theairfoil 36 and extends to thepressure side 70 of theplatform 34. - The
pressure side portion 96 of theplatform cooling circuit 90 generally extends under thetop surface 68 of thepressure side 70 of theplatform 34. As shown, thepressure side portion 96 may extend generally adjacent to the pressureside slash face 64 of theplatform 34 towards the leadingedge 60 of theplatform 34. In particular embodiments, thepressure side portion 96 may reverse directions at least once along thepressure side 70 of theplatform 34. For example, as shown, thepressure side portion 96 may have a generally serpentine pattern across thepressure side 70 of theplatform 34. - As shown in
FIGS. 5 through 7 at least oneoutlet port 98 may extend through at least one of the pressureside slash face 64 or the suctionside slash face 66. In addition or in the alternative, as shown inFIG. 7 , the at least oneoutlet port 98 may extend through thetop surface 68 of theplatform 34 on thepressure side 70 and/or thesuction side 72 of theplatform 34. For example, as shown inFIGS. 5 and 7 , the at least oneoutlet port 98 may be positioned between theleading edge 46 of theairfoil 36 and the leadingedge 60 of theplatform 34. In addition or in the alternative, the at least oneoutlet port 98 may extend through thetop surface 68 of theplatform 34 on at least one of thepressure side 70 or thesuction side 72 of theplatform 34. As shown inFIGS. 5 through 7 , the at least oneoutlet port 98 may be fluidly connected to thepressure side portion 96 of theplatform cooling circuit 90. - As shown in
FIGS. 5 through 7 , theplatform cooling circuit 90 and the at least oneoutlet port 98 may at least partially define afluid flow path 100 for flowing a cooling medium from thesuction side 72 of theplatform 34 to thepressure side 70 of theplatform 34, thereby removing heat energy from thesuction side 72 of theplatform 34 prior to flowing the cooling medium into thepressure portion 96 of theplatform cooling circuit 90. As a result, thesuction side 72 of theplatform 34 may be more effectively cooled, thereby improving overall mechanical performance of theturbine blade 30. In particular embodiments, the cooling medium may flow from theplatform cooling circuit 90 through the at least oneoutlet port 98 positioned along the pressureside slash face 64 and/or the suctionside slash face 66. In this manner, the cooling medium may be used to further cool theshank 38 portion and/or the pressures side and the suction side slash faces 64, 66 of themain body 32 of theturbine blade 30. In addition or in the alternative, as shown inFIG. 7 , the cooling medium may flow from theplatform cooling circuit 90 through the at least oneoutlet 98 disposed on thetop surface 68 of theplatform 34, thereby proving film cooling to thetop surface 68 of theplatform 34. - In further embodiments, as shown in
FIG. 6 at least oneexhaust passage 102 may extend within theplatform 34 and/or themain body 32 generally between theleading edge 46 of theairfoil 36 and the leadingedge 60 of theplatform 34. Theexhaust passage 102 may extend at least partially between the pressureside slash face 64 and the suctionside slash face 66. In particular embodiments, theexhaust passage 102 extends from the pressureside slash face 64 to the suctionside slash face 66. Theexhaust passage 102 may be at least partially defined by theplatform cooling circuit 90. In the alternative, theexhaust passage 102 may be milled, cast or otherwise formed in theplatform 34 separately from theplatform cooling circuit 90. Theexhaust passage 102 may be fluidly connected to theplatform cooling circuit 90 and to at least one of the at least oneoutlet ports 98. Theexhaust passage 102 may further define thefluid flow path 100. As a result, the cooling medium may provide further cooling to an area generally adjacent to the leadingedge 60 of theplatform 34 before it is exhausted through the at least oneoutlet port 98. - 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 performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other and examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.
Claims (20)
1. A turbine blade, comprising:
a. a platform having a pressure side, a suction side, a leading edge, a trailing edge, a pressure side slash face and a suction side slash face;
b. a platform cooling circuit within the platform, wherein the platform cooling circuit extends from the suction side to the pressure side of the platform; and
c. wherein the platform cooling circuit defines a fluid flow path that directs a cooling medium from the platform suction side to the platform pressure side.
2. The turbine blade as in claim 1 , wherein the platform cooling circuit reverses direction at least once along the pressure side of the platform.
3. The turbine blade as in claim 1 , wherein the platform cooling circuit reverses direction at least once along the suction side of the platform.
4. The turbine blade as in claim 1 , further comprising at least one outlet port in fluid communication with the platform cooling circuit.
5. The turbine blade as in claim 4 , wherein the at least one outlet port provides fluid communication through at least one of the pressure side slash face or the suction side slash face.
6. The turbine blade as in claim 4 , wherein the platform further includes a top surface that extends between the platform leading edge, the pressure side slash face and the suction side slash face, the at least one outlet port extending through the top surface of the platform.
7. The turbine blade as in claim 1 , further comprising an exhaust passage that extends within the platform generally parallel to the leading edge, the exhaust passage fluidly connected to the pressure side portion of the platform cooling circuit.
8. The turbine blade as in claim 1 , further comprising an airfoil that extends from the platform, the airfoil at least partially separating the platform pressure side from the platform suction side.
9. The turbine blade as in claim 8 , wherein the platform cooling circuit passes under the airfoil from the suction side to the pressure side of the platform.
10. A turbine blade, comprising:
a. a main body defining a primary cooling circuit within the main body;
b. a platform that at least partially surrounds the main body, the platform having a pressure side, a suction side, a leading edge, a trailing edge, a pressure side slash face and a suction side slash face;
c. a platform cooling circuit within the platform, the platform cooling circuit in fluid communication with the primary cooling circuit of the main body; and
d. wherein the platform cooling circuit extends within the platform from a point on the suction side of the platform, along the trailing edge and to the pressure side of the platform, the platform cooling circuit defining a fluid flow path that directs a cooling medium from the primary cooling circuit of the main body, across the platform trailing edge and to the platform pressure side.
11. The turbine blade as in claim 10 , further comprising at least one outlet port in fluid communication with the platform cooling circuit.
12. The turbine blade as in claim 11 , wherein the at least one outlet port extends through at least one of the pressure side slash face or the suction side slash face of the platform.
13. The turbine blade as in claim 11 , wherein the platform further includes a top surface that extends between the platform leading edge, the pressure side slash face and the suction side slash face, the at least one outlet port extending through the top surface of the platform.
14. The turbine blade as in claim 10 , wherein the platform cooling circuit reverses direction at least once along the pressure side of the platform.
15. The turbine blade as in claim 10 , wherein the platform cooling circuit reverses direction at least once along the trailing edge of the platform.
16. The turbine blade as in claim 10 , wherein the at least one outlet port includes a first outlet port and a second outlet port.
17. The turbine blade as in claim 16 , wherein the platform further includes a top surface that extends between the platform leading edge, the pressure side slash face and the suction side slash face, the first outlet port extends through at least one of the pressure side slash face or the suction side of the platform, and the second outlet port extends through the platform top surface.
18. The turbine blade as in claim 10 , wherein the platform cooling circuit extends across the leading edge of the platform.
19. The turbine blade as in claim 10 , further comprising an airfoil that extends from the platform, the airfoil at least partially separating the platform pressure side from the platform suction side, wherein the platform cooling circuit passes under the airfoil from the suction side to the pressure side of the platform.
20. A gas turbine, comprising:
a. a compressor, a combustor downstream form the compressor and a turbine downstream from the combustor, the turbine having at least one turbine blade;
b. a platform that at least partially surrounds the turbine blade, the platform having a leading edge, a trailing edge, a pressure side slash face, a suction side slash face, and a top surface, the top surface having a pressure side and a suction side, the platform defining one or more outlet ports that extend through at least one of the pressure side slash face, the suction side slash face or the top surface of the platform;
c. a platform cooling circuit within the platform and in fluid communication with the at least one outlet port, wherein the platform cooling circuit extends beneath the top surface of the platform from a point generally adjacent to the suction side slash face, along the trailing edge and to the pressure side of the platform; and
d. wherein the platform cooling circuit defines a fluid flow path that directs a cooling medium from the platform suction side to the platform pressure side and exhaust the cooling medium through the at least one outlet port.
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/646,023 US20140096538A1 (en) | 2012-10-05 | 2012-10-05 | Platform cooling of a turbine blade assembly |
CN201380051904.0A CN104704202A (en) | 2012-10-05 | 2013-10-04 | Turbine blades with platform cooling and corresponding gas turbine |
EP13780004.1A EP2912273A1 (en) | 2012-10-05 | 2013-10-04 | Turbine blades with platform cooling and corresponding gas turbine |
JP2015535796A JP2015531451A (en) | 2012-10-05 | 2013-10-04 | Turbine blade with platform cooling and corresponding gas turbine |
PCT/US2013/063359 WO2014055811A1 (en) | 2012-10-05 | 2013-10-04 | Turbine blades with platform cooling and corresponding gas turbine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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US13/646,023 US20140096538A1 (en) | 2012-10-05 | 2012-10-05 | Platform cooling of a turbine blade assembly |
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US20140096538A1 true US20140096538A1 (en) | 2014-04-10 |
Family
ID=49448300
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US13/646,023 Abandoned US20140096538A1 (en) | 2012-10-05 | 2012-10-05 | Platform cooling of a turbine blade assembly |
Country Status (5)
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US (1) | US20140096538A1 (en) |
EP (1) | EP2912273A1 (en) |
JP (1) | JP2015531451A (en) |
CN (1) | CN104704202A (en) |
WO (1) | WO2014055811A1 (en) |
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US9926788B2 (en) | 2015-12-21 | 2018-03-27 | General Electric Company | Cooling circuit for a multi-wall blade |
US9932838B2 (en) | 2015-12-21 | 2018-04-03 | General Electric Company | Cooling circuit for a multi-wall blade |
US9976425B2 (en) | 2015-12-21 | 2018-05-22 | General Electric Company | Cooling circuit for a multi-wall blade |
US10053989B2 (en) | 2015-12-21 | 2018-08-21 | General Electric Company | Cooling circuit for a multi-wall blade |
US10060269B2 (en) | 2015-12-21 | 2018-08-28 | General Electric Company | Cooling circuits for a multi-wall blade |
US10119405B2 (en) | 2015-12-21 | 2018-11-06 | General Electric Company | Cooling circuit for a multi-wall blade |
US10208608B2 (en) | 2016-08-18 | 2019-02-19 | General Electric Company | Cooling circuit for a multi-wall blade |
US10208607B2 (en) | 2016-08-18 | 2019-02-19 | General Electric Company | Cooling circuit for a multi-wall blade |
US10221696B2 (en) | 2016-08-18 | 2019-03-05 | General Electric Company | Cooling circuit for a multi-wall blade |
US10227877B2 (en) | 2016-08-18 | 2019-03-12 | General Electric Company | Cooling circuit for a multi-wall blade |
US20190085706A1 (en) * | 2017-09-18 | 2019-03-21 | General Electric Company | Turbine engine airfoil assembly |
US10267162B2 (en) | 2016-08-18 | 2019-04-23 | General Electric Company | Platform core feed for a multi-wall blade |
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EP3597859B1 (en) * | 2018-07-13 | 2023-08-30 | Honeywell International Inc. | Turbine blade with dust tolerant cooling system |
EP4273366A1 (en) * | 2022-05-02 | 2023-11-08 | Siemens Energy Global GmbH & Co. KG | Turbine component having platform cooling circuit |
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US20170175545A1 (en) * | 2015-12-21 | 2017-06-22 | General Electric Company | Platform core feed for a multi-wall blade |
US9926788B2 (en) | 2015-12-21 | 2018-03-27 | General Electric Company | Cooling circuit for a multi-wall blade |
US9932838B2 (en) | 2015-12-21 | 2018-04-03 | General Electric Company | Cooling circuit for a multi-wall blade |
US9976425B2 (en) | 2015-12-21 | 2018-05-22 | General Electric Company | Cooling circuit for a multi-wall blade |
US10030526B2 (en) * | 2015-12-21 | 2018-07-24 | General Electric Company | Platform core feed for a multi-wall blade |
US10053989B2 (en) | 2015-12-21 | 2018-08-21 | General Electric Company | Cooling circuit for a multi-wall blade |
US10060269B2 (en) | 2015-12-21 | 2018-08-28 | General Electric Company | Cooling circuits for a multi-wall blade |
US10119405B2 (en) | 2015-12-21 | 2018-11-06 | General Electric Company | Cooling circuit for a multi-wall blade |
US10781698B2 (en) | 2015-12-21 | 2020-09-22 | General Electric Company | Cooling circuits for a multi-wall blade |
US10221696B2 (en) | 2016-08-18 | 2019-03-05 | General Electric Company | Cooling circuit for a multi-wall blade |
US10208607B2 (en) | 2016-08-18 | 2019-02-19 | General Electric Company | Cooling circuit for a multi-wall blade |
US10227877B2 (en) | 2016-08-18 | 2019-03-12 | General Electric Company | Cooling circuit for a multi-wall blade |
US10267162B2 (en) | 2016-08-18 | 2019-04-23 | General Electric Company | Platform core feed for a multi-wall blade |
US10208608B2 (en) | 2016-08-18 | 2019-02-19 | General Electric Company | Cooling circuit for a multi-wall blade |
US20190085706A1 (en) * | 2017-09-18 | 2019-03-21 | General Electric Company | Turbine engine airfoil assembly |
EP3597859B1 (en) * | 2018-07-13 | 2023-08-30 | Honeywell International Inc. | Turbine blade with dust tolerant cooling system |
EP3719258A1 (en) * | 2019-04-04 | 2020-10-07 | MAN Energy Solutions SE | Rotor blade of a turbomachine |
US11408289B2 (en) | 2019-04-04 | 2022-08-09 | MAN Energy Solution SE | Moving blade of a turbo machine |
IL272567B1 (en) * | 2019-04-04 | 2023-06-01 | Man Energy Solutions Se | Moving blade of a turbo machine |
IL272567B2 (en) * | 2019-04-04 | 2023-10-01 | Man Energy Solutions Se | Moving blade of a turbo machine |
EP4273366A1 (en) * | 2022-05-02 | 2023-11-08 | Siemens Energy Global GmbH & Co. KG | Turbine component having platform cooling circuit |
Also Published As
Publication number | Publication date |
---|---|
WO2014055811A1 (en) | 2014-04-10 |
EP2912273A1 (en) | 2015-09-02 |
CN104704202A (en) | 2015-06-10 |
JP2015531451A (en) | 2015-11-02 |
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