WO2002027145A2 - Vane assembly for a turbine and combustion turbine with this vane assembly - Google Patents
Vane assembly for a turbine and combustion turbine with this vane assembly Download PDFInfo
- Publication number
- WO2002027145A2 WO2002027145A2 PCT/US2001/042269 US0142269W WO0227145A2 WO 2002027145 A2 WO2002027145 A2 WO 2002027145A2 US 0142269 W US0142269 W US 0142269W WO 0227145 A2 WO0227145 A2 WO 0227145A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- assembly
- ceramic
- vane
- metallic core
- vane assembly
- Prior art date
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/10—Cores; Manufacture or installation of cores
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- 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
Definitions
- This invention relates to the vanes of a turbine assembly and, more specifically, to a ceramic composite vane having a metallic substructure.
- Combustion turbine power plants generally, have three main assemblies: a compressor assembly, a combustor assembly, and a turbine assembly.
- the compressor assembly compresses ambient air.
- the compressed air is channeled into the combustor assembly where it is mixed with a fuel.
- the fuel and compressed air mixture is ignited creating a heated working gas.
- the heated working gas is typically at a temperature of between 2500 to 2900°F (1371 to 1593°C).
- the working gas is expanded through the turbine assembly.
- the turbine assembly includes a plurality of stationary vane assemblies and rotating blades. The rotating blades are coupled to a central shaft. The expansion of the working gas through the turbine assembly forces the blades to rotate creating a rotation in the shaft.
- the turbine assembly provides a means of cooling the vane assemblies.
- the first row of vane assemblies which typically precedes the first row of blades in the turbine assembly, is subject to the highest temperature of working gas.
- a coolant such as steam or compressed air, is passed through passageways formed within the vane structure. These passageways often include an opening along the trailing edge of the vane to allow the coolant to join the working gas.
- the cooling requirements for a vane assembly can be substantially reduced by providing the vane assembly with a ceramic shell as its outermost surface.
- Ceramic materials as compared to metallic materials, are less subject to degrading when exposed to high temperatures.
- Prior art ceramic vane structures included vanes constructed entirely of ceramic materials. These vanes were, however, less capable of handling the mechanical loads typically placed on turbine vanes and had a reduced length.
- Other ceramic vanes included a ceramic coating which was bonded to a thermal insulation disposed around a metallic substructure. Such a ceramic coating does not provide any significant structural support. Additionally, the bonding of the ceramic coating to the thermal insulation precludes the use of a composite ceramic. Additionally, because the ceramic was bonded to the insulating material, the ceramic could not be cooled in the conventional manner, i.e., passing a fluid through the vane assembly. The feltmetal typically has a lower tolerance to high temperature than the metallic substructure, thus additional cooling was required.
- Alternative ceramic shell/metallic substructure vanes include vanes having a ceramic leading edge and a metallic vane body, and a rotating blade having a metallic substructure and a ceramic shell having a corrugated metal partition therebetween. These structures require additional assembly steps during the final assembly of the vane or blade which are time-consuming and require a rotational force to activate certain internal seals.
- the invention provides a turbine vane assembly having a ceramic shell assembly and a metallic core assembly.
- the metallic core assembly includes an attached support assembly.
- the metallic core assembly includes passages for a cooling fluid to pass therethrough.
- the support assembly is structured to transmit the aerodynamic forces of the ceramic shell assembly to the metallic core assembly without imparting undue stress to the ceramic shell assembly.
- the support assembly can be any one of, or a combination of, a compliant layer, such as a feltmetal, contact points, such as a raised ribs or dimples on the metallic core assembly, or a biasing means, such as a leaf spring.
- the metallic core assembly includes at least one cooling passage therethrough.
- the ceramic shell assembly has an exterior surface, which is exposed to the working gas, and an interior surface.
- the ceramic shell assembly interior surface is in fluid communication with the metallic core assembly cooling passage. For example, if the ceramic shell assembly is supported by ribs on the metallic core assembly, a cooling fluid may pass between adjacent ribs. If the ceramic shell assembly is supported by a biasing means, the cooling fluid may be passed over the biasing means. If the ceramic shell assembly is supported by a compliant layer, the compliant layer may have cooling passages formed therein.
- Figure 1 is a cross sectional view of a compressor turbine power plant.
- Figure 2 is an isometric view of a vane assembly.
- Figure 3 is a cross-sectional view of a metallic core assembly, ceramic shell assembly, and support assembly comprising a layer of feltmetal.
- Figure 4 is a cross-sectional view of a metallic core assembly, ceramic shell assembly, and a support assembly comprising a plurality of contact points.
- FIG. 6 is a cross-sectional view of a metallic core assembly, ceramic shell assembly, and a support assembly comprising a layer of feltmetal, a plurality of contact points, and a biasing means.
- Figure 7 is a view of an alternate embodiment.
- Figure 8 is a view of an alternate embodiment.
- Figure 9 is a view of an alternate embodiment.
- Figure 10 is a view of an alternate embodiment. .
- a combustion turbine 1 includes a compressor assembly 2, at least one combustor assembly 3, a transition section 4, and a turbine assembly 5.
- a flow path 10 exists through the compressor assembly 2, combustor assembly 3, transition section 4, and turbine assembly 5.
- the turbine assembly 5 is mechanically coupled to the compressor assembly 2 by a central shaft 6.
- an outer casing 7 encloses a plurality of combustor assemblies 3 and transition sections 4.
- the outer casing 7 creates a compressed air plenum 8.
- the combustor assemblies 3 and transition sections 4 are disposed within the compressed air plenum 8.
- the combustor assemblies 3 are disposed circumferentiality about the central shaft 6.
- the compressor assembly 2 inducts ambient air and compresses it.
- the compressed air travels tlirough the flow path 10 to the compressed air plenum 8 defined by the casing 7.
- Compressed air within the compressed air plenum 8 enters a combustor assembly 3-where the compressed air is mixed with a fuel and ignited to create a working gas.
- the heated working gas is typically at a temperature of between 2500 to 2900°F (1371 to 1593°C).
- the working gas passes from the combustor assembly 3 tlirough the transition section 4 into the turbine assembly 5.
- the working gas is expanded through a series of rotatable blades 9, which are attached to the shaft 6, and a plurality of stationary ceramic vane assemblies 20.
- the turbine assembly 5 can be coupled to a -ge ⁇ erator ⁇ to ⁇ produce-ete ⁇ ctrioity7
- the ceramic vane assemblies 20, especially those adjacent to the transition sections 4, are exposed to the high temperature working gas.
- the turbine assembly includes a casing 12 having cooling passages 14 therethrough.
- the casing cooling passages 14 are coupled to a cooling system 16, such as an air or steam system.
- the casing cooling passages 14 are coupled to vane assembly main cooling passages 36 (described below).
- the vane assemblies 20 have an inner endcap 22, an outer endcap 24 and a body 26.
- the end caps 22, 24 are structured to be coupled to casing 12.
- the body 26 is preferably an airfoil which, in operation, will have a high pressure side and a low pressure side.
- the body 26 includes a metallic core assembly 30, a ceramic shell assembly 40, and a support assembly 50.
- the support assembly 50 is a compliant layer 52, as will be described below.
- the support assembly 50 may also be a plurality of hard contact points 54 or a biasing means 56, both described below.
- the support assembly 50 may also be a combination of two or more of a compliant layer 52, a plurality of hard contact points 54, or a biasing means 56.
- the metallic core assembly 30 includes a frame 31.
- the metallic core assembly 30 is coupled to, including being integral with, the inner endcap 22. and/or outer endcap 24. .
- the metallic core assembly 30 bears almost all mechanical loading, including aerodynamic loading, during operation.
- the frame 31 of the metallic core assembly 30 form at least one main cooling passage 36 -that-extend -between the outer endcap 24 and the inner endcap 22.
- the main cooling passages 36 are in fluid communication with the cooling system 16.
- the metallic core assembly 30 may also include at least one, and possibly two or more, spars 32, and a metallic trailing edge assembly 34. If a spar 32 is used, the metallic core assembly forms at least two cooling passages 36.
- the ceramic shell assembly 40 includes at least one layer, and preferably two layers, of a ceramic material 42.
- the ceramic layer 42 is not bonded or fixed to the metallic core assembly 30.
- the ceramic material 42 as will be descrfbed ⁇ foslow7 is "supported on the metallic core assembly 30 by the support assembly 50.
- the ceramic layer may also extend over the end caps 22, 24.
- the inner layer 46 is preferably a strain tolerant continuous fiber reinforced ceramic composite matrix which can deform to accommodate slight manufacturing tolerance mismatches and distortions due to loading such as AS-N720, A-N720, AS-N610, or A-N610 from COI Ceramics, 9617 Distribution Avenue, San Diego, CA, 92121.
- the outer layer 44 may be a monolithic ceramic.
- the outer layer 44 is, however, preferably a high temperature insulating ceramic.
- the outer layer may have an outer coating such as a conventional environmental coating or thermal barrier 45.
- the ceramic shell assembly 40 is supported on the metallic core assembly 30 by the support assembly 50.
- the support assembly 50 is coupled to, including being integral with, the metallic core assembly 30.
- the support assembly 50 may include one or more of the following support members: a compliant layer 52, a plurality of hard contact points 54, or a biasing means 56.
- the compliant layer 52 may be in the form of a continuous layer of material between the metallic core assembly 30 and the ceramic shell assembly 40.
- compliant strips may be placed between hard contact points 54 (described below).
- any combination of a semi-continuous layer and strips may also be used.
- passages 53 may be formed therein to allow cooling fluid to reach the ceramic shell assembly 40 (described below).
- the compliant layer passages 53 are in fluid communication with the main cooling passages 36 of the metallic core assembly 30.
- the compliant layer 52 may have a sufficiently porous consistency to allow a cooling fluid to pass therethrough to contact the ceramic shell assembly 40.
- the compliant layer 52 is preferably a feltmetal, such as Hastelloy-X material FM528A, FM515B, FM509D, Haynes 188 material FM21B, FM522A, or FeCrAlY material FM542, FM543, FM544, all from Technetics Corporation, 1600 Industrial Drive, DeLand, FL 32724-2095.
- the compliant layer 52 is a feltmetal, the feltmetal may be bonded or brazed to the metallic core assembly 30.
- the compliant layer 52 may also be a porous metallic foam, such as open cell foam made by Doucel ® Foams made by ERG, 900 Stanford, CA, 94608 or closed cell foam made from hollow metal powders.
- a "hard contact point” may still be somewhat compliant.
- the hard contact points 54 are, preferably, raised ribs 55 which extend over the length of the body 26.
- the hard contact points may be raised dimples as well.
- the ribs 55 may be formed integrally with the metallic core assembly 30 extending toward the ceramic shell assembly 40, or the ribs 55a may be integral with the inner layer 46 and extend toward the metallic core assembly 30.
- the ribs aid in heat transfer thereby increasing' the effectiveness of the cooling system 16.
- the hard contact points 54 are generally located on the high pressure side of the airfoil shaped body 26. Between the ribs 55 are interstices 58.
- the interstices 58 are in fluid communication with the main cooling passages 36. As described above, strips of a compliant layer 52 may be disposed in the interstices 58.
- a vane assembly 20 having a biasing means 56 for a support structure 50 is shown in Figure 5.
- the biasing means 56 is preferably a plurality of leaf springs 57, however, any type of spring may be used.
- the biasing means 56 maintains a supporting force on the ceramic shell assembly 40. This supporting force also accommodates the differential thermal expansion between the metallic core assembly 30 and the ceramic shell assembly 40.
- the biasing means 56 preferably interacts with the low pressure side of the body 26.
- a cooling fluid may flow in and around the ⁇ structure of the biasing means 56 and be in fluid communication with the ceramic shell assembly 40.
- the combination of the metallic core assembly 30, ceramic shell assembly 40 -and support assembly 50 may be structured in many -configurations.
- the ceramic shell assembly 40 may include a trailing edge portion 48 of the body 26.
- the ceramic trailing edge portion 48 may include cooling passages 49 which are in fluid communication with the cooling system 16 via openings 60.
- Another alternate design is shown in Figure 7.
- This embodiment includes a two piece metallic core assembly 30a, 30b, a ceramic shell assembly 40 having a two piece inner layer 46a, 46b and a one piece outer layer 44, and a compliant layer 52 disposed between metallic core assembly 30a, 30b and the ⁇ two-pTCce ⁇ innerlayer-46a", 46hr ⁇ Figure-?- further ⁇ shows ⁇ a -plurality of'connecting passages 60 which are in fluid communication with the main passages 36 and the compliant layer 52.
- Figure 8 shows another alternate embodiment.
- this embodiment includes a two piece metallic core assembly 30a, 30b, and a ceramic shell assembly 40 having a two piece inner layer 46a, 46b and a one piece outer layer 44.
- the support assembly 50 is a plurality of leaf springs 70.
- the metallic core assembly 30 includes a plurality of connecting passages 60 that permit fluid communication between the main passages 36 and the support assembly 50.
- a support pin 80 extending between the endcaps.22, 24, may be used to reduce the movement between the inner layer portions 46a, 46b.
- the inner layer portions 46a, 46b may include deflections 82, 84 along an interface 86 to reduce the movement between the inner layer portions 46a, 46b.
- the metallic core assembly 30 and ceramic shell assembly 40 may include a structural lock 90 formed by the metallic core assembly 30 and the inner layer 46a, 46b.
- the structural lock 90 includes tabs 91, 92, 93, and 94, which extend toward the interface 86 between the inner layer portions 46a, 46b.
- the inner layer portions 46a, 46b include tabs 95, 96, 97, and 98 which are structured to extend around tabs 91, 92, 93, and 94 respectively.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP01985737.4A EP1392956B1 (en) | 2000-09-29 | 2001-09-24 | Vane assembly for a turbine and combustion turbine with this vane assembly |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/677,044 US6514046B1 (en) | 2000-09-29 | 2000-09-29 | Ceramic composite vane with metallic substructure |
US09/676,061 US6558114B1 (en) | 2000-09-29 | 2000-09-29 | Gas turbine with baffle reducing hot gas ingress into interstage disc cavity |
US09/677,044 | 2000-09-29 |
Publications (3)
Publication Number | Publication Date |
---|---|
WO2002027145A2 true WO2002027145A2 (en) | 2002-04-04 |
WO2002027145A3 WO2002027145A3 (en) | 2003-12-11 |
WO2002027145A8 WO2002027145A8 (en) | 2004-01-15 |
Family
ID=29715548
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2001/042269 WO2002027145A2 (en) | 2000-09-29 | 2001-09-24 | Vane assembly for a turbine and combustion turbine with this vane assembly |
Country Status (1)
Country | Link |
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WO (1) | WO2002027145A2 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1367223A2 (en) * | 2002-05-31 | 2003-12-03 | Siemens Westinghouse Power Corporation | Ceramic matrix composite gas turbine vane |
EP2853688A3 (en) * | 2013-09-30 | 2015-07-22 | MTU Aero Engines GmbH | Blade for a gas turbine |
EP2599959A3 (en) * | 2011-12-01 | 2016-09-14 | United Technologies Corporation | Ceramic matrix composite airfoil structure with trailing edge support for a gas turbine engine |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
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US3758233A (en) * | 1972-01-17 | 1973-09-11 | Gen Motors Corp | Vibration damping coatings |
GB1487063A (en) * | 1974-08-23 | 1977-09-28 | Rolls Royce | Aero-foil member for a gas turbine engine |
US4148350A (en) * | 1975-01-28 | 1979-04-10 | Mtu-Motoren Und Turbinen-Union Munchen Gmbh | Method for manufacturing a thermally high-stressed cooled component |
GB2123489A (en) * | 1982-07-12 | 1984-02-01 | Rockwell International Corp | Support a ceramic blade for a gas turbine |
DE3235230A1 (en) * | 1982-09-23 | 1984-03-29 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Gas turbine blade having a metal core and a ceramic vane |
US4629397A (en) * | 1983-07-28 | 1986-12-16 | Mtu Motoren-Und Turbinen-Union Muenchen Gmbh | Structural component for use under high thermal load conditions |
US5279111A (en) * | 1992-08-27 | 1994-01-18 | Inco Limited | Gas turbine cooling |
US5419039A (en) * | 1990-07-09 | 1995-05-30 | United Technologies Corporation | Method of making an air cooled vane with film cooling pocket construction |
US5626462A (en) * | 1995-01-03 | 1997-05-06 | General Electric Company | Double-wall airfoil |
-
2001
- 2001-09-24 WO PCT/US2001/042269 patent/WO2002027145A2/en active Application Filing
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3758233A (en) * | 1972-01-17 | 1973-09-11 | Gen Motors Corp | Vibration damping coatings |
GB1487063A (en) * | 1974-08-23 | 1977-09-28 | Rolls Royce | Aero-foil member for a gas turbine engine |
US4148350A (en) * | 1975-01-28 | 1979-04-10 | Mtu-Motoren Und Turbinen-Union Munchen Gmbh | Method for manufacturing a thermally high-stressed cooled component |
GB2123489A (en) * | 1982-07-12 | 1984-02-01 | Rockwell International Corp | Support a ceramic blade for a gas turbine |
DE3235230A1 (en) * | 1982-09-23 | 1984-03-29 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Gas turbine blade having a metal core and a ceramic vane |
US4629397A (en) * | 1983-07-28 | 1986-12-16 | Mtu Motoren-Und Turbinen-Union Muenchen Gmbh | Structural component for use under high thermal load conditions |
US5419039A (en) * | 1990-07-09 | 1995-05-30 | United Technologies Corporation | Method of making an air cooled vane with film cooling pocket construction |
US5279111A (en) * | 1992-08-27 | 1994-01-18 | Inco Limited | Gas turbine cooling |
US5626462A (en) * | 1995-01-03 | 1997-05-06 | General Electric Company | Double-wall airfoil |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1367223A2 (en) * | 2002-05-31 | 2003-12-03 | Siemens Westinghouse Power Corporation | Ceramic matrix composite gas turbine vane |
EP1367223A3 (en) * | 2002-05-31 | 2005-11-09 | Siemens Westinghouse Power Corporation | Ceramic matrix composite gas turbine vane |
EP2599959A3 (en) * | 2011-12-01 | 2016-09-14 | United Technologies Corporation | Ceramic matrix composite airfoil structure with trailing edge support for a gas turbine engine |
EP2853688A3 (en) * | 2013-09-30 | 2015-07-22 | MTU Aero Engines GmbH | Blade for a gas turbine |
Also Published As
Publication number | Publication date |
---|---|
WO2002027145A3 (en) | 2003-12-11 |
WO2002027145A8 (en) | 2004-01-15 |
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