US20080219855A1 - Turbine blade with micro-turbine nozzle provided in the blade root - Google Patents

Turbine blade with micro-turbine nozzle provided in the blade root Download PDF

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Publication number
US20080219855A1
US20080219855A1 US12/073,620 US7362008A US2008219855A1 US 20080219855 A1 US20080219855 A1 US 20080219855A1 US 7362008 A US7362008 A US 7362008A US 2008219855 A1 US2008219855 A1 US 2008219855A1
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Prior art keywords
turbine
micro
blade
nozzle element
duct
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Abandoned
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US12/073,620
Inventor
Richard Whitton
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Rolls Royce Deutschland Ltd and Co KG
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Rolls Royce Deutschland Ltd and Co KG
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Assigned to ROLLS-ROYCE DEUTSCHLAND LTD & CO KG reassignment ROLLS-ROYCE DEUTSCHLAND LTD & CO KG ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: WHITTON, RICHARD
Publication of US20080219855A1 publication Critical patent/US20080219855A1/en
Abandoned legal-status Critical Current

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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
    • 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
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction
    • 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
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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
    • F05D2210/00—Working fluids
    • F05D2210/40—Flow geometry or direction
    • F05D2210/43—Radial inlet and axial outlet
    • 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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/238—Soldering
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • F05D2250/141—Two-dimensional elliptical circular
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/184—Two-dimensional patterned sinusoidal
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/713—Shape curved inflexed

Definitions

  • This invention relates to a turbine blade having a curved and converging micro-turbine nozzle in its blade root which originates at a cooling-air chamber in the blade root and issues downstream opposite to a direction of rotation of a turbine rotor wheel.
  • the blade roots of the turbine blades of the turbine rotor wheel of the first stage are each provided with a cooling-air duct which branches off a cooling-air chamber and issues downstream and through which part of the cooling air fed into the turbine blade is supplied to the next turbine stage.
  • This cooling-air duct which originates at a cooling-air chamber in the blade root, converges and continuously curves towards the air exit side such that the cooling air exits opposite to the direction of rotation of the turbine rotor wheel.
  • the cooling air produces power.
  • the micro-turbine so provided in the blade roots is an additional propulsive element for the first turbine rotor wheel.
  • the cooling air is cooled according to the turbine principle, thus being available with improved cooling effect for the cooling of the turbine wheel of the following turbine stage.
  • the essence of the present invention is that the turbine blade does not form one part with the micro-turbine nozzle, but that a passage duct with large diameter is formed in the area of the blade root provided for the micro-turbine nozzle, which extends from the cooling-air chamber to the downstream side of the blade root, and that said passage duct is produced by drilling, machining or integrally in the casting process, and that a separately produced micro-turbine nozzle element is partly or also completely fitted into this duct, has a converging nozzle with a cross-section which is minimised in size and is flexible, i.e. is adapted to the required operating conditions.
  • An essential advantage of the turbine blade in accordance with the present invention lies in the flexible cross-sectional size of the micro-turbine nozzle which is adaptable to the respective operating conditions by way of a separately produced micro-turbine nozzle element fitted into the passage duct.
  • the nozzle cross-section is reducible, as a result of which an efficiency-reducing decrease of the pressure of the cooling air supplied is not necessary.
  • the cooling-air mass flow introduced into the space between the two turbine rotor wheels can be set as low as necessary, thereby avoiding cooling air losses and a reduction of turbine efficiency.
  • FIG. 1 shows a turbine blade with a micro-turbine nozzle integrated into the blade root by way of a separately produced component according to the present invention.
  • FIG. 1 shows a turbine blade 1 of the first turbine stage with a cooling-air chamber 3 provided in the blade root 2 , this cooling-air chamber 3 being continuously supplied with cooling air via an opening 4 in the blade root 2 . While part of the cooling air is used for cooling the airfoil 5 , another part of the cooling air flows, via the passage duct 6 branching off the cooling-air chamber 3 and through a duct 9 of a micro-turbine nozzle element 7 partly integrated into the passage duct 6 , into the space 8 between the first and the second turbine stage and, from there, into the blade root of the turbine blades of the second stage (not shown).
  • the turbine blades 1 are produced in a casting process, actually with passage ducts 6 having a sufficiently large diameter. With its correspondingly large diameter, the ceramic core for casting the passage duct 6 will have adequate strength and will, therefore, not be damaged or destroyed during casting.
  • the passage duct can also be produced by drilling the blade root.
  • the micro-turbine nozzle element 7 is a separate component which is produced in a simple manner, for instance, in a cutting shaping process from a blank which is formed by machining or in a non-cutting shaping process, or by injection molding, or by other methods, and is fitted completely or, as shown here, partly into the passage duct 6 and attached therein by known joining processes, such as brazing.
  • the flow area of the duct 9 of the nozzle element 7 according to the present invention is no longer dictated by the passage duct 6 , and can be selectively varied as desired.
  • the now freely selectable size of the flow area of the micro-turbine nozzle allows the cooling air supply to the following turbine stage to be optimally and variably set in accordance with the required operating conditions, at least without unnecessary cooling air losses.

Abstract

A turbine blade, in the blade root (2) of which a curved and converging micro-turbine nozzle is provided, includes a passage duct (6) with large diameter originating at a cooling-air chamber (3) in the blade root, with a separately prefabricated micro-turbine nozzle element (7) with minimized flow cross-section, that is variably adaptable in size to the respective operating conditions, being fitted into said passage duct (6). Due to the reducible air mass flow that is adaptable to the actual requirements in the space between the turbine rotor wheels, air losses are reduced and efficiency is enhanced.

Description

  • This application claims priority to German Patent Application DE 102007012320.7 filed Mar. 9, 2007, the entirety of which is incorporated by reference herein.
  • This invention relates to a turbine blade having a curved and converging micro-turbine nozzle in its blade root which originates at a cooling-air chamber in the blade root and issues downstream opposite to a direction of rotation of a turbine rotor wheel.
  • On a gas-turbine engine known from specification U.S. Pat. No. 6,290,464 B1, the blade roots of the turbine blades of the turbine rotor wheel of the first stage are each provided with a cooling-air duct which branches off a cooling-air chamber and issues downstream and through which part of the cooling air fed into the turbine blade is supplied to the next turbine stage. This cooling-air duct, which originates at a cooling-air chamber in the blade root, converges and continuously curves towards the air exit side such that the cooling air exits opposite to the direction of rotation of the turbine rotor wheel. Because of the curvature and convergence of the cooling-air duct resulting in continuous deflection of the cooling air opposite to the direction of rotation of the rotor wheel and the expansion of the cooling air, the cooling air produces power. The micro-turbine so provided in the blade roots is an additional propulsive element for the first turbine rotor wheel. Simultaneously, the cooling air is cooled according to the turbine principle, thus being available with improved cooling effect for the cooling of the turbine wheel of the following turbine stage.
  • Manufacture of a cooling-air duct of such curvature and convergence towards the air exit side in the blade roots is, however, problematic in that the very slender and also brittle ceramic cores applied in precision casting of turbine blades by the lost-wax process for forming the very thin cooling-air ducts are liable to failure, rendering manufacture by conventional precision casting processes impossible. Also, manufacture of the converging and curved cooling-air duct by cutting machining directly in the blade root is only possible to a limited extent and confined to larger diameters, especially as the smaller diameter is formed by the exit opening. Directly in the blade root, the known casting and mechanical machining processes are only appropriate for the manufacture of cooling-air ducts with larger diameter. However, such larger diameters will entail high cooling-air losses and decrease the efficiency of the turbine. Disposing the micro-turbine nozzles in turbine holding or cover plates, which is also proposed in specification U.S. Pat. No. 6,290,464, is restricted to the design provided for these plates. This bears on the efficiency of the micro-turbine nozzles.
  • It is a broad aspect of the present invention to provide the micro-turbine nozzle in the blade root such that small duct cross-sections and, thus, low cooling-air losses and improved engine efficiency can be obtained.
  • The essence of the present invention is that the turbine blade does not form one part with the micro-turbine nozzle, but that a passage duct with large diameter is formed in the area of the blade root provided for the micro-turbine nozzle, which extends from the cooling-air chamber to the downstream side of the blade root, and that said passage duct is produced by drilling, machining or integrally in the casting process, and that a separately produced micro-turbine nozzle element is partly or also completely fitted into this duct, has a converging nozzle with a cross-section which is minimised in size and is flexible, i.e. is adapted to the required operating conditions.
  • The known precision casting processes for the manufacture of turbine blades whose blade root forms one integral part with the micro-turbine nozzle, only allows large nozzle cross-sections which affect the efficiency of the turbine. An essential advantage of the turbine blade in accordance with the present invention lies in the flexible cross-sectional size of the micro-turbine nozzle which is adaptable to the respective operating conditions by way of a separately produced micro-turbine nozzle element fitted into the passage duct. Other than in the state of the art, the nozzle cross-section is reducible, as a result of which an efficiency-reducing decrease of the pressure of the cooling air supplied is not necessary. The cooling-air mass flow introduced into the space between the two turbine rotor wheels can be set as low as necessary, thereby avoiding cooling air losses and a reduction of turbine efficiency.
  • FIG. 1 shows a turbine blade with a micro-turbine nozzle integrated into the blade root by way of a separately produced component according to the present invention.
  • FIG. 1 shows a turbine blade 1 of the first turbine stage with a cooling-air chamber 3 provided in the blade root 2, this cooling-air chamber 3 being continuously supplied with cooling air via an opening 4 in the blade root 2. While part of the cooling air is used for cooling the airfoil 5, another part of the cooling air flows, via the passage duct 6 branching off the cooling-air chamber 3 and through a duct 9 of a micro-turbine nozzle element 7 partly integrated into the passage duct 6, into the space 8 between the first and the second turbine stage and, from there, into the blade root of the turbine blades of the second stage (not shown).
  • The turbine blades 1 are produced in a casting process, actually with passage ducts 6 having a sufficiently large diameter. With its correspondingly large diameter, the ceramic core for casting the passage duct 6 will have adequate strength and will, therefore, not be damaged or destroyed during casting. The passage duct can also be produced by drilling the blade root. The micro-turbine nozzle element 7 is a separate component which is produced in a simple manner, for instance, in a cutting shaping process from a blank which is formed by machining or in a non-cutting shaping process, or by injection molding, or by other methods, and is fitted completely or, as shown here, partly into the passage duct 6 and attached therein by known joining processes, such as brazing. The flow area of the duct 9 of the nozzle element 7 according to the present invention is no longer dictated by the passage duct 6, and can be selectively varied as desired.
  • Besides reduced manufacturing cost, the now freely selectable size of the flow area of the micro-turbine nozzle allows the cooling air supply to the following turbine stage to be optimally and variably set in accordance with the required operating conditions, at least without unnecessary cooling air losses.
    • LIST OF REFERENCE NUMERALS
    • 1 Turbine blade
    • 2 Blade root
    • 3 Cooling-air chamber
    • 4 Opening
    • 5 Airfoil
    • 6 Passage duct
    • 7 Micro-turbine nozzle element
    • 8 Space between turbine rotor wheels
    • 9 Duct of nozzle element

Claims (16)

1. A turbine blade, comprising:
an airfoil:
a blade root connected to the airfoil;
a cooling air chamber positioned in the blade root and connected between a cooling air supply and the airfoil;
a passage duct connected between the cooling air chamber and an exterior of the blade to a space between turbine rotor wheels;
a separately prefabricated micro-turbine nozzle element having a portion positioned in the passage duct and attached to the blade root, the micro-turbine nozzle element having a duct for directing cooling air flow from the cooling air chamber to the space between the turbine rotor wheels in a direction opposite to a direction of rotation of the turbine rotor wheels, the duct of the micro-turbine nozzle element having a flow cross-section smaller than a flow cross-section of the passage duct and which is selectable in size depending on respective operating conditions.
2. The turbine blade of claim 1, wherein the prefabricated micro-turbine nozzle element is attached to the blade root by a joining process.
3. The turbine blade of claim 2, wherein the prefabricated micro-turbine nozzle element is attached to the blade root by brazing.
4. The turbine blade of claim 1, wherein the micro-turbine nozzle element is a machined component fabricated from a non-machined but shaped blank.
5. The turbine blade of claim 1, wherein the micro-turbine nozzle element is injection molded.
6. The turbine blade of claim 1, wherein the passage duct is a cast duct.
7. The turbine blade of claim 1, wherein the passage duct is a drilled duct.
8. The turbine blade of claim 1, wherein the micro-turbine nozzle element fits entirely within the passage duct.
9. A method for producing a turbine blade having an airfoil and a blade root connected to the airfoil, comprising:
forming a cooling air chamber in the blade root and connected between a cooling air supply and the airfoil;
forming a passage duct connected between the cooling air chamber and an exterior of the blade to a space between turbine rotor wheels;
separately fabricating a micro-turbine nozzle element having a duct for directing cooling air flow from the cooling air chamber to the space between the turbine rotor wheels in a direction opposite to a direction of rotation of the turbine rotor wheels, the duct of the micro-turbine nozzle element having a flow cross-section smaller than a flow cross-section of the passage duct;
varying the flow cross-section of the duct of the micro-turbine nozzle element depending on respective operating conditions;
positioning the micro-turbine nozzle element so that at least a portion thereof is placed in the passage duct;
attaching the micro-turbine nozzle element to the blade root.
10. The method of claim 9, wherein the micro-turbine nozzle element is attached to the blade root by a joining process.
11. The method of claim 10, wherein the micro-turbine nozzle element is attached to the blade root by brazing.
12. The method of claim 9, wherein the micro-turbine nozzle element is fabricated in a cutting shaping process from a blank produced by non-cutting shaping.
13. The method of claim 9, wherein the micro-turbine nozzle element is injection molded.
14. The method of claim 9, wherein the passage duct is integrally cast when casting the turbine blade.
15. The method of claim 9, wherein the passage duct is drilled into the turbine blade.
16. The method of claim 9, wherein the micro-turbine nozzle element is positioned entirely within the passage duct.
US12/073,620 2007-03-09 2008-03-07 Turbine blade with micro-turbine nozzle provided in the blade root Abandoned US20080219855A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007012320A DE102007012320A1 (en) 2007-03-09 2007-03-09 Turbine blade with blade-formed microturbine nozzle
DE102007012320.7 2007-03-09

Publications (1)

Publication Number Publication Date
US20080219855A1 true US20080219855A1 (en) 2008-09-11

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EP (1) EP1967692A3 (en)
DE (1) DE102007012320A1 (en)

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WO2014025440A2 (en) * 2012-05-31 2014-02-13 United Technologies Corporation Turbine blade root with microcircuit cooling passages
EP2204533A3 (en) * 2008-12-30 2017-06-14 General Electric Company Methods, systems and/or apparatus relating to inducers for turbine engines
US10436031B2 (en) 2015-07-20 2019-10-08 Rolls-Royce Deutschland Ltd & Co Kg Cooled turbine runner, in particular for an aircraft engine
CN112459849A (en) * 2020-10-27 2021-03-09 哈尔滨广瀚燃气轮机有限公司 Cooling structure for turbine blade of gas turbine

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US4453888A (en) * 1981-04-01 1984-06-12 United Technologies Corporation Nozzle for a coolable rotor blade
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US5795130A (en) * 1995-11-24 1998-08-18 Mitsubishi Jukogyo Kabushiki Kaisha Heat recovery type gas turbine rotor
US6290464B1 (en) * 1998-11-27 2001-09-18 Bmw Rolls-Royce Gmbh Turbomachine rotor blade and disk
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US6971852B2 (en) * 2003-03-26 2005-12-06 Rolls-Royce Plc Method of and structure for enabling cooling of the engaging firtree features of a turbine disk and associated blades
US7029236B2 (en) * 2000-03-02 2006-04-18 Hitachi, Ltd. Closed circuit blade-cooled turbine
US7121797B2 (en) * 2003-07-11 2006-10-17 Rolls-Royce Deutschland Ltd & Co Kg Cooled turbine rotor wheel, in particular, a high-pressure turbine rotor wheel for an aircraft engine
US20090297361A1 (en) * 2008-01-22 2009-12-03 United Technologies Corporation Minimization of fouling and fluid losses in turbine airfoils

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US6234746B1 (en) * 1999-08-04 2001-05-22 General Electric Co. Apparatus and methods for cooling rotary components in a turbine
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Publication number Priority date Publication date Assignee Title
US3846041A (en) * 1972-10-31 1974-11-05 Avco Corp Impingement cooled turbine blades and method of making same
US4453888A (en) * 1981-04-01 1984-06-12 United Technologies Corporation Nozzle for a coolable rotor blade
US4645421A (en) * 1985-06-19 1987-02-24 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Hybrid vane or blade for a fluid flow engine
US5795130A (en) * 1995-11-24 1998-08-18 Mitsubishi Jukogyo Kabushiki Kaisha Heat recovery type gas turbine rotor
US6290464B1 (en) * 1998-11-27 2001-09-18 Bmw Rolls-Royce Gmbh Turbomachine rotor blade and disk
US6485255B1 (en) * 1999-09-18 2002-11-26 Rolls-Royce Plc Cooling air flow control device for a gas turbine engine
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WO2014025440A2 (en) * 2012-05-31 2014-02-13 United Technologies Corporation Turbine blade root with microcircuit cooling passages
WO2014025440A3 (en) * 2012-05-31 2014-04-17 United Technologies Corporation Turbine blade root with microcircuit cooling passages
US9422817B2 (en) 2012-05-31 2016-08-23 United Technologies Corporation Turbine blade root with microcircuit cooling passages
US10436031B2 (en) 2015-07-20 2019-10-08 Rolls-Royce Deutschland Ltd & Co Kg Cooled turbine runner, in particular for an aircraft engine
CN112459849A (en) * 2020-10-27 2021-03-09 哈尔滨广瀚燃气轮机有限公司 Cooling structure for turbine blade of gas turbine

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