US3807892A - Cooled guide blade for a gas turbine - Google Patents

Cooled guide blade for a gas turbine Download PDF

Info

Publication number
US3807892A
US3807892A US00324779A US32477973A US3807892A US 3807892 A US3807892 A US 3807892A US 00324779 A US00324779 A US 00324779A US 32477973 A US32477973 A US 32477973A US 3807892 A US3807892 A US 3807892A
Authority
US
United States
Prior art keywords
blade
flow path
flow
coolant
pressure chamber
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.)
Expired - Lifetime
Application number
US00324779A
Other languages
English (en)
Inventor
O Frei
O Iten
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Brown Boveri Sulzer Turbomaschinen AG
ABB Stal AB
Original Assignee
Brown Boveri Sulzer Turbomaschinen AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Brown Boveri Sulzer Turbomaschinen AG filed Critical Brown Boveri Sulzer Turbomaschinen AG
Application granted granted Critical
Publication of US3807892A publication Critical patent/US3807892A/en
Assigned to ABB STAL AB, A CORP. OF SWEDEN reassignment ABB STAL AB, A CORP. OF SWEDEN ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: BROWN BOVERI-SULZER TURBOMACHINERY LTD., A CORP. OF SWITZERLAND
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F05D2260/221—Improvement of heat transfer
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the first path is subjected to a low pressuredrop and with a narrow cross-section allows the collant to flow through atvhigh velocity to obtain a rapid heat transfer.
  • the second path is also subjected to a low pressure drop, but with a larger cross-section in the middle part of the blade body and restrictors at the trailing edge, also allows discharge at high velocity.
  • both guide blades and rotor blades in an operating turbine, two contradictory conditions must be basically satisfied.
  • good cooling requires high coefficients of heat transmission which, in turn, involve high flow velocities and relatively high pressure losses.
  • the amount of cooling air required by each blade should be as small as possible because the cooling air branched off, for example, from a compressor represents a loss in a certain sense and results in a deterioration of the efficiency of the entire process.
  • the pressure gradient available between the cooling air entry into the blade and the cooling air exit from the blade is relatively low.
  • the required velocities cannot be obtained or, if obtained because a high consumption of cooling air can be tolerated, is done only with difficulty.
  • one or more streams of cooling air are blown into the blade, generally through the blade root.
  • the flows have then been branched and/or are repeatedly reversed before emerging from' the blade through air exits which may be disposed in the blade front or tip and/or the blade root or in the trailing edge. If the flow ducts in these constructions are relatively narrow to achieve the necessary velocities, this will necessarily result in high pressure losses. This applies particularly to constructions in which the cooling air in the zone of the blade front or in the middle of the blade is fed into the blade root and is guided to the trailing edge after repeated reversals.
  • any defined distribution of branch flows can hardly be achieved, for example, because of uneven bulkhead perforations.
  • either specific parts receive only insufficient cooling or unnecessarily large quantities of cooling air are required.
  • the invention provides a guide blade for a gas turbine comprising a blade body having a blade front and a trailing edge with two separate flow paths in which a coolant flow is reversed at least once for cooling different portions of the blade.
  • a first means defines a first flow path in the body immediately downstream of and parallel to the blade front. This first flow path includes at least two parallel portions to reverse the flow of coolant at least once and terminates in a first exit in or near to the trailing edge of the blade.
  • a second means defines a second flow path in the body which includes at least two parallel portions to reverse a second flow of coolant at least once and also terminates in a second exit in or near to the trailing edge of the blade. Both flow paths emanate from a common pressure chamber in the blade body which is adapted to receive a supply of coolant, such as air while only the first flow path passes through a second pressure chamber on the opposite side of the body.
  • the respective pressure chambers can be defined in part by blade coverings or boundary jackets which extend outwardly from the blade front.
  • the direct stream flowing in the longitudinal direction of the blade front not only cools the blade front because of its high velocity but is also utilized to absorb a substantial part of the heat on the trailing edge without the pressure losses becoming excessively high.
  • This latter effect is due to the practically loss-free pressure chamber which is disposed between the blade front and air exit.
  • defined distribution over the part flows may beachieved in known manner by the use of suitable restrictors in the air exits. Such restrictors may be varied to a certain extent and may be individually adjusted on the basis of tests in order to vary the distribution over a small range and, for example, to compensate for manufacturing inaccuracies.
  • the second flow path may be advantageously constructed to extend parallel to the first flow path with at least two reversals through and to be practically free'sr pressure isss'sas far as the seeoaa'revsrsai;
  • the portions of the body which define this second flow path may also be provided with boundary walls on which fins are provided at least over a portion of the walls to project into the flow path. The purpose of this is to increase the cooled surface in the low-pressure loss zone of low flow velocity and thus to improve cooling thereat.
  • the construction enables the entire blade segments, that is the blades of the segment and the jacket boundaries of the common external and internal pressure chambers to be integrally cast while a separate separating plate is provided for each blade and cover plates are provided which are common to the entire segment.
  • FIG. 1 illustrates a longitudinal sectional view taken along. line I-I of FIG. 2 of a guide blade according to the invention
  • FIG. 2 illustrates a sectional view taken on line IIII of FIG. 1;
  • FIGS. 3 and 4 each illustrates in the same manner as in FIG. 2 a detail of the trailing edge of a blade according to FIG. 1 but of different construction.
  • the guide blade to which hot gases flow from the left (arrow A) as viewed, through a flow duct 2 from one or more combustion chambers (not shown) is retained in a guide blade support 3 within a gas turbine (not shown).
  • the hot gas duct 2 is defined in the upstream direction by different parts of a hot gas casing 4 in which flow paths 5, 6 are provided for cooling the blade from the outside. These flow paths are adapted to conduct a coolant such as cooling air from an air receiver (not shown) which surrounds the guide blade support 3 along the inner and outer boundaries of the duct 2.
  • the cooling air flow paths 5, 6 also cool the parts 4a of the hot gas casing 4 of hightemperature resistant materials and separate these parts 4a from another part 4b of the casing 4 which is not directly subjected to the hot gases or from the guide blade support 3. Both of these latter parts 4b, 3 are constructed of ferritic material having a lower hightemperature strength. Downstream of the illustrated guide blade, the guide blade support 3 is also protected against hot gases by a filler ring segment 9 which is also constructed of high-temperature resistant material.
  • the cooling air for the blade first passes from the air receiver (not shown) through an aperture 10 in the blade support 3 into an intermediate chamber 11. The air then flows through an aperture 12 into a pressure chamber 13 which is disposed in an outer blade covering or boundary jacket 14'.
  • the blade body has a blade front 8 facing the duct 2 and a trailing edge 19 disposed downstream of the blade front 8.
  • two flow paths are defined by various means within the blade body. These flow paths serve to pass cooling air through the blade and extend from the pressure chamber 13.
  • the first flow path leads into a second pressure chamber 16 through a relatively narrow duct 15 disposed immediately downstream of the blade front 8.
  • the second pressure chamber 16 is shown disposed in an inner blade covering or boundary jacket 17. Air which passes through the first path leaves the pressure chamber 16, through which the air flows practically without pressure loss, and passes through an air exit 18 which extends over part of the blade height in the zone of the trailing edge 19.
  • This air exit 18 may be disposed in the trailing edge itself as shown in FIG. 2 or may be disposed on the suction side (FIG. 3) or on the delivery side (FIG. 4) of the blade.
  • the second flow path extends parallel to the first flow path and includes a relatively wide duct 20 in the blade body which is connected via a reversal chamber 21 in which the flow passes through a first reversal of to a duct 22 which is also relatively wide and is disposed in the middle part of the blade.
  • the duct 22 communicates via a reversal chamber 23, of optimum construction for the flow because of the pressure-loss, in which the flow passes through a further reversal of 180 to an air exit 24 which is also disposed in the zone of the trailing edge 19. This exit 24 is separated by a bulkhead 26 from the air exit 18 for the first flow path and fills the height of the blade 1 which is not covered by the exit 18.
  • the air exit 24 may, of course, also be disposed in the trailing edge 19 itself or on the suction side or on the delivery side of the blade.
  • the duct 22 is provided with fins 25 over the height of the opposed boundary walls to increase the heat dissipating surfaces.
  • the relatively low available pressure gradient between the pressure chamber l3-and the first duct 2 in the zone of the trailing edge 19 of the blade in the first flow path allows a relatively high velocity to be obtained in the arrow duct 15. This, therefore, allows a large coefficient of heat transfer and intensive cooling of the blade front 8 to be achieved. In a practical embodiment, approximately half the pressure gradient is utilized in this way. After flowing through the pressure chamber 16 practically without loss, the remaining positive pressure relative to the duct 2 results in high velocities in the air exit 18 and therefore in good cooling of part of the blade height in the zone of the trailing edge 19.
  • the air enters the reversal chamber 23 with relatively low velocities and practically without pressure losses, that is, with the exception of the two reversals through 180.
  • the entire available pressure gradient is thus utilized to achieve the most uniform possible discharge at high velocities and corresponding good cooling of the trailing edge l9over the remaining blade height in the zone of the air exit 24.
  • the flow resistances which may be altered to a certain extent by modification of the fins 30 which act as restrictors and guide surfaces in the air exits 18 and 24, may be experimentally matched to each other in both flow paths so that the available amount of cooling air is distributed over both paths in a ratio which is at least approximately constant. This ratio will then also define the relative height of the bulkhead 26 by means of which the entire blade height is subdivided over the two air exits l8 and 24 approximately in'the ratio of the part quantities, if the exit cross-section is approximately constant over the entire height.
  • the blade together with the coverings l4 and 17 can be made as a precision casting of a hightemperature resistant cast alloy. After completion of the casting, a separating plate 27 is welded therein sealtight manner to separate the reversing chamber 21 from the delivery chamber 16. Cover plates 28 and 29 which are also subsequently welded in position in sealtight manner are provided to separate the delivery chambers l3, 16 from the ambient zone.
  • the guide blades are constructed as blade segments in a guide blade ring with the blade segments comprising a plurality of blades, such can also be produced as a casting by the precision casting method.
  • the separating plates 27 are then co-ordinated to the individual blades but the cover plates 28 and 29 are common to the entire segment.
  • a cooled guide blade for a gas turbine comprising a blade body having a blade front and a trailing edge;
  • a first pressure chamber in said body for receiving a supply of coolant
  • a cooled guide blade as set forth in claim 1 which further comprises an outer cover plate over said first pressure chamber and an inner cover plate over said second pressure chamber.
  • a cooled guide blade as set forth in claim 7 wherein said body and said coverings form an integral one-piece precision casting and which further comprises a separating plate disposed in said body in sealtight manner between said flow paths, an outer cover plate disposed in said body in seal-tight manner over said first chamber and an inner cover plate disposed in said body in seal-tight manner over said second chamber and opposite to said separating plate relative to said second chamber.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US00324779A 1972-01-18 1973-01-18 Cooled guide blade for a gas turbine Expired - Lifetime US3807892A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH69972 1972-01-18

Publications (1)

Publication Number Publication Date
US3807892A true US3807892A (en) 1974-04-30

Family

ID=4193097

Family Applications (1)

Application Number Title Priority Date Filing Date
US00324779A Expired - Lifetime US3807892A (en) 1972-01-18 1973-01-18 Cooled guide blade for a gas turbine

Country Status (11)

Country Link
US (1) US3807892A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
JP (1) JPS5145726B2 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
BE (1) BE794195A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
CA (1) CA967095A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
CH (1) CH547431A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
DE (1) DE2202858C2 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
FR (1) FR2168802A5 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
GB (1) GB1359983A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
IT (1) IT978243B (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
NL (1) NL164358C (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
SE (1) SE381311B (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)

Cited By (68)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3989412A (en) * 1974-07-17 1976-11-02 Brown Boveri-Sulzer Turbomachinery, Ltd. Cooled rotor blade for a gas turbine
US4019831A (en) * 1974-09-05 1977-04-26 Brown Boveri Sulzer Turbomachinery Ltd. Cooled rotor blade for a gas turbine
FR2326570A1 (fr) * 1975-10-03 1977-04-29 United Technologies Corp Aube de turbine refroidie par air
US4236870A (en) * 1977-12-27 1980-12-02 United Technologies Corporation Turbine blade
US4278400A (en) * 1978-09-05 1981-07-14 United Technologies Corporation Coolable rotor blade
US4293275A (en) * 1978-09-14 1981-10-06 Hitachi, Ltd. Gas turbine blade cooling structure
US4303374A (en) * 1978-12-15 1981-12-01 General Electric Company Film cooled airfoil body
US4330235A (en) * 1979-02-28 1982-05-18 Tokyo Shibaura Denki Kabushiki Kaisha Cooling apparatus for gas turbine blades
US4462754A (en) * 1981-06-30 1984-07-31 Rolls Royce Limited Turbine blade for gas turbine engine
US4474532A (en) * 1981-12-28 1984-10-02 United Technologies Corporation Coolable airfoil for a rotary machine
US4753575A (en) * 1987-08-06 1988-06-28 United Technologies Corporation Airfoil with nested cooling channels
US4767268A (en) * 1987-08-06 1988-08-30 United Technologies Corporation Triple pass cooled airfoil
US5030060A (en) * 1988-10-20 1991-07-09 The United States Of America As Represented By The Secretary Of The Air Force Method and apparatus for cooling high temperature ceramic turbine blade portions
US5217347A (en) * 1991-09-05 1993-06-08 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) Mounting system for a stator vane
US5503529A (en) * 1994-12-08 1996-04-02 General Electric Company Turbine blade having angled ejection slot
US5536143A (en) * 1995-03-31 1996-07-16 General Electric Co. Closed circuit steam cooled bucket
US5591002A (en) * 1994-08-23 1997-01-07 General Electric Co. Closed or open air cooling circuits for nozzle segments with wheelspace purge
US5634766A (en) * 1994-08-23 1997-06-03 General Electric Co. Turbine stator vane segments having combined air and steam cooling circuits
US5741117A (en) * 1996-10-22 1998-04-21 United Technologies Corporation Method for cooling a gas turbine stator vane
US5902093A (en) * 1997-08-22 1999-05-11 General Electric Company Crack arresting rotor blade
WO1999054597A1 (de) * 1998-04-21 1999-10-28 Siemens Aktiengesellschaft Turbinenschaufel
RU2151303C1 (ru) * 1996-03-14 2000-06-20 АББ Унитурбо Лтд. Охлаждаемая рабочая или сопловая лопатка газовой турбины
DE19810339C2 (de) * 1997-03-11 2000-07-13 Mitsubishi Heavy Ind Ltd Gekühlte stationäre Gasturbinenschaufel
EP1099825A1 (de) * 1999-11-12 2001-05-16 Siemens Aktiengesellschaft Turbinenschaufel und Verfahren zur Herstellung einer Turbinenschaufel
US6343911B1 (en) * 2000-04-05 2002-02-05 General Electric Company Side wall cooling for nozzle segments for a gas turbine
US6375415B1 (en) * 2000-04-25 2002-04-23 General Electric Company Hook support for a closed circuit fluid cooled gas turbine nozzle stage segment
US6386825B1 (en) * 2000-04-11 2002-05-14 General Electric Company Apparatus and methods for impingement cooling of a side wall of a turbine nozzle segment
US6419445B1 (en) * 2000-04-11 2002-07-16 General Electric Company Apparatus for impingement cooling a side wall adjacent an undercut region of a turbine nozzle segment
US6454526B1 (en) * 2000-09-28 2002-09-24 Siemens Westinghouse Power Corporation Cooled turbine vane with endcaps
US6508620B2 (en) * 2001-05-17 2003-01-21 Pratt & Whitney Canada Corp. Inner platform impingement cooling by supply air from outside
US6527514B2 (en) 2001-06-11 2003-03-04 Alstom (Switzerland) Ltd Turbine blade with rub tolerant cooling construction
EP1318274A1 (fr) * 2001-12-10 2003-06-11 Snecma Moteurs Aube de turbine haute-pression ayant un bord de fuite refroidi
EP1149982A3 (en) * 2000-04-11 2004-05-26 General Electric Company A method of joining a vane cavity insert to a nozzle segment of a gas turbine
US20040139746A1 (en) * 2003-01-22 2004-07-22 Mitsubishi Heavy Industries Ltd. Gas turbine tail tube seal and gas turbine using the same
EP1267040A3 (de) * 2001-06-11 2004-10-13 ALSTOM Technology Ltd Gasturbinenschaufelblatt
US20050013686A1 (en) * 2003-07-14 2005-01-20 Siemens Westinghouse Power Corporation Turbine vane plate assembly
US20050089393A1 (en) * 2003-10-22 2005-04-28 Zatorski Darek T. Split flow turbine nozzle
US6887040B2 (en) 2001-09-12 2005-05-03 Siemens Aktiengesellschaft Turbine blade/vane
US20050123388A1 (en) * 2003-12-04 2005-06-09 Brian Chan Sze B. Method and apparatus for convective cooling of side-walls of turbine nozzle segments
EP1571295A1 (de) * 2004-03-01 2005-09-07 ALSTOM Technology Ltd Gekühlte Strömungsmaschinenschaufel und Verfahren zur Kühlung
RU2268370C2 (ru) * 2000-06-27 2006-01-20 Дженерал Электрик Компани Сопло турбины, способ его изготовления и лопатка сопла
US20060034690A1 (en) * 2004-08-10 2006-02-16 Papple Michael Leslie C Internally cooled gas turbine airfoil and method
US20060045745A1 (en) * 2004-08-24 2006-03-02 Pratt & Whitney Canada Corp. Vane attachment arrangement
RU2276732C2 (ru) * 2004-01-16 2006-05-20 Ульяновский государственный технический университет Охлаждаемая лопатка турбины
US20060153679A1 (en) * 2005-01-07 2006-07-13 Siemens Westinghouse Power Corporation Cooling system including mini channels within a turbine blade of a turbine engine
CH695702A5 (de) * 2002-01-15 2006-07-31 Alstom Technology Ltd Gasturbinenschaufelblatt.
WO2006108764A1 (de) * 2005-04-14 2006-10-19 Alstom Technology Ltd Konvektiv gekühlte gasturbinenschaufel
CN100347411C (zh) * 2003-02-27 2007-11-07 通用电气公司 具有单岔开腔的中空叶片的燃气涡轮发动机涡轮喷嘴弧段
US20090003987A1 (en) * 2006-12-21 2009-01-01 Jack Raul Zausner Airfoil with improved cooling slot arrangement
US20110008177A1 (en) * 2009-05-19 2011-01-13 Alstom Technology Ltd Gas turbine vane with improved cooling
US20110081237A1 (en) * 2009-10-01 2011-04-07 Pratt & Whitney Canada Corp. Sealing for vane segments
US20110268562A1 (en) * 2010-04-30 2011-11-03 General Electric Company Gas turbine engine airfoil integrated heat exchanger
US20120082548A1 (en) * 2010-09-30 2012-04-05 General Electric Company Apparatus and methods for cooling platform regions of turbine rotor blades
US20120082549A1 (en) * 2010-09-30 2012-04-05 General Electric Company Apparatus and methods for cooling platform regions of turbine rotor blades
US20130251508A1 (en) * 2012-03-21 2013-09-26 Marc Tardif Dual-use of cooling air for turbine vane and method
EP2628903A3 (en) * 2011-12-15 2013-11-13 United Technologies Corporation Gas Turbine Engine Airfoil Cooling Circuit
WO2014009074A1 (de) * 2012-07-12 2014-01-16 Siemens Aktiengesellschaft Turbinenschaufel für eine gasturbine
US9359902B2 (en) 2013-06-28 2016-06-07 Siemens Energy, Inc. Turbine airfoil with ambient cooling system
US20160341047A1 (en) * 2014-01-30 2016-11-24 General Electric Technology Gmbh Gas turbine component
US20170234142A1 (en) * 2016-02-17 2017-08-17 General Electric Company Rotor Blade Trailing Edge Cooling
US20170306765A1 (en) * 2016-04-25 2017-10-26 General Electric Company Airfoil with variable slot decoupling
US20180171810A1 (en) * 2016-12-20 2018-06-21 Doosan Heavy Industries & Construction Co., Ltd Gas turbine
EP3597857A1 (en) * 2018-07-20 2020-01-22 United Technologies Corporation Airfoil having angled trailing edge slots
EP3650641A1 (en) * 2018-11-09 2020-05-13 United Technologies Corporation Airfoil with cooling passage circuit through platforms and airfoil section
EP3862537A1 (en) 2020-02-10 2021-08-11 General Electric Company Polska sp. z o.o. Cooled turbine nozzle and nozzle segment
CN115075891A (zh) * 2022-05-29 2022-09-20 中国船舶重工集团公司第七0三研究所 一种压力侧排气的气冷涡轮导叶尾缘结构
EP4198269A1 (en) * 2021-12-10 2023-06-21 Rolls-Royce plc Vane assembly for a gas turbine engine
US20250075624A1 (en) * 2023-09-06 2025-03-06 Siemens Energy Global GmbH & Co. KG Turbine component for gas turbine engine

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2163218B (en) * 1981-07-07 1986-07-16 Rolls Royce Cooled vane or blade for a gas turbine engine
FR2678318B1 (fr) * 1991-06-25 1993-09-10 Snecma Aube refroidie de distributeur de turbine.
GB2345942B (en) * 1998-12-24 2002-08-07 Rolls Royce Plc Gas turbine engine internal air system
GB2366600A (en) * 2000-09-09 2002-03-13 Rolls Royce Plc Cooling arrangement for trailing edge of aerofoil
RU2188323C1 (ru) * 2001-02-21 2002-08-27 "МАТИ" - Российский государственный технологический университет им. К.Э.Циолковского Охлаждаемая лопатка газовой турбины
RU2208683C1 (ru) * 2002-01-08 2003-07-20 Ульяновский государственный технический университет Охлаждаемая лопатка турбины
GB0813839D0 (en) 2008-07-30 2008-09-03 Rolls Royce Plc An aerofoil and method for making an aerofoil
RU2439336C1 (ru) * 2010-05-11 2012-01-10 Открытое акционерное общество "Авиадвигатель" Охлаждаемая лопатка турбомашины
US9771816B2 (en) * 2014-05-07 2017-09-26 General Electric Company Blade cooling circuit feed duct, exhaust duct, and related cooling structure

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3017159A (en) * 1956-11-23 1962-01-16 Curtiss Wright Corp Hollow blade construction
US3533711A (en) * 1966-02-26 1970-10-13 Gen Electric Cooled vane structure for high temperature turbines
US3623825A (en) * 1969-11-13 1971-11-30 Avco Corp Liquid-metal-filled rotor blade

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3017159A (en) * 1956-11-23 1962-01-16 Curtiss Wright Corp Hollow blade construction
US3533711A (en) * 1966-02-26 1970-10-13 Gen Electric Cooled vane structure for high temperature turbines
US3623825A (en) * 1969-11-13 1971-11-30 Avco Corp Liquid-metal-filled rotor blade

Cited By (105)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3989412A (en) * 1974-07-17 1976-11-02 Brown Boveri-Sulzer Turbomachinery, Ltd. Cooled rotor blade for a gas turbine
US4019831A (en) * 1974-09-05 1977-04-26 Brown Boveri Sulzer Turbomachinery Ltd. Cooled rotor blade for a gas turbine
FR2326570A1 (fr) * 1975-10-03 1977-04-29 United Technologies Corp Aube de turbine refroidie par air
US4025226A (en) * 1975-10-03 1977-05-24 United Technologies Corporation Air cooled turbine vane
US4236870A (en) * 1977-12-27 1980-12-02 United Technologies Corporation Turbine blade
US4278400A (en) * 1978-09-05 1981-07-14 United Technologies Corporation Coolable rotor blade
US4293275A (en) * 1978-09-14 1981-10-06 Hitachi, Ltd. Gas turbine blade cooling structure
US4303374A (en) * 1978-12-15 1981-12-01 General Electric Company Film cooled airfoil body
US4330235A (en) * 1979-02-28 1982-05-18 Tokyo Shibaura Denki Kabushiki Kaisha Cooling apparatus for gas turbine blades
US4462754A (en) * 1981-06-30 1984-07-31 Rolls Royce Limited Turbine blade for gas turbine engine
US4474532A (en) * 1981-12-28 1984-10-02 United Technologies Corporation Coolable airfoil for a rotary machine
US4767268A (en) * 1987-08-06 1988-08-30 United Technologies Corporation Triple pass cooled airfoil
US4753575A (en) * 1987-08-06 1988-06-28 United Technologies Corporation Airfoil with nested cooling channels
WO1989001564A1 (en) * 1987-08-06 1989-02-23 United Technologies Corporation Airfoil with nested cooling channels
US5030060A (en) * 1988-10-20 1991-07-09 The United States Of America As Represented By The Secretary Of The Air Force Method and apparatus for cooling high temperature ceramic turbine blade portions
US5217347A (en) * 1991-09-05 1993-06-08 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) Mounting system for a stator vane
US5591002A (en) * 1994-08-23 1997-01-07 General Electric Co. Closed or open air cooling circuits for nozzle segments with wheelspace purge
US5634766A (en) * 1994-08-23 1997-06-03 General Electric Co. Turbine stator vane segments having combined air and steam cooling circuits
US5743708A (en) * 1994-08-23 1998-04-28 General Electric Co. Turbine stator vane segments having combined air and steam cooling circuits
US5503529A (en) * 1994-12-08 1996-04-02 General Electric Company Turbine blade having angled ejection slot
US5536143A (en) * 1995-03-31 1996-07-16 General Electric Co. Closed circuit steam cooled bucket
RU2151303C1 (ru) * 1996-03-14 2000-06-20 АББ Унитурбо Лтд. Охлаждаемая рабочая или сопловая лопатка газовой турбины
US5741117A (en) * 1996-10-22 1998-04-21 United Technologies Corporation Method for cooling a gas turbine stator vane
DE19810339C2 (de) * 1997-03-11 2000-07-13 Mitsubishi Heavy Ind Ltd Gekühlte stationäre Gasturbinenschaufel
US5902093A (en) * 1997-08-22 1999-05-11 General Electric Company Crack arresting rotor blade
US6533544B1 (en) 1998-04-21 2003-03-18 Siemens Aktiengesellschaft Turbine blade
WO1999054597A1 (de) * 1998-04-21 1999-10-28 Siemens Aktiengesellschaft Turbinenschaufel
EP1099825A1 (de) * 1999-11-12 2001-05-16 Siemens Aktiengesellschaft Turbinenschaufel und Verfahren zur Herstellung einer Turbinenschaufel
US6631561B1 (en) * 1999-11-12 2003-10-14 Siemens Aktiengesellschaft Turbine blade and method for producing a turbine blade
WO2001036790A1 (de) * 1999-11-12 2001-05-25 Siemens Aktiengesellschaft Turbinenschaufel und verfahren zur herstellung einer turbinenschaufel
CN1312381C (zh) * 1999-11-12 2007-04-25 西门子公司 透平叶片和制造透平叶片的方法
US6343911B1 (en) * 2000-04-05 2002-02-05 General Electric Company Side wall cooling for nozzle segments for a gas turbine
US6386825B1 (en) * 2000-04-11 2002-05-14 General Electric Company Apparatus and methods for impingement cooling of a side wall of a turbine nozzle segment
US6419445B1 (en) * 2000-04-11 2002-07-16 General Electric Company Apparatus for impingement cooling a side wall adjacent an undercut region of a turbine nozzle segment
EP1149982A3 (en) * 2000-04-11 2004-05-26 General Electric Company A method of joining a vane cavity insert to a nozzle segment of a gas turbine
US6375415B1 (en) * 2000-04-25 2002-04-23 General Electric Company Hook support for a closed circuit fluid cooled gas turbine nozzle stage segment
RU2268370C2 (ru) * 2000-06-27 2006-01-20 Дженерал Электрик Компани Сопло турбины, способ его изготовления и лопатка сопла
US6454526B1 (en) * 2000-09-28 2002-09-24 Siemens Westinghouse Power Corporation Cooled turbine vane with endcaps
US6508620B2 (en) * 2001-05-17 2003-01-21 Pratt & Whitney Canada Corp. Inner platform impingement cooling by supply air from outside
US6527514B2 (en) 2001-06-11 2003-03-04 Alstom (Switzerland) Ltd Turbine blade with rub tolerant cooling construction
EP1267040A3 (de) * 2001-06-11 2004-10-13 ALSTOM Technology Ltd Gasturbinenschaufelblatt
US6887040B2 (en) 2001-09-12 2005-05-03 Siemens Aktiengesellschaft Turbine blade/vane
FR2833298A1 (fr) * 2001-12-10 2003-06-13 Snecma Moteurs Perfectionnements apportes au comportement thermique du bord de fuite d'une aube de turbine haute-pression
US6830431B2 (en) 2001-12-10 2004-12-14 Snecma Moteurs High-temperature behavior of the trailing edge of a high pressure turbine blade
US20030108425A1 (en) * 2001-12-10 2003-06-12 Snecma Moteurs High-temperature behavior of the trailing edge of a high pressure turbine blade
EP1318274A1 (fr) * 2001-12-10 2003-06-11 Snecma Moteurs Aube de turbine haute-pression ayant un bord de fuite refroidi
CH695702A5 (de) * 2002-01-15 2006-07-31 Alstom Technology Ltd Gasturbinenschaufelblatt.
US20040139746A1 (en) * 2003-01-22 2004-07-22 Mitsubishi Heavy Industries Ltd. Gas turbine tail tube seal and gas turbine using the same
DE102004002888A1 (de) * 2003-01-22 2004-08-12 Mitsubishi Heavy Industries, Ltd. Gasturbinen-Endrohrdichtung und diese verwendende Gasturbine
US6860108B2 (en) 2003-01-22 2005-03-01 Mitsubishi Heavy Industries, Ltd. Gas turbine tail tube seal and gas turbine using the same
DE102004002888B4 (de) * 2003-01-22 2006-03-02 Mitsubishi Heavy Industries, Ltd. Gasturbinen-Endrohrdichtungsanordnung
CN100347411C (zh) * 2003-02-27 2007-11-07 通用电气公司 具有单岔开腔的中空叶片的燃气涡轮发动机涡轮喷嘴弧段
US6984101B2 (en) 2003-07-14 2006-01-10 Siemens Westinghouse Power Corporation Turbine vane plate assembly
US20050013686A1 (en) * 2003-07-14 2005-01-20 Siemens Westinghouse Power Corporation Turbine vane plate assembly
US6929445B2 (en) 2003-10-22 2005-08-16 General Electric Company Split flow turbine nozzle
US20050089393A1 (en) * 2003-10-22 2005-04-28 Zatorski Darek T. Split flow turbine nozzle
US20050123388A1 (en) * 2003-12-04 2005-06-09 Brian Chan Sze B. Method and apparatus for convective cooling of side-walls of turbine nozzle segments
US7029228B2 (en) 2003-12-04 2006-04-18 General Electric Company Method and apparatus for convective cooling of side-walls of turbine nozzle segments
RU2276732C2 (ru) * 2004-01-16 2006-05-20 Ульяновский государственный технический университет Охлаждаемая лопатка турбины
EP1571295A1 (de) * 2004-03-01 2005-09-07 ALSTOM Technology Ltd Gekühlte Strömungsmaschinenschaufel und Verfahren zur Kühlung
US20060034690A1 (en) * 2004-08-10 2006-02-16 Papple Michael Leslie C Internally cooled gas turbine airfoil and method
US7210906B2 (en) 2004-08-10 2007-05-01 Pratt & Whitney Canada Corp. Internally cooled gas turbine airfoil and method
US20060045745A1 (en) * 2004-08-24 2006-03-02 Pratt & Whitney Canada Corp. Vane attachment arrangement
US7238003B2 (en) 2004-08-24 2007-07-03 Pratt & Whitney Canada Corp. Vane attachment arrangement
US20060153679A1 (en) * 2005-01-07 2006-07-13 Siemens Westinghouse Power Corporation Cooling system including mini channels within a turbine blade of a turbine engine
US7189060B2 (en) * 2005-01-07 2007-03-13 Siemens Power Generation, Inc. Cooling system including mini channels within a turbine blade of a turbine engine
US20080181784A1 (en) * 2005-04-14 2008-07-31 Alstom Technology Ltd Convectively cooled gas turbine blade
WO2006108764A1 (de) * 2005-04-14 2006-10-19 Alstom Technology Ltd Konvektiv gekühlte gasturbinenschaufel
US7766619B2 (en) 2005-04-14 2010-08-03 Alstom Technology Ltd Convectively cooled gas turbine blade
US20090003987A1 (en) * 2006-12-21 2009-01-01 Jack Raul Zausner Airfoil with improved cooling slot arrangement
US20110008177A1 (en) * 2009-05-19 2011-01-13 Alstom Technology Ltd Gas turbine vane with improved cooling
US8920110B2 (en) 2009-05-19 2014-12-30 Alstom Technology Ltd. Gas turbine vane with improved cooling
US20110081237A1 (en) * 2009-10-01 2011-04-07 Pratt & Whitney Canada Corp. Sealing for vane segments
US8500392B2 (en) * 2009-10-01 2013-08-06 Pratt & Whitney Canada Corp. Sealing for vane segments
US20110268562A1 (en) * 2010-04-30 2011-11-03 General Electric Company Gas turbine engine airfoil integrated heat exchanger
US8616834B2 (en) * 2010-04-30 2013-12-31 General Electric Company Gas turbine engine airfoil integrated heat exchanger
US8777568B2 (en) * 2010-09-30 2014-07-15 General Electric Company Apparatus and methods for cooling platform regions of turbine rotor blades
US20120082549A1 (en) * 2010-09-30 2012-04-05 General Electric Company Apparatus and methods for cooling platform regions of turbine rotor blades
US20120082548A1 (en) * 2010-09-30 2012-04-05 General Electric Company Apparatus and methods for cooling platform regions of turbine rotor blades
US8840369B2 (en) * 2010-09-30 2014-09-23 General Electric Company Apparatus and methods for cooling platform regions of turbine rotor blades
US9145780B2 (en) 2011-12-15 2015-09-29 United Technologies Corporation Gas turbine engine airfoil cooling circuit
US10612388B2 (en) 2011-12-15 2020-04-07 United Technologies Corporation Gas turbine engine airfoil cooling circuit
EP2628903A3 (en) * 2011-12-15 2013-11-13 United Technologies Corporation Gas Turbine Engine Airfoil Cooling Circuit
US20130251508A1 (en) * 2012-03-21 2013-09-26 Marc Tardif Dual-use of cooling air for turbine vane and method
US9151164B2 (en) * 2012-03-21 2015-10-06 Pratt & Whitney Canada Corp. Dual-use of cooling air for turbine vane and method
WO2014009074A1 (de) * 2012-07-12 2014-01-16 Siemens Aktiengesellschaft Turbinenschaufel für eine gasturbine
US9359902B2 (en) 2013-06-28 2016-06-07 Siemens Energy, Inc. Turbine airfoil with ambient cooling system
US20160341047A1 (en) * 2014-01-30 2016-11-24 General Electric Technology Gmbh Gas turbine component
US10883372B2 (en) * 2014-01-30 2021-01-05 General Electric Technology Gmbh Gas turbine component
US20170234142A1 (en) * 2016-02-17 2017-08-17 General Electric Company Rotor Blade Trailing Edge Cooling
US20170306765A1 (en) * 2016-04-25 2017-10-26 General Electric Company Airfoil with variable slot decoupling
US10156146B2 (en) * 2016-04-25 2018-12-18 General Electric Company Airfoil with variable slot decoupling
US10502078B2 (en) * 2016-12-20 2019-12-10 Doosan Heavy Industries Construction Co., Ltd. Gas turbine
US20180171810A1 (en) * 2016-12-20 2018-06-21 Doosan Heavy Industries & Construction Co., Ltd Gas turbine
EP3597857A1 (en) * 2018-07-20 2020-01-22 United Technologies Corporation Airfoil having angled trailing edge slots
EP3650641A1 (en) * 2018-11-09 2020-05-13 United Technologies Corporation Airfoil with cooling passage circuit through platforms and airfoil section
US11028700B2 (en) 2018-11-09 2021-06-08 Raytheon Technologies Corporation Airfoil with cooling passage circuit through platforms and airfoil section
EP3862537A1 (en) 2020-02-10 2021-08-11 General Electric Company Polska sp. z o.o. Cooled turbine nozzle and nozzle segment
US11346248B2 (en) * 2020-02-10 2022-05-31 General Electric Company Polska Sp. Z O.O. Turbine nozzle segment and a turbine nozzle comprising such a turbine nozzle segment
EP4198269A1 (en) * 2021-12-10 2023-06-21 Rolls-Royce plc Vane assembly for a gas turbine engine
US12129794B2 (en) 2021-12-10 2024-10-29 Rolls-Royce Plc Vane assembly for a gas turbine engine
CN115075891A (zh) * 2022-05-29 2022-09-20 中国船舶重工集团公司第七0三研究所 一种压力侧排气的气冷涡轮导叶尾缘结构
US20250075624A1 (en) * 2023-09-06 2025-03-06 Siemens Energy Global GmbH & Co. KG Turbine component for gas turbine engine
EP4520921A1 (en) * 2023-09-06 2025-03-12 Siemens Energy Global GmbH & Co. KG Turbine component for gas turbine engine
GB2633337A (en) * 2023-09-06 2025-03-12 Siemens Energy Global Gmbh & Co Kg Turbine component for gas turbine engine

Also Published As

Publication number Publication date
BE794195A (fr) 1973-07-18
JPS4882210A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1973-11-02
IT978243B (it) 1974-09-20
DE2202858B1 (de) 1973-07-26
FR2168802A5 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1973-08-31
JPS5145726B2 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1976-12-04
SE381311B (sv) 1975-12-01
GB1359983A (en) 1974-07-17
NL7300634A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1973-07-20
DE2202858C2 (de) 1974-02-28
NL164358C (nl) 1980-12-15
NL164358B (nl) 1980-07-15
CH547431A (de) 1974-03-29
CA967095A (en) 1975-05-06

Similar Documents

Publication Publication Date Title
US3807892A (en) Cooled guide blade for a gas turbine
US3782852A (en) Gas turbine engine blades
US3885609A (en) Cooled rotor blade for a gas turbine
US4183716A (en) Air-cooled turbine blade
US3574481A (en) Variable area cooled airfoil construction for gas turbines
US4601638A (en) Airfoil trailing edge cooling arrangement
US4056332A (en) Cooled turbine blade
US3635585A (en) Gas-cooled turbine blade
US4021139A (en) Gas turbine guide vane
US3540810A (en) Slanted partition for hollow airfoil vane insert
US4297077A (en) Cooled turbine vane
US8262355B2 (en) Cooled component
US3051439A (en) Blades for gas turbine engines
US3572031A (en) Variable area cooling passages for gas turbine burners
US3799696A (en) Cooled vane or blade for a gas turbine engine
US4859147A (en) Cooled gas turbine blade
US5954475A (en) Gas turbine stationary blade
EP0753097B1 (en) Turbine vane with a platform cavity having a double feed for cooling fluid
US8870537B2 (en) Near-wall serpentine cooled turbine airfoil
JP2001107705A (ja) 冷却回路及び冷却可能な壁
JP2001107704A (ja) 冷却可能なエアフォイル及び冷却回路及び壁の冷却方法
JP2000038901A (ja) 中空状エアロフォイル
JPH0610704A (ja) エアホイル装置
US20170002685A1 (en) Guide vane of a gas turbine engine, in particular of an aircraft engine
GB834811A (en) Cooled hollow turbine blades

Legal Events

Date Code Title Description
AS Assignment

Owner name: ABB STAL AB, FINSPANG, SWEDEN, A CORP. OF SWEDEN

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:BROWN BOVERI-SULZER TURBOMACHINERY LTD., A CORP. OF SWITZERLAND;REEL/FRAME:005186/0295

Effective date: 19890913