GB1442860A - Stator vane construction - Google Patents

Stator vane construction

Info

Publication number
GB1442860A
GB1442860A GB1075174A GB1075174A GB1442860A GB 1442860 A GB1442860 A GB 1442860A GB 1075174 A GB1075174 A GB 1075174A GB 1075174 A GB1075174 A GB 1075174A GB 1442860 A GB1442860 A GB 1442860A
Authority
GB
United Kingdom
Prior art keywords
vane
slot
march
slots
metal
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
Application number
GB1075174A
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.)
Raytheon Technologies Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB1442860A publication Critical patent/GB1442860A/en
Expired legal-status Critical Current

Links

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
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1442860 Stator vane fixing UNITED AIRCRAFT CORP 11 March 1974 [28 March 1973] 10751/74 Heading FIT Mounting of stator vanes 12, e.g. for a compressor in a turbine power-plant, is effected in slots 26 in a casing or shroud ring by means of a metal strip 30 formed with stamped out projections 32 compressed between the slot side wall and the side of the vane end portion in the slot. As shown, a rigid metal member 28 is applied also to both sides of the vane end portion. A metal sheath (18), Fig. 1 (not shown), may be applied to the leading edge of a blade made from aluminium or boron epoxy. Bosses (24) may be provided surrounding the slots 26 and to which the vanes and metal strips are riveted. Opposite ends of the vane may be similarly fixed, or one end by a simple tang (16) and slot (40).
GB1075174A 1973-03-28 1974-03-11 Stator vane construction Expired GB1442860A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US00345808A US3836282A (en) 1973-03-28 1973-03-28 Stator vane support and construction thereof

Publications (1)

Publication Number Publication Date
GB1442860A true GB1442860A (en) 1976-07-14

Family

ID=23356570

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1075174A Expired GB1442860A (en) 1973-03-28 1974-03-11 Stator vane construction

Country Status (7)

Country Link
US (1) US3836282A (en)
CA (1) CA987237A (en)
DE (1) DE2407960A1 (en)
FR (1) FR2223551A1 (en)
GB (1) GB1442860A (en)
IT (1) IT1010995B (en)
SE (1) SE390189B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2220034A (en) * 1988-06-22 1989-12-28 Rolls Royce Plc Load transmission in gas turbine engines

Families Citing this family (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3966353A (en) * 1975-02-21 1976-06-29 Westinghouse Electric Corporation Ceramic-to-metal (or ceramic) cushion/seal for use with three piece ceramic stationary vane assembly
US4452564A (en) * 1981-11-09 1984-06-05 The Garrett Corporation Stator vane assembly and associated methods
GB2115883B (en) * 1982-02-26 1986-04-30 Gen Electric Turbomachine airfoil mounting assembly
CH660403A5 (en) * 1983-08-30 1987-04-15 Bbc Brown Boveri & Cie AXIAL SWIRL FOR GENERATING TURNING FLOWS.
FR2606071B1 (en) * 1986-10-29 1990-11-30 Snecma STATOR STAGE AND TURBOMACHINE COMPRESSOR COMPRISING THE SAME
US5174715A (en) * 1990-12-13 1992-12-29 General Electric Company Turbine nozzle
FR2671140B1 (en) * 1990-12-27 1995-01-13 Snecma RECTIFIER BLADE FOR TURBOMACHINE COMPRESSOR.
US5180282A (en) * 1991-09-27 1993-01-19 General Electric Company Gas turbine engine structural frame with multi-yoke attachment of struts to outer casing
US5292227A (en) * 1992-12-10 1994-03-08 General Electric Company Turbine frame
US5474419A (en) * 1992-12-30 1995-12-12 Reluzco; George Flowpath assembly for a turbine diaphragm and methods of manufacture
US5332360A (en) * 1993-09-08 1994-07-26 General Electric Company Stator vane having reinforced braze joint
US5411368A (en) * 1993-11-08 1995-05-02 Allied-Signal Inc. Ceramic-to-metal stator vane assembly with braze
US5704762A (en) * 1993-11-08 1998-01-06 Alliedsignal Inc. Ceramic-to-metal stator vane assembly
US5438756A (en) * 1993-12-17 1995-08-08 General Electric Company Method for assembling a turbine frame assembly
US5494404A (en) * 1993-12-22 1996-02-27 Alliedsignal Inc. Insertable stator vane assembly
US5586864A (en) * 1994-07-27 1996-12-24 General Electric Company Turbine nozzle diaphragm and method of assembly
US6000906A (en) * 1997-09-12 1999-12-14 Alliedsignal Inc. Ceramic airfoil
US6409472B1 (en) 1999-08-09 2002-06-25 United Technologies Corporation Stator assembly for a rotary machine and clip member for a stator assembly
US6439841B1 (en) * 2000-04-29 2002-08-27 General Electric Company Turbine frame assembly
WO2002006636A1 (en) * 2000-07-19 2002-01-24 Honeywell Garrett Sa Sliding vane turbocharger with graduated vanes
DE102006050907A1 (en) * 2006-10-28 2008-05-15 Man Turbo Ag Guide device of a turbomachine and vane for such a guide device
US8210819B2 (en) * 2008-02-22 2012-07-03 Siemens Energy, Inc. Airfoil structure shim
US8292580B2 (en) * 2008-09-18 2012-10-23 Siemens Energy, Inc. CMC vane assembly apparatus and method
US8469661B2 (en) * 2009-10-01 2013-06-25 Pratt & Whitney Canada Corp. Fabricated gas turbine vane ring
GB201015862D0 (en) * 2010-09-22 2010-10-27 Rolls Royce Plc A damped assembly
US8966756B2 (en) * 2011-01-20 2015-03-03 United Technologies Corporation Gas turbine engine stator vane assembly
US9951639B2 (en) * 2012-02-10 2018-04-24 Pratt & Whitney Canada Corp. Vane assemblies for gas turbine engines
WO2014137468A1 (en) * 2013-03-07 2014-09-12 Rolls-Royce Canada, Ltd. Gas turbine engine comprising an outboard insertion system of vanes and corresponding assembling method
US9840929B2 (en) * 2013-05-28 2017-12-12 Pratt & Whitney Canada Corp. Gas turbine engine vane assembly and method of mounting same
BE1022513B1 (en) * 2014-11-18 2016-05-19 Techspace Aero S.A. INTERNAL COMPRESSOR OF AXIAL TURBOMACHINE COMPRESSOR
US10378383B2 (en) * 2017-01-26 2019-08-13 General Electric Company Alignment apparatus for coupling diaphragms of turbines
US10392945B2 (en) * 2017-05-19 2019-08-27 General Electric Company Turbomachine cooling system
US10612386B2 (en) * 2017-07-17 2020-04-07 Rolls-Royce Corporation Apparatus for airfoil leading edge protection
CN111406146B (en) * 2017-12-01 2023-03-14 西门子能源美国公司 Brazed-in heat transfer features for cooled turbine components
US11286798B2 (en) * 2019-08-20 2022-03-29 Rolls-Royce Corporation Airfoil assembly with ceramic matrix composite parts and load-transfer features
CN114278391B (en) * 2021-12-29 2024-04-19 河北国源电气股份有限公司 Stator blade group for turbine with tight fit installation

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1025421B (en) * 1955-10-31 1958-03-06 Maschf Augsburg Nuernberg Ag Fastening of blades made of sproated material in a metallic blade carrier
US2914300A (en) * 1955-12-22 1959-11-24 Gen Electric Nozzle vane support for turbines
GB995228A (en) * 1964-05-08 1965-06-16 Rolls Royce Bladed structure, for example, for a gas turbine engine compressor
FR2073239A1 (en) * 1969-12-01 1971-10-01 Snecma

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2220034A (en) * 1988-06-22 1989-12-28 Rolls Royce Plc Load transmission in gas turbine engines
US4984423A (en) * 1988-06-22 1991-01-15 Rolls-Royce Plc Aerodynamic loading in gas turbine engines
GB2220034B (en) * 1988-06-22 1992-12-02 Rolls Royce Plc Aerodynamic loading in gas turbine engines

Also Published As

Publication number Publication date
CA987237A (en) 1976-04-13
DE2407960A1 (en) 1974-10-10
SE390189B (en) 1976-12-06
FR2223551A1 (en) 1974-10-25
US3836282A (en) 1974-09-17
IT1010995B (en) 1977-01-20

Similar Documents

Publication Publication Date Title
GB1442860A (en) Stator vane construction
GB1518076A (en) Ceramic rotor blade assembly for a gas turbine engine
GB1287223A (en) Improvements in or relating to turbine blading
IL65894A0 (en) Vane type compressor having elliptical stator with doubly-offset rotor
GB1512882A (en) Bladed rotor assembly for a gas turbine engine
GB1506096A (en) Air cooled turbine vane
GB2050524B (en) Turbine stator shroud assembly
GB2043798B (en) Gas turbine stator vane assembly
GB1465282A (en) Leakage control structure
GB2060077B (en) Arrangement for controlling the clearance between turbine rotor blades and a stator shroud ring
JPS5327714A (en) Gas turbine rotor blade
JPS55123302A (en) Gas turbine engine blade rotor
GB1507156A (en) Stators for multistage axial flow compressors
GB1491557A (en) Turbomachinery blade assembly
JPS53125518A (en) Cooling type rotor blade for gas turbine engine
GB1491556A (en) Rotor blades for turbomachines
IT1099249B (en) COOLED ROTOR BLADE FOR A GAS TURBO ENGINE
GB1187227A (en) Improvements in Bladed Rotors for Axial Flow Compressors, Turbines and the like
GB2105415B (en) Air-cooled turbine rotor blade with trailing edge recessed holes
GB1353114A (en) Turbo-machinery
JPS52118117A (en) Rotor blade for gas turbine engine
GB902064A (en) Blade damping means for compressors and turbines
GB1087629A (en) Rotor blade mounting
IL51704A (en) Taorsionally compliant helicopter rotor blade with improved stability and performance characteristics
GB1215623A (en) A method of making a torque converter and converters obtained by this method

Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee