[go: up one dir, main page]

GB926947A - Improvements relating to gas turbine engine casings - Google Patents

Improvements relating to gas turbine engine casings

Info

Publication number
GB926947A
GB926947A GB42402/61A GB4240261A GB926947A GB 926947 A GB926947 A GB 926947A GB 42402/61 A GB42402/61 A GB 42402/61A GB 4240261 A GB4240261 A GB 4240261A GB 926947 A GB926947 A GB 926947A
Authority
GB
United Kingdom
Prior art keywords
butt welded
sheet metal
shaft
walls
annular
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
GB42402/61A
Inventor
Jack Palfreyman
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB42402/61A priority Critical patent/GB926947A/en
Publication of GB926947A publication Critical patent/GB926947A/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • 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
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

926,947. Gas turbine plant; axial-flow compressors. ROLLS-ROYCE Ltd. Nov. 27, 1961, No. 42402/61. Classes 110 (1) and 110 (3). A gas turbine engine casing portion has inner and outer walls between which extend a number of angularly spaced apart vanes, which casing portion is fabricated solely from sheet metal parts and extruded metal parts. A casing 17, Fig. 2, formed wholly of titanium alloy and placed between high and low pressure compressors of a gas turbine engine, has redially inner and outer annular walls 20, 21 formed of sheet metal strips bent into circular form and butt welded at their ends. These walls are each . provided with two extruded metal annular strengthening ribs 24, 25 or 26, 27, butt welded to the walls. Each of the ribs 26, 27 may be formed of two concentric extruded metal parts 30, 31, Fig. 4, welded to a rolled sheet metal part. 32. Extruded metal flanges 33-36, butt welded to their respective wall 20 or 21, are bolted to flanges 40-43 of adjacent parts of the engine casing. The flanges 35, 36 are butt welded to annular sheet metal members 44, 45 which are lap welded to the ribs 26, 27. Annular sheet metal strips 20a and 21a form part of the inner and outer walls of a main fluid duct 22, the inner and outer walls of a main fluid strips being supported by flanges 40, 41 and 42, 43 respectively. A number of angularly spaced hollow vanes 23 fabricated from sheet metal members butt welded together, extend between the walls 20, 21. Annular members 47, 48 are butt welded to flanges 33, 34 and to an annular member 50 which supports a bearing 51 for the low pressure compressor shaft 52 splined to a low pressure turbine shaft 53. The member 50 also supports a bearing 54 for a shaft 55 which is splined to the high pressure compressor and turbine shaft 56 and geared at 58 to a shaft 57 splined to a shaft 60. The latter passes through holes 61 in one of the vanes 23 to drive auxiliary equipment through a gear-box 63. The ribs 26, 27 are butt welded to extruded metal engine trunnion mountings (not shown).
GB42402/61A 1961-11-27 1961-11-27 Improvements relating to gas turbine engine casings Expired GB926947A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB42402/61A GB926947A (en) 1961-11-27 1961-11-27 Improvements relating to gas turbine engine casings

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB42402/61A GB926947A (en) 1961-11-27 1961-11-27 Improvements relating to gas turbine engine casings

Publications (1)

Publication Number Publication Date
GB926947A true GB926947A (en) 1963-05-22

Family

ID=10424251

Family Applications (1)

Application Number Title Priority Date Filing Date
GB42402/61A Expired GB926947A (en) 1961-11-27 1961-11-27 Improvements relating to gas turbine engine casings

Country Status (1)

Country Link
GB (1) GB926947A (en)

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0147351A1 (en) * 1983-12-05 1985-07-03 United Technologies Corporation Bearing support structure
EP0392401A1 (en) * 1989-04-10 1990-10-17 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Flow control device for fanjet/ramjet engine
US5160251A (en) * 1991-05-13 1992-11-03 General Electric Company Lightweight engine turbine bearing support assembly for withstanding radial and axial loads
US5161940A (en) * 1991-06-21 1992-11-10 Pratt & Whitney Canada, Inc. Annular support
US6099165A (en) * 1999-01-19 2000-08-08 Pratt & Whitney Canada Corp. Soft bearing support
EP1247944A2 (en) 2001-04-06 2002-10-09 General Electric Company Gas turbine frame
JP2008082323A (en) * 2006-09-28 2008-04-10 Mitsubishi Heavy Ind Ltd Two-shaft gas turbine
EP1911938A1 (en) * 2006-10-13 2008-04-16 Snecma Turbofan
EP2045447A1 (en) * 2007-10-04 2009-04-08 Snecma Turbofan engine intermediate casing and corresponding turbofan engine
FR2927365A1 (en) * 2008-02-13 2009-08-14 Snecma Sa Exhaust case for turbomachine, has arms limited by trailing edges that make concavity at portion connecting arms to ferrule, and ferrule's end composed of circular sections, where each section has constant thickness around ferrule
WO2009142552A1 (en) * 2008-05-20 2009-11-26 Volvo Aero Corporation A gas turbine engine, a structural unit for a gas turbine engine and a method for manufacturing a structural unit
EP1458967B1 (en) * 2001-12-21 2012-05-02 Pratt & Whitney Canada Corp. Gas turbine engine with offset drive
WO2013004964A1 (en) 2011-07-04 2013-01-10 Snecma Turbine engine drive shaft device
WO2014018137A3 (en) * 2012-04-25 2014-04-17 General Electric Company Aircraft engine driveshaft vessel assembly and method of assembling the same
FR3026776A1 (en) * 2014-10-03 2016-04-08 Snecma POWER TRANSMISSION DEVICE FOR AN AIRCRAFT TURBOMACHINE
US9376935B2 (en) 2012-12-18 2016-06-28 Pratt & Whitney Canada Corp. Gas turbine engine mounting ring
US9498850B2 (en) 2012-03-27 2016-11-22 Pratt & Whitney Canada Corp. Structural case for aircraft gas turbine engine
US10392939B2 (en) 2015-06-12 2019-08-27 Rolls-Royce Plc Gas turbine arrangement
RU2711895C2 (en) * 2017-06-19 2020-01-23 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" Double-flow jet turbine engine
US20200284197A1 (en) * 2011-04-15 2020-09-10 United Technologies Corporation Gas turbine engine front center body architecture
EP4431706A1 (en) * 2023-03-14 2024-09-18 RTX Corporation Cast compressor case with a cooling cavity

Cited By (40)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0147351A1 (en) * 1983-12-05 1985-07-03 United Technologies Corporation Bearing support structure
EP0392401A1 (en) * 1989-04-10 1990-10-17 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Flow control device for fanjet/ramjet engine
US5160251A (en) * 1991-05-13 1992-11-03 General Electric Company Lightweight engine turbine bearing support assembly for withstanding radial and axial loads
US5161940A (en) * 1991-06-21 1992-11-10 Pratt & Whitney Canada, Inc. Annular support
US6099165A (en) * 1999-01-19 2000-08-08 Pratt & Whitney Canada Corp. Soft bearing support
EP1247944A3 (en) * 2001-04-06 2009-04-08 General Electric Company Gas turbine frame
EP1247944A2 (en) 2001-04-06 2002-10-09 General Electric Company Gas turbine frame
EP1458967B1 (en) * 2001-12-21 2012-05-02 Pratt & Whitney Canada Corp. Gas turbine engine with offset drive
JP2008082323A (en) * 2006-09-28 2008-04-10 Mitsubishi Heavy Ind Ltd Two-shaft gas turbine
US8042341B2 (en) 2006-10-13 2011-10-25 Snecma Turbojet engine accessory gear box driveshaft; modular additional accessory
FR2907167A1 (en) * 2006-10-13 2008-04-18 Snecma Sa GEARBOX DRIVE SHAFT OF AUXILIARY MACHINES OF A TURBOJET ENGINE; MODULAR SUPPLEMENTARY AUXILIARY MACHINE
RU2442000C2 (en) * 2006-10-13 2012-02-10 Снекма Double-flow turbojet engine with the intermediate jacket, with the drive shaft of transfer gearbox for turbojet engine accessory drive
EP1911938A1 (en) * 2006-10-13 2008-04-16 Snecma Turbofan
EP2045447A1 (en) * 2007-10-04 2009-04-08 Snecma Turbofan engine intermediate casing and corresponding turbofan engine
FR2921973A1 (en) * 2007-10-04 2009-04-10 Snecma Sa INTERMEDIATE CASING OF TURBOJET AND TURBOREACTOR
US8038386B2 (en) 2007-10-04 2011-10-18 Snecma Intermediate casing of a turbojet and a turbojet
FR2927365A1 (en) * 2008-02-13 2009-08-14 Snecma Sa Exhaust case for turbomachine, has arms limited by trailing edges that make concavity at portion connecting arms to ferrule, and ferrule's end composed of circular sections, where each section has constant thickness around ferrule
WO2009142552A1 (en) * 2008-05-20 2009-11-26 Volvo Aero Corporation A gas turbine engine, a structural unit for a gas turbine engine and a method for manufacturing a structural unit
US11713713B2 (en) * 2011-04-15 2023-08-01 Raytheon Technologies Corporation Gas turbine engine front center body architecture
US20200284197A1 (en) * 2011-04-15 2020-09-10 United Technologies Corporation Gas turbine engine front center body architecture
CN103717844A (en) * 2011-07-04 2014-04-09 斯奈克玛 Turbine engine drive shaft device
RU2621854C2 (en) * 2011-07-04 2017-06-07 Снекма Gas-turbine engine drive shaft device, gas-turbine engine and aircraft
JP2014518354A (en) * 2011-07-04 2014-07-28 スネクマ Turbine engine drive shaft device
WO2013004964A1 (en) 2011-07-04 2013-01-10 Snecma Turbine engine drive shaft device
FR2977635A1 (en) * 2011-07-04 2013-01-11 Snecma DRIVE SHAFT DEVICE OF A TURBOMACHINE
CN103717844B (en) * 2011-07-04 2015-12-23 斯奈克玛 Turbine engine drive shaft device, turbogenerator and aircraft
US9771968B2 (en) 2011-07-04 2017-09-26 Snecma Turbine engine drive shaft device
US9498850B2 (en) 2012-03-27 2016-11-22 Pratt & Whitney Canada Corp. Structural case for aircraft gas turbine engine
US10180084B2 (en) 2012-03-27 2019-01-15 Pratt & Whitney Canada Corp. Structural case for aircraft gas turbine engine
WO2014018137A3 (en) * 2012-04-25 2014-04-17 General Electric Company Aircraft engine driveshaft vessel assembly and method of assembling the same
US9657646B2 (en) 2012-04-25 2017-05-23 General Electric Company Aircraft engine driveshaft vessel assembly and method of assembling the same
CN104350237B (en) * 2012-04-25 2016-03-02 通用电气公司 Aircraft engine drive shaft container assembly and method of assembling said assembly
JP2015514909A (en) * 2012-04-25 2015-05-21 ゼネラル・エレクトリック・カンパニイ Aircraft engine drive shaft compartment assembly and method of assembling an aircraft engine drive shaft compartment assembly
CN104350237A (en) * 2012-04-25 2015-02-11 通用电气公司 Aircraft engine driveshaft vessel assembly and method of assembling same
US9376935B2 (en) 2012-12-18 2016-06-28 Pratt & Whitney Canada Corp. Gas turbine engine mounting ring
FR3026776A1 (en) * 2014-10-03 2016-04-08 Snecma POWER TRANSMISSION DEVICE FOR AN AIRCRAFT TURBOMACHINE
US10392939B2 (en) 2015-06-12 2019-08-27 Rolls-Royce Plc Gas turbine arrangement
RU2711895C2 (en) * 2017-06-19 2020-01-23 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" Double-flow jet turbine engine
EP4431706A1 (en) * 2023-03-14 2024-09-18 RTX Corporation Cast compressor case with a cooling cavity
US12158078B2 (en) 2023-03-14 2024-12-03 Rtx Corporation Compressor case with a cooling cavity

Similar Documents

Publication Publication Date Title
GB926947A (en) Improvements relating to gas turbine engine casings
US3704075A (en) Combined turbine nozzle and bearing frame
ES476461A1 (en) Gas turbine plant
GB1151613A (en) Improvements In Gas Turbine Ducted Fan Engine Assemblies
GB1149513A (en) Bearing assembly
GB938189A (en) Improvements in the construction of turbine and compressor blade elements
CH653098A5 (en) GAS TURBINE PLANT.
US2925954A (en) Compressor group with intercooler
GB856670A (en) Improvements in compressor rear frame
GB726072A (en) Improvements in and relating to elastic fluid turbines
GB954063A (en) Low-pressure diaphragm assembly for high-power condensing turbines
US2994508A (en) Lightweight compressor housing construction
GB603996A (en) Improvements relating to multi-stage turbines and compressors
US4197702A (en) Rotor support structure for a gas turbine engine
GB797445A (en) Improvements in or relating to rotary fluid machines, for example turbines and compressors
GB707353A (en) Improvements in or relating to axial-flow compressor apparatus
US3496628A (en) Method of joining thin-walled members,particularly in casings for gas turbine engines
GB789204A (en) Improvements in or relating to axial flow compressors or turbines
GB897907A (en) Hydraulic machines for hydraulic storage power stations
US2996280A (en) Heat shield
GB844020A (en) Stator vane assemblies for axial-flow compressors and turbines
GB1442350A (en) Gas turbine engine combustion equipment
GB808655A (en) Improvements in or relating to multi-stage axial-flow compressors
GB815032A (en) Improvements in or relating to multi-stage axial-flow turbines and compressors
US4087200A (en) Stator of multistage centrifugal compressor