GB1345910A - Gas turbine engines - Google Patents

Gas turbine engines

Info

Publication number
GB1345910A
GB1345910A GB1267971*[A GB1267971A GB1345910A GB 1345910 A GB1345910 A GB 1345910A GB 1267971 A GB1267971 A GB 1267971A GB 1345910 A GB1345910 A GB 1345910A
Authority
GB
United Kingdom
Prior art keywords
compressor
chamber
air
rotor
discs
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
GB1267971*[A
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB1345910A publication Critical patent/GB1345910A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • 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
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Landscapes

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

Abstract

1345910 Gas turbine engines - control of cooling air GENERAL ELECTRIC CO 3 May 1971 [3 Aug 1970] 12679/71 Heading F1G A gas turbine engine comprises a compressor and a vortex chamber in communication with the working fluid path of the compressor, there being an outlet from the vortex chamber, and means for varying the strength of a natural vortex which forms in the chamber upon rotation of the rotor so as to vary the mass flow rate of fluid passing through the chamber from the fluid path of the compressor to the outlet. The engine shown comprises a compressor 14, combustion equipment 16 and a turbine 22, the compressor rotor comprising discs 26 and the turbine rotor comprising discs 42, the compressor and turbine rotors being connected together by a shaft member comprising conical portions 52, 54. One of the compressor rotor discs comprises two discs 62 spaced apart to form a vortex chamber 64 therebetween into which air tapped off the compressor flow path through openings 66 flows, the air discharging from the vortex chamber into a first plenum chamber 68 defined within the compressor rotor, as indicated by arrow 76. The air then flows through openings 72 in the conical portion 52 of the shaft into a second plenum chamber 70, then through openings 82 in the conical portion 54 of the shaft into a third plenum chamber 78 defined within the turbine rotor. The air then flows radially outwardly between the turbine rotor discs 42, through openings in the connecting member 46 to passages in the turbine rotor blades for cooling thereof. Air under higher pressure is tapped from the compressor through openings 102 and passes through line 100 to a control valve 98 then through line 96 to a manifold disposed adjacent one of the discs 62. The air then discharges through a series of nozzles 92 into the vortex chamber 64, the nozzles discharging in a circumferential direction opposite to the direction of rotation of the rotor. The valve 98 is of centrifugal type such that at maximum speed the flow of air through nozzles 92 is a maximum so that formation of a natural vortex in chamber 64 is prevented and flow of cooling air from the chamber 64 is a maximum.
GB1267971*[A 1970-08-03 1971-05-03 Gas turbine engines Expired GB1345910A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US6032070A 1970-08-03 1970-08-03

Publications (1)

Publication Number Publication Date
GB1345910A true GB1345910A (en) 1974-02-06

Family

ID=22028757

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1267971*[A Expired GB1345910A (en) 1970-08-03 1971-05-03 Gas turbine engines

Country Status (6)

Country Link
US (1) US3632221A (en)
BE (1) BE766536A (en)
CA (1) CA951921A (en)
DE (1) DE2121069A1 (en)
FR (1) FR2101178B1 (en)
GB (1) GB1345910A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2433550A (en) * 2005-12-20 2007-06-27 Gen Electric Turbine disk and forward shaft arrangement in a gas turbine engine
CN109110138A (en) * 2017-06-26 2019-01-01 通用电气公司 Method for the propulsion system of aircraft and for operating it

Families Citing this family (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3897168A (en) * 1974-03-05 1975-07-29 Westinghouse Electric Corp Turbomachine extraction flow guide vanes
US4213738A (en) * 1978-02-21 1980-07-22 General Motors Corporation Cooling air control valve
US4217755A (en) * 1978-12-04 1980-08-19 General Motors Corporation Cooling air control valve
FR2491549B1 (en) * 1980-10-08 1985-07-05 Snecma DEVICE FOR COOLING A GAS TURBINE, BY TAKING AIR FROM THE COMPRESSOR
US4397471A (en) * 1981-09-02 1983-08-09 General Electric Company Rotary pressure seal structure and method for reducing thermal stresses therein
DE3638960C1 (en) * 1986-11-14 1988-04-28 Mtu Muenchen Gmbh Gas turbine jet engine with a cooled high pressure compressor
DE3638961A1 (en) * 1986-11-14 1988-05-26 Mtu Muenchen Gmbh GAS TURBINE ENGINE WITH A HIGH PRESSURE COMPRESSOR
EP0267478B1 (en) * 1986-11-14 1991-12-18 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Gas turbine jet engine with a high pressure compressor
FR2609500B1 (en) * 1987-01-14 1991-04-12 Snecma TURBOMACHINE COMPRESSOR DISC WITH CENTRIPTIC ACCELERATOR FOR SUCTION OF TURBINE COOLING AIR
GB2207465B (en) * 1987-07-18 1992-02-19 Rolls Royce Plc A compressor and air bleed arrangement
US5316437A (en) * 1993-02-19 1994-05-31 General Electric Company Gas turbine engine structural frame assembly having a thermally actuated valve for modulating a flow of hot gases through the frame hub
DE19632038A1 (en) * 1996-08-08 1998-02-12 Asea Brown Boveri Device for separating dust particles
US6672072B1 (en) 1998-08-17 2004-01-06 General Electric Company Pressure boosted compressor cooling system
DE10159670A1 (en) * 2001-12-05 2003-06-18 Rolls Royce Deutschland Vortex rectifier in the high pressure compressor of a gas turbine
EP1566531A1 (en) * 2004-02-19 2005-08-24 Siemens Aktiengesellschaft Gas turbine with compressor casing protected against cooling and Method to operate a gas turbine
DE102004042295A1 (en) * 2004-09-01 2006-03-02 Mtu Aero Engines Gmbh Rotor for an engine
US8578716B2 (en) * 2008-03-22 2013-11-12 United Technologies Corporation Valve system for a gas turbine engine
US9605663B2 (en) 2010-08-24 2017-03-28 Qwtip Llc System and method for separating fluids and creating magnetic fields
US8636910B2 (en) 2010-08-24 2014-01-28 Qwtip Llc Water treatment and revitalization system and method
US10790723B2 (en) 2010-08-24 2020-09-29 Qwtip Llc Disk-pack turbine
US9469553B2 (en) 2011-08-24 2016-10-18 Qwtip, Llc Retrofit attachments for water treatment systems
US9474991B2 (en) 2011-08-24 2016-10-25 Qwtip, Llc Water treatment system and method
US20140183144A1 (en) 2011-08-24 2014-07-03 Qwtip Llc Water Treatment System and Method
WO2013130901A1 (en) 2012-02-28 2013-09-06 Qwtip Llc Desalination and/or gas production system and method
WO2013130888A1 (en) 2012-02-29 2013-09-06 Qwtip Llc Levitation and distribution system and method
US9091173B2 (en) 2012-05-31 2015-07-28 United Technologies Corporation Turbine coolant supply system
US9617917B2 (en) 2013-07-31 2017-04-11 General Electric Company Flow control assembly and methods of assembling the same
US11149642B2 (en) 2015-12-30 2021-10-19 General Electric Company System and method of reducing post-shutdown engine temperatures

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2618433A (en) * 1948-06-23 1952-11-18 Curtiss Wright Corp Means for bleeding air from compressors
US2791091A (en) * 1950-05-15 1957-05-07 Gen Motors Corp Power plant cooling and thrust balancing systems
GB712051A (en) * 1951-10-10 1954-07-14 Rolls Royce Improvements in or relating to axial-flow fluid machines
US2787440A (en) * 1953-05-21 1957-04-02 Westinghouse Electric Corp Turbine apparatus
US3043561A (en) * 1958-12-29 1962-07-10 Gen Electric Turbine rotor ventilation system
CH487337A (en) * 1968-01-10 1970-03-15 Sulzer Ag Arrangement for the passage of gas through the shell of a hollow rotor

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2433550A (en) * 2005-12-20 2007-06-27 Gen Electric Turbine disk and forward shaft arrangement in a gas turbine engine
US7331763B2 (en) 2005-12-20 2008-02-19 General Electric Company Turbine disk
GB2433550B (en) * 2005-12-20 2011-02-09 Gen Electric Turbine disk having balanced thermal response rate
CN109110138A (en) * 2017-06-26 2019-01-01 通用电气公司 Method for the propulsion system of aircraft and for operating it
CN109110138B (en) * 2017-06-26 2021-11-30 通用电气公司 Propulsion system for an aircraft and method for operating the same

Also Published As

Publication number Publication date
DE2121069A1 (en) 1972-02-10
BE766536A (en) 1971-09-16
CA951921A (en) 1974-07-30
FR2101178A1 (en) 1972-03-31
US3632221A (en) 1972-01-04
FR2101178B1 (en) 1974-04-05

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees