GB1345910A - Gas turbine engines - Google Patents
Gas turbine enginesInfo
- 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
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.
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)
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)
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 MàNchen 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)
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 |
-
1970
- 1970-08-03 US US60320A patent/US3632221A/en not_active Expired - Lifetime
-
1971
- 1971-04-29 DE DE19712121069 patent/DE2121069A1/en active Pending
- 1971-04-30 FR FR7115649A patent/FR2101178B1/fr not_active Expired
- 1971-04-30 BE BE766536A patent/BE766536A/en unknown
- 1971-05-03 GB GB1267971*[A patent/GB1345910A/en not_active Expired
- 1971-05-18 CA CA113,229A patent/CA951921A/en not_active Expired
Cited By (5)
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 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
GB1345910A (en) | Gas turbine engines | |
US3602605A (en) | Cooling system for a gas turbine | |
US2435836A (en) | Centrifugal compressor | |
GB1350471A (en) | Gas turbine engine | |
GB1424925A (en) | Air cooling of turbine blades | |
GB1075030A (en) | A vane or blade of stacked wafer const ruction for a turbine or like fluid flow machine | |
GB1534000A (en) | Turbine vane cooling | |
GB1018166A (en) | Gas-turbine plant | |
US5941687A (en) | Gas turbine engine turbine system | |
GB1088360A (en) | Improvements in gas turbine ducted fan engine sealing means | |
GB1321524A (en) | Gas turbine engine | |
GB1457634A (en) | Converging-diverging supersonic nozzles | |
GB981848A (en) | Gas turbine plant | |
GB1090173A (en) | Gas turbine engine | |
GB1516466A (en) | Gas turbine engine air inlets having particle separators | |
GB774425A (en) | Improvements in or relating to turbine engines | |
GB1435687A (en) | Gas generators | |
GB1256486A (en) | ||
GB1524956A (en) | Gas tubine engine | |
GB1270959A (en) | Means for cooling or regulating the temperature of a gas turbine engine | |
US2937498A (en) | Mechanically controlled multistage combustion chambers for gas-impulsetype engines and improved discharge control therefor | |
GB1282142A (en) | Improvements in or relating to gas turbine engines | |
GB1348127A (en) | Gas turbine engine | |
US2393713A (en) | Aircraft supercharger | |
GB787666A (en) | Improvements in blades for gas turbine engines |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed [section 19, patents act 1949] | ||
PLNP | Patent lapsed through nonpayment of renewal fees |