GB751884A - Improvements relating to the air-cooling of gas turbines - Google Patents

Improvements relating to the air-cooling of gas turbines

Info

Publication number
GB751884A
GB751884A GB9137/54A GB913754A GB751884A GB 751884 A GB751884 A GB 751884A GB 9137/54 A GB9137/54 A GB 9137/54A GB 913754 A GB913754 A GB 913754A GB 751884 A GB751884 A GB 751884A
Authority
GB
United Kingdom
Prior art keywords
blades
compressor
air
turbine
cooling air
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
GB9137/54A
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.)
Daimler Benz AG
Original Assignee
Daimler Benz 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 Daimler Benz AG filed Critical Daimler Benz AG
Publication of GB751884A publication Critical patent/GB751884A/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
    • 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
    • F02C7/185—Cooling means for reducing the temperature of the cooling air or gas
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)

Abstract

751,884. Gas turbine plant. DAIMLERBENZ AKT.-GES. March 29, 1954 [March 27, 1953], No. 9137/54. Class 110(3) A gas turbine plant having cooling air branched off from the air for combustion in or after an air compressor and led through the interior of the turbine blades has the amount of cooling air regulated in dependence upon the temperature of the turbine blades or upon the temperature of the gas flowing past the blades so that the full amount of cooling air only flows at high blade or gas temperature. Air from the compressor 14 passes through the heat exchanger 19 and combustion chamber 21 to the turbine 16 which exhausts through the heat exchanger 19. Cooling air is taken from the discharge of the compressor arid led through a duct 25, control valve 51 and cooler 28 to the inlet of a compressor 26 driven by the turbine shaft through gearing 27. The discharge of the compressor 26 is divided, part flows through the pipe 31 to a jacket space 33 and then through the stator blades 16 in succession and part flows through the pipe 39 to a bore 40 in the turbine shaft 12 and then through the rotor blades 16<SP>11</SP> in succession. The heated air from the stator blades is led into the air supply pipe to the combustion chamber 21 through a pipe 35. The heated air from the rotor blades is used to heat the inlet distributer of the compressor and may then be led to the air supply pipe to the combustion chamber. The cooling air may, if desired, be arranged to flow through the guide and motor blades in series instead of in parallel as described. The valve 51 is controlled by a thermostat arranged in the turbine exhaust so that at high temperatures the valve 51 is fully open. As the exhaust gas temperature falls, the thermostat may close the valve 51 gradually or in stages or suddenly. The thermostat may also operate a clutch in the drive to the compressor 26. A modification in' which the valve 51 is operated -through ra servomotor by a thermostat fitted to one of the guide blades 16<SP>1</SP> is also describes. To keep the cooling air supply constant irrespective of the speed of rotation a compensating lever adjustable by a speed responsive device may be incorporated in the system of rods 52.
GB9137/54A 1953-03-27 1954-03-29 Improvements relating to the air-cooling of gas turbines Expired GB751884A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE751884X 1953-03-27

Publications (1)

Publication Number Publication Date
GB751884A true GB751884A (en) 1956-07-04

Family

ID=6652844

Family Applications (2)

Application Number Title Priority Date Filing Date
GB9136/54A Expired GB754856A (en) 1953-03-27 1954-03-29 Improvements relating to the air cooling of gas turbines
GB9137/54A Expired GB751884A (en) 1953-03-27 1954-03-29 Improvements relating to the air-cooling of gas turbines

Family Applications Before (1)

Application Number Title Priority Date Filing Date
GB9136/54A Expired GB754856A (en) 1953-03-27 1954-03-29 Improvements relating to the air cooling of gas turbines

Country Status (3)

Country Link
US (1) US2940257A (en)
FR (1) FR1097374A (en)
GB (2) GB754856A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5016436A (en) * 1987-10-20 1991-05-21 Rolls-Royce Plc Interturbine duct

Families Citing this family (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2951340A (en) * 1956-01-03 1960-09-06 Curtiss Wright Corp Gas turbine with control mechanism for turbine cooling air
US3015937A (en) * 1958-07-03 1962-01-09 James V Giliberty Temperature modulating system for internal combustion turbines and the like
US3302397A (en) * 1958-09-02 1967-02-07 Davidovic Vlastimir Regeneratively cooled gas turbines
US3209536A (en) * 1960-04-04 1965-10-05 Ford Motor Co Re-expansion type gas turbine engine with intercooler fan driven by the low pressure turbine
US3142155A (en) * 1961-11-29 1964-07-28 Gen Electric Gas turbine engine cooling arrangement
GB1479599A (en) * 1973-11-09 1977-07-13 Secr Defence Aircraft gas turbine engine turbine blade cooling
US3973396A (en) * 1974-10-16 1976-08-10 United Turbine Ab & Co., Kommanditbolag Gas turbine power plant
US4576547A (en) * 1983-11-03 1986-03-18 United Technologies Corporation Active clearance control
FR2656657A1 (en) * 1989-12-28 1991-07-05 Snecma AIR COOLED TURBOMACHINE AND METHOD FOR COOLING THE SAME.
DE4210541A1 (en) * 1992-03-31 1993-10-07 Asea Brown Boveri Process for operating a gas turbine group
JP3353259B2 (en) * 1994-01-25 2002-12-03 謙三 星野 Turbin
US5724806A (en) * 1995-09-11 1998-03-10 General Electric Company Extracted, cooled, compressed/intercooled, cooling/combustion air for a gas turbine engine
US6098395A (en) * 1996-04-04 2000-08-08 Siemens Westinghouse Power Corporation Closed-loop air cooling system for a turbine engine
WO1998013584A1 (en) * 1996-09-26 1998-04-02 Siemens Aktiengesellschaft Method of compensating pressure loss in a cooling air guide system in a gas turbine plant
JPH1193694A (en) * 1997-09-18 1999-04-06 Toshiba Corp Gas turbine plant
US6389793B1 (en) * 2000-04-19 2002-05-21 General Electric Company Combustion turbine cooling media supply system and related method
EP1614858A1 (en) * 2004-07-09 2006-01-11 Siemens Aktiengesellschaft Method and apparatus for monitoring the cooling system of a turbine
US20090051167A1 (en) * 2007-08-22 2009-02-26 General Electric Company Combustion turbine cooling media supply method
US8096747B2 (en) * 2008-02-01 2012-01-17 General Electric Company Apparatus and related methods for turbine cooling
CN104564183B (en) * 2008-10-08 2016-08-24 三菱重工业株式会社 Gas turbine and method of operation thereof
US8100632B2 (en) * 2008-12-03 2012-01-24 General Electric Company Cooling system for a turbomachine
ITFI20110257A1 (en) * 2011-12-02 2013-06-03 Nuovo Pignone Spa "COOLING SYSTEM FOR GAS TURBINE LOAD COUPLING"
US20160069264A1 (en) * 2013-07-22 2016-03-10 Joseph D. Brostmeyer Gas turbine engine with turbine cooling and combustor air preheating
EP3044430B1 (en) * 2013-09-12 2020-03-25 Florida Turbine Technologies, Inc. Industrial gas turbine engine
US9850819B2 (en) * 2015-04-24 2017-12-26 United Technologies Corporation Intercooled cooling air with dual pass heat exchanger
US10830148B2 (en) 2015-04-24 2020-11-10 Raytheon Technologies Corporation Intercooled cooling air with dual pass heat exchanger
US20170218844A1 (en) * 2016-02-01 2017-08-03 United Technologies Corporation Cooling air for variable area turbine
US10563577B2 (en) * 2016-08-22 2020-02-18 United Technologies Corporation Low rotor boost compressor for engine cooling circuit
US20180180289A1 (en) * 2016-12-23 2018-06-28 General Electric Company Turbine engine assembly including a rotating detonation combustor

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB190915565A (en) * 1909-07-03 1910-07-04 Hans Holzwarth Improvements in Gas Turbines.
US2551307A (en) * 1944-10-14 1951-05-01 Frank B Yingling Turbocharged two-cycle engine with liquid cooled exhaust ducts
FR57013E (en) * 1945-06-16 1952-11-03
US2618120A (en) * 1946-06-07 1952-11-18 Papini Anthony Coaxial combustion products generator and turbine with cooling means
US2445837A (en) * 1946-08-24 1948-07-27 Jr Thomas M Mckenzie Air-cooled gas turbine
US2652816A (en) * 1949-03-26 1953-09-22 Adiel Y Dodge Thermostatically controlled clutch and fan drive

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5016436A (en) * 1987-10-20 1991-05-21 Rolls-Royce Plc Interturbine duct

Also Published As

Publication number Publication date
US2940257A (en) 1960-06-14
FR1097374A (en) 1955-07-05
GB754856A (en) 1956-08-15

Similar Documents

Publication Publication Date Title
GB751884A (en) Improvements relating to the air-cooling of gas turbines
GB609682A (en) Improvements in or relating to turbines
GB938247A (en) Gas turbine engine having cooled turbine blading
US2253809A (en) Gas compressing apparatus and method of regulating the same
GB649639A (en) Improvements in thermal power plants
GB682469A (en) Improvements relating to gas turbine plants
US2544941A (en) Gas turbine plant
GB744162A (en) Improvements relating to pressure exchangers
GB695891A (en) Improvements in or relating to gas-turbine engines
GB652048A (en) Improvements relating to exhaust driven turbines on reciprocating internal combustion engines
SU384038A1 (en) STAND FOR AERODYNAMIC TEST OF FANS
GB592389A (en) Improvements in or relating to thermal power plants
GB695339A (en) Improvements relating to plants for producing a supply of compressed air
GB621123A (en) Improvements in air conditioning and cabin pressurising plant for aircraft
GB578628A (en) Gas-or air-turbine plant
GB488538A (en) Means for regulating and starting thermal power plants
GB574921A (en) Improvements in or relating to gas-turbine plants
GB935172A (en) Gas turbine installation comprising at least one mechanically independent useful power turbine
GB716274A (en) Improvements in or relating to recuperative heat exchangers
GB716145A (en) Improvements in aircraft jet propulsion engines including a ducted fan
GB760240A (en) Improvements in and relating to power control systems for gas turbines
SU826088A1 (en) Compressor output control system
GB737648A (en) Improvements in gas turbine power plants
GB693227A (en) Improvements in and relating to gas turbine units
GB586912A (en) Turbine system