GB754856A - Improvements relating to the air cooling of gas turbines - Google Patents

Improvements relating to the air cooling of gas turbines

Info

Publication number
GB754856A
GB754856A GB9136/54A GB913654A GB754856A GB 754856 A GB754856 A GB 754856A GB 9136/54 A GB9136/54 A GB 9136/54A GB 913654 A GB913654 A GB 913654A GB 754856 A GB754856 A GB 754856A
Authority
GB
United Kingdom
Prior art keywords
conduit
air
compressor
turbine
passages
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
GB9136/54A
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 GB754856A publication Critical patent/GB754856A/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

754.856. Gas turbine plant. DAIMLERBENZ AKT.-GES. March 29, 1954 [March 27, 1953], No. 9136/54. Class 110(3) In a gas turbine plant, air is branched from the combustion air supply then caused to pass through enclosed circuits, including ducts in the stator and rotor blades, in parallel with the combustion air flow and then finally mixed with the combustion air to complement the latter in supporting combustion. Air compressed in the compressor 14 is heated in the heatexchanger 19 by the turbine exhaust gases and then passed into a combustion chamber 21 feeding a gas turbine 16 driving the compressor. A part of the air compressed in the compressor 14 is passed through the cooler 28 and then further compressed in a compressor 26 driven from the turbine shaft. The discharge of the compressor 26 passes through a dust separator 30 into a conduit 29 which branches into conduits 31, 32. The conduit 31 passes into the turbine casing where the cooling air is caused to pass through annular spaces 33 and U-shaped passages 34 in the guide blades to a conduit 35 leading through a change-over valve 36 and a conduit 37 into the main air or gas pipe 20 leading to the turbine 16. The conduit 32 is connected through a changeover valve 38 to a conduit 39 which is in turn connected to a bore 40 in the turbine shaft and to the change-over valve 36. The bore 40 is connected through U-shaped cooling air passages 41, 43 in the rotor blades and passages 42, 44 to a conduit 45 which leads to cooling passages 47 in the compressor inlet guide blades and thence to a conduit 49 to the main air or gas pipe 20. A change-over or short-circuit valve may be provided at the point 50 to by-pass the compressor inlet guide blades. In the position of the change-over valves 36, 38 shown, the cooling air is passed through the stator and rotor blades in series. By changing over the valves, the circuits through the stator and rotor blades may be arranged in parallel. One or more intermediate coolers for the cooling air may be provided between the parts of the turbine to be cooled.
GB9136/54A 1953-03-27 1954-03-29 Improvements relating to the air cooling of gas turbines Expired GB754856A (en)

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
GB754856A true GB754856A (en) 1956-08-15

Family

ID=6652844

Family Applications (2)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3142155A (en) * 1961-11-29 1964-07-28 Gen Electric Gas turbine engine cooling arrangement

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
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
GB8724537D0 (en) * 1987-10-20 1987-11-25 Rolls Royce Plc Interturbine duct
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
CN102112704B (en) * 2008-10-08 2015-07-15 三菱重工业株式会社 Gas turbine and operating method therefor
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
JP6356813B2 (en) * 2013-09-12 2018-07-11 フロリダ タービン テクノロジーズ インコーポレイテッドＦｌｏｒｉｄａ Ｔｕｒｂｉｎｅ Ｔｅｃｈｎｏｌｏｇｉｅｓ， Ｉｎｃ． High pressure ratio twin spool industrial gas turbine engine
US10830148B2 (en) 2015-04-24 2020-11-10 Raytheon Technologies Corporation Intercooled cooling air with dual pass heat exchanger
US9850819B2 (en) * 2015-04-24 2017-12-26 United 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
US3142155A (en) * 1961-11-29 1964-07-28 Gen Electric Gas turbine engine cooling arrangement

Also Published As

Publication number Publication date
FR1097374A (en) 1955-07-05
US2940257A (en) 1960-06-14
GB751884A (en) 1956-07-04

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