GB926160A - A gas turbine with preheating and cooling of the turbine rotor - Google Patents

A gas turbine with preheating and cooling of the turbine rotor

Info

Publication number
GB926160A
GB926160A GB44099/59A GB4409959A GB926160A GB 926160 A GB926160 A GB 926160A GB 44099/59 A GB44099/59 A GB 44099/59A GB 4409959 A GB4409959 A GB 4409959A GB 926160 A GB926160 A GB 926160A
Authority
GB
United Kingdom
Prior art keywords
turbine
coolant
rotor
nozzles
disc
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
GB44099/59A
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 GB926160A publication Critical patent/GB926160A/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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • 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

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)

Abstract

926,160. Gas turbine engines. GENERAL ELECTRIC CO. Dec. 29, 1959 [Dec. 29, 1958], No. 44099/59. Class 110 (3). In a gas turbine having passage means in communication with the compressor discharge side and which establish a flow path around the inner portion of at least the first stage rotor disc and which form nozzle members 17, said nozzle members being rearwardly directed relative to the direction of rotation of the rotor. Coolant flows from a chamber 9c, through nozzles 9d, which are inwardly tapered and rearwardly directed relative to the direction of rotation of the rotor, thereby imparting rotational energy to the cylinder 9 to reduce the pressure and temperature of the coolant. The nozzle members 17 are machined in trapezoidal blocks, the coolant passing through a nozzle 17b via a cylindrical chamber 17a. The blocks also serve as heads of bolt members 17c, which hold the turbine discs 2a, 2b together. From the nozzles 17b part of the coolant flows along the rear face of the disc 2a, while the remainder of the coolant passes through a sealing ring member 15 to cool the front of the second turbine disc 2b. The fluid flow through the nozzles 17b also imparts rotational energy to the turbine rotor. On starting the flow of coolant will heat the turbine discs sufficiently to eliminate dangerous thermal stress gradients until normal running temperatures are reached.
GB44099/59A 1958-12-29 1959-12-29 A gas turbine with preheating and cooling of the turbine rotor Expired GB926160A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US783376A US3043561A (en) 1958-12-29 1958-12-29 Turbine rotor ventilation system

Publications (1)

Publication Number Publication Date
GB926160A true GB926160A (en) 1963-05-15

Family

ID=25129059

Family Applications (1)

Application Number Title Priority Date Filing Date
GB44099/59A Expired GB926160A (en) 1958-12-29 1959-12-29 A gas turbine with preheating and cooling of the turbine rotor

Country Status (3)

Country Link
US (1) US3043561A (en)
CH (1) CH378100A (en)
GB (1) GB926160A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2633291A1 (en) * 1976-07-23 1978-01-26 Kraftwerk Union Ag GAS TURBINE SYSTEM WITH COOLING THROUGH TWO SEPARATE COOLING AIR FLOWS
EP0037897A1 (en) * 1980-04-15 1981-10-21 M.A.N. MASCHINENFABRIK AUGSBURG-NÜRNBERG Aktiengesellschaft Means for internally cooling a gas turbine
WO1999006671A1 (en) * 1997-07-31 1999-02-11 Siemens Aktiengesellschaft Distribution of cooling air in a turbine stage of a gas turbine

Families Citing this family (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3230710A (en) * 1962-12-24 1966-01-25 Garrett Corp Gas turbine
GB1152331A (en) * 1966-05-18 1969-05-14 Rolls Royce Improvements in Gas Turbine Blade Cooling
US3631672A (en) * 1969-08-04 1972-01-04 Gen Electric Eductor cooled gas turbine casing
US3632221A (en) * 1970-08-03 1972-01-04 Gen Electric Gas turbine engine cooling system incorporating a vortex shaft valve
US3748056A (en) * 1971-02-09 1973-07-24 Nissan Motor Turbine blade cooling
US3904307A (en) * 1974-04-10 1975-09-09 United Technologies Corp Gas generator turbine cooling scheme
US4008977A (en) * 1975-09-19 1977-02-22 United Technologies Corporation Compressor bleed system
GB2042086B (en) * 1979-02-26 1983-10-12 Gen Electric Gas turbine engine seal
US4332133A (en) * 1979-11-14 1982-06-01 United Technologies Corporation Compressor bleed system for cooling and clearance control
US4453888A (en) * 1981-04-01 1984-06-12 United Technologies Corporation Nozzle for a coolable rotor blade
US4543038A (en) * 1982-03-08 1985-09-24 The Garrett Corporation Sealing apparatus and method and machinery utilizing same
US4674955A (en) * 1984-12-21 1987-06-23 The Garrett Corporation Radial inboard preswirl system
US4759688A (en) * 1986-12-16 1988-07-26 Allied-Signal Inc. Cooling flow side entry for cooled turbine blading
FR2614654B1 (en) * 1987-04-29 1992-02-21 Snecma TURBOMACHINE AXIAL COMPRESSOR DISC WITH CENTRIPTED AIR TAKE-OFF
GB9723268D0 (en) * 1997-11-05 1998-01-07 Rolls Royce Plc Turbine
DE10159670A1 (en) * 2001-12-05 2003-06-18 Rolls Royce Deutschland Vortex rectifier in the high pressure compressor of a gas turbine
FR2851010B1 (en) * 2003-02-06 2005-04-15 Snecma Moteurs DEVICE FOR VENTILATION OF A HIGH PRESSURE TURBINE ROTOR OF A TURBOMACHINE
FR2881794B1 (en) * 2005-02-09 2007-04-20 Snecma Moteurs Sa TURBOMACHINE WITH A NOISE REDUCTION MEANS
GB0603030D0 (en) * 2006-02-15 2006-03-29 Rolls Royce Plc Gas turbine engine rotor ventilation arrangement
US8677766B2 (en) * 2010-04-12 2014-03-25 Siemens Energy, Inc. Radial pre-swirl assembly and cooling fluid metering structure for a gas turbine engine
RU2443882C1 (en) * 2010-08-23 2012-02-27 Открытое акционерное общество "Авиадвигатель" Gas turbine engine
GB201103890D0 (en) * 2011-03-08 2011-04-20 Rolls Royce Plc Gas turbine engine swirled cooling air
US20130051974A1 (en) * 2011-08-25 2013-02-28 Honeywell International Inc. Gas turbine engines and methods for cooling components thereof with mid-impeller bleed cooling air
CN103046964B (en) * 2012-06-27 2015-12-09 北京航空航天大学 A kind of aero-engine turbine disk based on active temperature gradient proof stress
JP6432110B2 (en) * 2014-08-29 2018-12-05 三菱日立パワーシステムズ株式会社 gas turbine
FR3048998B1 (en) * 2016-03-16 2019-12-13 Safran Aircraft Engines TURBINE ROTOR COMPRISING A VENTILATION SPACER
CN106640212B (en) * 2016-11-04 2019-07-02 北京航空航天大学 A kind of oblique nozzle of air supply of prewhirling of aero gas turbine engine high-pressure turbine disk chamber cooling air

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2369795A (en) * 1941-11-17 1945-02-20 Andre P E Planiol Gaseous fluid turbine or the like
US2632626A (en) * 1947-02-12 1953-03-24 United Aircraft Corp Dirt trap for turbine cooling air
US2639579A (en) * 1949-06-21 1953-05-26 Hartford Nat Bank & Trust Co Turbojet engine having tail pipe ejector to induce flow of cooling air
US2680001A (en) * 1950-11-13 1954-06-01 United Aircraft Corp Arrangement for cooling turbine bearings
US2858101A (en) * 1954-01-28 1958-10-28 Gen Electric Cooling of turbine wheels

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2633291A1 (en) * 1976-07-23 1978-01-26 Kraftwerk Union Ag GAS TURBINE SYSTEM WITH COOLING THROUGH TWO SEPARATE COOLING AIR FLOWS
EP0037897A1 (en) * 1980-04-15 1981-10-21 M.A.N. MASCHINENFABRIK AUGSBURG-NÜRNBERG Aktiengesellschaft Means for internally cooling a gas turbine
WO1999006671A1 (en) * 1997-07-31 1999-02-11 Siemens Aktiengesellschaft Distribution of cooling air in a turbine stage of a gas turbine
US6231303B1 (en) 1997-07-31 2001-05-15 Siemens Aktiengesellschaft Gas turbine having a turbine stage with cooling-air distribution

Also Published As

Publication number Publication date
US3043561A (en) 1962-07-10
CH378100A (en) 1964-05-31

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