GB1284858A - Gas turbine engine constructions - Google Patents

Gas turbine engine constructions

Info

Publication number
GB1284858A
GB1284858A GB26584/71A GB2658471A GB1284858A GB 1284858 A GB1284858 A GB 1284858A GB 26584/71 A GB26584/71 A GB 26584/71A GB 2658471 A GB2658471 A GB 2658471A GB 1284858 A GB1284858 A GB 1284858A
Authority
GB
United Kingdom
Prior art keywords
air
openings
rotor
disc
turbine
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
GB26584/71A
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.)
Raytheon Technologies Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB1284858A publication Critical patent/GB1284858A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • 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
    • 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)

Abstract

1284858 Gas turbine engines - cooling UNITED AIRCRAFT CORP 19 April 1971 [28 April 1970] 26584/71 Heading F1G The invention relates to a gas turbine engine and to means for supplying coolant air-flow to the turbine rotor blades. The engine shown comprises a compressor outlet diffuser 2, combustion equipment 4 comprising a series of flame tubes 6 disposed within an annular air space formed by walls 8, 14, turbine inlet nozzle guide vanes 18 and a two-stage turbine comprising rotor discs 40, 60 having hollow blades 42, 62 mounted thereon. A portion of air from the diffuser 2 passes into an annular manifold 100 and thence through struts 104 to an annular space 17 defined between the inner air casing walls 14, 15, the air passing to a space defined between fixed wall members 28, 30. The air passes from this space into an annular passage 26 defined between fixed wall members 24, 30, a series of inclined guide vanes 27 being located in the passage 26 whereby the cooling air is given a swirl in the same direction as the rotation of the rotor disc 40. The passage assembly 26 extends into a rotating annular passage assembly defined by wall members 48, 49 secured to the upstream face of the turbine rotor disc 40, air passing from the annular passage through openings 52, 54 formed in the rotor disc, the air passing through opening 52 passing into a space defined by side plates 44, 46 thence through openings and into the hollow interiors of the rotor blades 42, the air finally discharged through openings 56 along the trailing edges of the blades into the working fluid passage. The air passing through the openings 54 in the rotor disc 40 enters the chamber 70 formed between the rotor discs 40, 60, the air passing through openings 72 into the space defined between side plates 66, 68 of the second rotor disc 60, the air then passing into the hollow rotor blades 62 of the turbine disc 60, finally discharging through openings at the blade tips. Seal means are provided at 22, 32. Some air leaking through the seal 32 flows as indicated by arrows through openings 94 in the rotor shaft 41 to cool the downstream face of the disc 60.
GB26584/71A 1970-04-28 1971-04-19 Gas turbine engine constructions Expired GB1284858A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US3268770A 1970-04-28 1970-04-28

Publications (1)

Publication Number Publication Date
GB1284858A true GB1284858A (en) 1972-08-09

Family

ID=21866294

Family Applications (1)

Application Number Title Priority Date Filing Date
GB26584/71A Expired GB1284858A (en) 1970-04-28 1971-04-19 Gas turbine engine constructions

Country Status (4)

Country Link
CA (1) CA939521A (en)
DE (1) DE2119024A1 (en)
FR (1) FR2086406A1 (en)
GB (1) GB1284858A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2449789A1 (en) * 1979-02-26 1980-09-19 Gen Electric TURBOMACHINE WITH IMPROVED SEAL COOLING STRUCTURE
GB2151715A (en) * 1983-12-22 1985-07-24 United Technologies Corp Two stage rotor assembly with improved coolant flow
GB2189845A (en) * 1986-04-30 1987-11-04 Gen Electric Gas turbine cooling air transferring apparatus
EP0266297A2 (en) * 1986-10-28 1988-05-04 United Technologies Corporation Cooling air manifold for a gas turbine engine
US4852355A (en) * 1980-12-22 1989-08-01 General Electric Company Dispensing arrangement for pressurized air
US5245821A (en) * 1991-10-21 1993-09-21 General Electric Company Stator to rotor flow inducer
EP3012405A3 (en) * 2014-09-04 2016-07-27 United Technologies Corporation Coolant flow redirection component

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4348157A (en) * 1978-10-26 1982-09-07 Rolls-Royce Limited Air cooled turbine for a gas turbine engine
GB2057573A (en) * 1979-08-30 1981-04-01 Rolls Royce Turbine rotor assembly
DE3014279A1 (en) * 1980-04-15 1981-10-22 M.A.N. Maschinenfabrik Augsburg-Nürnberg AG, 4200 Oberhausen DEVICE FOR COOLING THE INSIDE OF A GAS TURBINE
GB2089894B (en) * 1980-12-22 1985-08-14 Gen Electric Gas turbine engine air dispensing arrangement
US4435123A (en) * 1982-04-19 1984-03-06 United Technologies Corporation Cooling system for turbines
DE4433289A1 (en) * 1994-09-19 1996-03-21 Abb Management Ag Axial gas turbine

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2449789A1 (en) * 1979-02-26 1980-09-19 Gen Electric TURBOMACHINE WITH IMPROVED SEAL COOLING STRUCTURE
US4852355A (en) * 1980-12-22 1989-08-01 General Electric Company Dispensing arrangement for pressurized air
GB2151715A (en) * 1983-12-22 1985-07-24 United Technologies Corp Two stage rotor assembly with improved coolant flow
GB2189845A (en) * 1986-04-30 1987-11-04 Gen Electric Gas turbine cooling air transferring apparatus
GB2189845B (en) * 1986-04-30 1991-01-23 Gen Electric Turbine cooling air transferring apparatus
EP0266297A2 (en) * 1986-10-28 1988-05-04 United Technologies Corporation Cooling air manifold for a gas turbine engine
EP0266297A3 (en) * 1986-10-28 1990-01-10 United Technologies Corporation Cooling air manifold for a gas turbine engine
US5245821A (en) * 1991-10-21 1993-09-21 General Electric Company Stator to rotor flow inducer
EP3012405A3 (en) * 2014-09-04 2016-07-27 United Technologies Corporation Coolant flow redirection component
US9890645B2 (en) 2014-09-04 2018-02-13 United Technologies Corporation Coolant flow redirection component
EP3553276A1 (en) * 2014-09-04 2019-10-16 United Technologies Corporation Coolant flow redirection component
US10822953B2 (en) 2014-09-04 2020-11-03 Raytheon Technologies Corporation Coolant flow redirection component

Also Published As

Publication number Publication date
FR2086406A1 (en) 1971-12-31
DE2119024A1 (en) 1971-11-11
CA939521A (en) 1974-01-08

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee