GB755411A - Improvements relating to gas turbine engines - Google Patents

Improvements relating to gas turbine engines

Info

Publication number
GB755411A
GB755411A GB36334/54A GB3633454A GB755411A GB 755411 A GB755411 A GB 755411A GB 36334/54 A GB36334/54 A GB 36334/54A GB 3633454 A GB3633454 A GB 3633454A GB 755411 A GB755411 A GB 755411A
Authority
GB
United Kingdom
Prior art keywords
ring
air
secured
flange
channel
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
GB36334/54A
Inventor
Wilgus S Broffitt
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.)
Motors Liquidation Co
Original Assignee
Motors Liquidation 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
Priority to US359746A priority Critical patent/US2811833A/en
Application filed by Motors Liquidation Co filed Critical Motors Liquidation Co
Priority to GB36334/54A priority patent/GB755411A/en
Priority to CH325612D priority patent/CH325612A/en
Publication of GB755411A publication Critical patent/GB755411A/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
    • 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
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

755,411. Gas turbine engines. GENERAL MOTORS CORPORATION. Dec. 15, 1954, No. 36334/54. Class 110(3) In a gas turbine engine, means are provided for conducting cooling air to the turbine rotor and include a rotatable ring valve having passages therethrough for controlling delivery of the cooling air. The gas turbine jet propulsion engine shown comprises a centrifugal compressor rotor 10 driven by turbine rotor 12 by means of a splined coupling 60, the shafts being mounted in bearings 14. The outer frame member 42 has a ring flange member 62 secured thereto and the flange has a channel-shaped ring member 66 secured thereto by bolts 74. Angle section ring members 68, 70, 72 are secured to the channel member 66 by the bolts 74. The turbine nozzle inner ring 76 is secured to the angle section ring 68 and inlet nozzle vanes 56 are welded between the inner ring 76 and outer ring 78. The angle-section rings 70, 72 define an annular space A to which cooling air is fed through conduits 90 from the air spaces between the combustion chamber outer casings 52 and the frame tubes 50, the air passing from the space A through the passage 96 in the turbine rotor and into the hollow rotor blades 58 through inlets 98 in the roots thereof, the air finally discharging through outlets 102 in the blades. The air from the conduits 90 passes through openings D in the flange 62 to the annular space B formed by the channel 66, the air supply being controlled by a ring member 92 having ports E therein which is rotatably mounted between the flange 62 and the channel 66. The ring valve is operated by means of a geared sector 110 which engages an internally toothed portion of the ring valve, the sector being mounted on a shaft 114 which is rotatable in bearings 120, 122. The rod 114 is operable by means of a rod 134 through a link 116, movement being limited by means of a pair of stops engageable by a lug. The valve may be operated by the throttle of the engine or by manual action so that greater cooling is provided at increased power. Sealing means 104, 106 are provided on the angle-section rings 70, 72 to prevent leakage from the space A.
GB36334/54A 1953-06-05 1954-12-15 Improvements relating to gas turbine engines Expired GB755411A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US359746A US2811833A (en) 1953-06-05 1953-06-05 Turbine cooling
GB36334/54A GB755411A (en) 1954-12-15 1954-12-15 Improvements relating to gas turbine engines
CH325612D CH325612A (en) 1954-12-15 1954-12-22 Gas turbine plant

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB36334/54A GB755411A (en) 1954-12-15 1954-12-15 Improvements relating to gas turbine engines

Publications (1)

Publication Number Publication Date
GB755411A true GB755411A (en) 1956-08-22

Family

ID=10387194

Family Applications (1)

Application Number Title Priority Date Filing Date
GB36334/54A Expired GB755411A (en) 1953-06-05 1954-12-15 Improvements relating to gas turbine engines

Country Status (2)

Country Link
CH (1) CH325612A (en)
GB (1) GB755411A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1106557B (en) * 1957-07-18 1961-05-10 Rolls Royce Gas turbine, the rotor blades of which have inner cooling ducts
EP0203353A1 (en) * 1985-04-20 1986-12-03 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Cooled gas turbine with a load-dependent, controllable quantity of cooling air

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1106557B (en) * 1957-07-18 1961-05-10 Rolls Royce Gas turbine, the rotor blades of which have inner cooling ducts
EP0203353A1 (en) * 1985-04-20 1986-12-03 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Cooled gas turbine with a load-dependent, controllable quantity of cooling air

Also Published As

Publication number Publication date
CH325612A (en) 1957-11-15

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