GB1069706A - Gas turbine engines with axial-flow turbine wheels - Google Patents

Gas turbine engines with axial-flow turbine wheels

Info

Publication number
GB1069706A
GB1069706A GB9303/66A GB930366A GB1069706A GB 1069706 A GB1069706 A GB 1069706A GB 9303/66 A GB9303/66 A GB 9303/66A GB 930366 A GB930366 A GB 930366A GB 1069706 A GB1069706 A GB 1069706A
Authority
GB
United Kingdom
Prior art keywords
wall
tangs
downstream
secured
extension
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
GB9303/66A
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
Application filed by Motors Liquidation Co filed Critical Motors Liquidation Co
Publication of GB1069706A publication Critical patent/GB1069706A/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
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • 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
    • F01D5/021—Blade-carrying members, e.g. rotors for flow machines or engines with only one axial stage
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,069,706. Turbines. GENERAL MOTORS CORPORATION. March 3, 1966 [March 22, 1965], No. 9303/66. Heading F1T. A gas turbine vertical lift engine has an axial flow turbine rotor wheel 32 with blades 36 having roots fitting in axial slots 34 in the wheel rim, each blade having a platform with a downstream extension 50, and the adjacent platforms abutting so that the extensions form the inner wall 68 of the turbine exhaust duct (92), Fig. 1 (not shown). The platform (44) of each blade 36, Fig. 3 (not shown), is spaced from the root (38) by a stalk 56 having cooling air inlets 54 to the hollow aerofoil portion 60. A web (70) extends from the downstream end of stalk 56 to support the extension 50. An annular concave wall 72 is mounted on the rotor wheel adjacent the webs (70) by engagement of a flange 78 on the wall under tangs (42) on the downstream side of the blade roots. Castellations at the downstream end of the wall 72 engage with corresponding castellations (76) in a lip 52 on each extension 50 with freedom for sliding. A backplate 80 is secured to the inner extremity of wall 72 by loosely fitting pins 89. The cupped centre 82 of the backplate is secured to the rotor wheel 32 by a screw member 84. The tangs (42) prevent movement of the blades out of their slots 34 in the upstream direction and similar tangs 40 engaged by rings 94 prevent movement of the blades in the downstream direction. The outer wall (28) of the exhaust duct (92) is secured to the casing (12, 14) surrounding the reverse flow combustion chamber (17) by straps (30) held in position by the fuel nozzles (18).
GB9303/66A 1965-03-22 1966-03-03 Gas turbine engines with axial-flow turbine wheels Expired GB1069706A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US441513A US3333818A (en) 1965-03-22 1965-03-22 Turbine rotor-jet nozzle assembly

Publications (1)

Publication Number Publication Date
GB1069706A true GB1069706A (en) 1967-05-24

Family

ID=23753171

Family Applications (1)

Application Number Title Priority Date Filing Date
GB9303/66A Expired GB1069706A (en) 1965-03-22 1966-03-03 Gas turbine engines with axial-flow turbine wheels

Country Status (2)

Country Link
US (1) US3333818A (en)
GB (1) GB1069706A (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2956626B1 (en) * 2013-02-12 2019-11-20 United Technologies Corporation Fan blade including external cavities

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2656146A (en) * 1948-04-08 1953-10-20 Curtiss Wright Corp Turbine blade construction
BE540433A (en) * 1954-08-12

Also Published As

Publication number Publication date
US3333818A (en) 1967-08-01

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