GB774502A - Gas turbine plant - Google Patents

Gas turbine plant

Info

Publication number
GB774502A
GB774502A GB1935754A GB1935754A GB774502A GB 774502 A GB774502 A GB 774502A GB 1935754 A GB1935754 A GB 1935754A GB 1935754 A GB1935754 A GB 1935754A GB 774502 A GB774502 A GB 774502A
Authority
GB
United Kingdom
Prior art keywords
blades
turbine
slits
ring
blade
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
GB1935754A
Inventor
Sydney William Henry Perry
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.)
Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development Ltd
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 Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Priority to GB1935754A priority Critical patent/GB774502A/en
Publication of GB774502A publication Critical patent/GB774502A/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
    • 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
    • F02C3/073—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 the compressor and turbine stages being concentric
    • 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
    • F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/062—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with aft fan

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

774,502. Gas-turbine plant. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. June 30, 1955 [July 1, 1954], No. 19357/54. Class 110 (3). In a gas-turbine power plant comprising a rotor carrying two concentric rows of blades one within the other, the two rows operating at different temperatures, the blades of the blade row operating at the lower temperature are mounted at their ends nearest the other blade row on an annular support member to which is connected one end of an axiallyextending ring which is formed with a plurality of axially-extending slits open at the other end of the ring. The slits provide between them a plurality of flexible fingers, the end of each finger being secured to one of the blades of the other blade row at the end of that blade nearer the first-mentioned blades. The gas-turbine plant shown is of the ducted-fan type and comprises two contra-rotating turbine rotors 4, 6, the turbine 4 being connected through shaft 5 to the compressor 3, and the turbine 6 being connected to the ducted fan blades 7 which are disposed in the duct 8. The blades 6a mounted on the rotor disc 6 have tip shrouds 6b which are not connected with each other. A thin sheet metal frusto-conical ring 10 having flanges 10a, 10e at its ends is formed with axial slits 10b (see Fig. 3), the slits forming axial fingers 10d and the flange 10e on each finger 10d is secured to a blade tip shroud 6b. The other flange 10a of the ring 10 is secured to a built-up annular support member 9 which is formed with a groove 9a in which the roost of the ductedfan blades 7 are mounted. A second ring member 11 having axial slits 11b forming fingers 11a is secured by flanges on the fingers 11a to the individual tip shrouds 6b. Interengaging sealing rings 9c and 1b are mounted on the support member 9 and combustion chamber outer casing 1a respectively. Cooling air flows from the space between the combustion chamber casing 1a and the wall 2 of the annular flame tube between the blade shrouds 6b, 4b and the support member 9 through the slits 10b, 11b in the rings 10, 11. The outer wall 13 of the ducted fan is connected by struts 14 to the combustion chamber casing 1a, and carries a row of stationary blades 15. The invention is also applicable in the case of gas-turbine plant in which the annular compressor flow channel is disposed around the annular turbine flow channel. Specification 774,503 is referred to.
GB1935754A 1954-07-01 1954-07-01 Gas turbine plant Expired GB774502A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1935754A GB774502A (en) 1954-07-01 1954-07-01 Gas turbine plant

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1935754A GB774502A (en) 1954-07-01 1954-07-01 Gas turbine plant

Publications (1)

Publication Number Publication Date
GB774502A true GB774502A (en) 1957-05-08

Family

ID=10128000

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1935754A Expired GB774502A (en) 1954-07-01 1954-07-01 Gas turbine plant

Country Status (1)

Country Link
GB (1) GB774502A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3024601A (en) * 1960-04-12 1962-03-13 Gen Electric Thrust spoiler and reingestion control
EP0073689A1 (en) * 1981-08-31 1983-03-09 Elliott Turbomachinery Company, Inc. Method and apparatus for controlling thermal growth
GB2129502A (en) * 1982-11-01 1984-05-16 Gen Electric Counter rotation power turbine
US4790133A (en) * 1986-08-29 1988-12-13 General Electric Company High bypass ratio counterrotating turbofan engine
US4860537A (en) * 1986-08-29 1989-08-29 Brandt, Inc. High bypass ratio counterrotating gearless front fan engine
FR2644515A1 (en) * 1989-03-20 1990-09-21 Gen Electric POWER TURBINE ASSEMBLY
GB2230821A (en) * 1989-04-11 1990-10-31 Gen Electric Aircraft propulsion system
US5079916A (en) * 1982-11-01 1992-01-14 General Electric Company Counter rotation power turbine

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3024601A (en) * 1960-04-12 1962-03-13 Gen Electric Thrust spoiler and reingestion control
EP0073689A1 (en) * 1981-08-31 1983-03-09 Elliott Turbomachinery Company, Inc. Method and apparatus for controlling thermal growth
GB2129502A (en) * 1982-11-01 1984-05-16 Gen Electric Counter rotation power turbine
GB2129502B (en) * 1982-11-01 1989-10-18 Gen Electric Aircraft engine having a counter rotation power turbine
US5079916A (en) * 1982-11-01 1992-01-14 General Electric Company Counter rotation power turbine
US4790133A (en) * 1986-08-29 1988-12-13 General Electric Company High bypass ratio counterrotating turbofan engine
US4860537A (en) * 1986-08-29 1989-08-29 Brandt, Inc. High bypass ratio counterrotating gearless front fan engine
FR2644515A1 (en) * 1989-03-20 1990-09-21 Gen Electric POWER TURBINE ASSEMBLY
GB2230821A (en) * 1989-04-11 1990-10-31 Gen Electric Aircraft propulsion system
US5112191A (en) * 1989-04-11 1992-05-12 General Electric Company Rotating cowling

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