GB622369A - Improvements relating to gas turbine engines - Google Patents

Improvements relating to gas turbine engines

Info

Publication number
GB622369A
GB622369A GB706347A GB706347A GB622369A GB 622369 A GB622369 A GB 622369A GB 706347 A GB706347 A GB 706347A GB 706347 A GB706347 A GB 706347A GB 622369 A GB622369 A GB 622369A
Authority
GB
United Kingdom
Prior art keywords
rotor
compressor
chamber
gas turbine
thrust
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
GB706347A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to GB706347A priority Critical patent/GB622369A/en
Publication of GB622369A publication Critical patent/GB622369A/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
    • F02C7/28—Arrangement of seals
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam

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

622,369. Gas turbine plant for jet-propulsion. LOMBARD, A. A. March 13,1947, No. 7063. [Classes 110(i) and 110(iii)] In a gas turbine plant for jet-propulsion, air from the compressor delivery is led to the inlet side of the turbine disc rim to prevent inward flow of hot gases. A balancing piston and other areas are provided to balance the end-thrust in a turbine plant with an axial flow compressor. The delivery end of a compressor rotor 10 is sealed by labyrinth packings on both surfaces of an annular extension 26 of the rotor. Air leaking past the packings enters a chamber P, which is sealed by a packing 30, and is led by a conduit 31 to a chamber Q. A packing 33, between the turbine rotor 16 and a casing part 25A, seals the chamber Q on its inner side. On its outer side the chamber is open at the gap between the casing and the rotor rim. An end-thrust balancing piston 35 is secured to the compressor rotor 10 and is subjected on one side to the pressure of air which passes through a port 37. The compressor and turbine shafts are connected by a universal coupling 20 which can transmit end thrust from one shaft to the other.
GB706347A 1947-03-13 1947-03-13 Improvements relating to gas turbine engines Expired GB622369A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB706347A GB622369A (en) 1947-03-13 1947-03-13 Improvements relating to gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB706347A GB622369A (en) 1947-03-13 1947-03-13 Improvements relating to gas turbine engines

Publications (1)

Publication Number Publication Date
GB622369A true GB622369A (en) 1949-05-02

Family

ID=9825901

Family Applications (1)

Application Number Title Priority Date Filing Date
GB706347A Expired GB622369A (en) 1947-03-13 1947-03-13 Improvements relating to gas turbine engines

Country Status (1)

Country Link
GB (1) GB622369A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2648866A1 (en) * 1989-06-23 1990-12-28 United Technologies Corp DEVICE FOR CONTROLLING A LEAK AIR FLOW IN A TURBOMOTEUR
EP2570633A3 (en) * 2011-09-16 2017-03-15 United Technologies Corporation Thrust bearing system with inverted non-contacting dynamic seals for gas turbine engine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2648866A1 (en) * 1989-06-23 1990-12-28 United Technologies Corp DEVICE FOR CONTROLLING A LEAK AIR FLOW IN A TURBOMOTEUR
GB2235019A (en) * 1989-06-23 1991-02-20 United Technologies Corp Seal vent bypass conduit for gas turbine engine
EP2570633A3 (en) * 2011-09-16 2017-03-15 United Technologies Corporation Thrust bearing system with inverted non-contacting dynamic seals for gas turbine engine
US10119476B2 (en) 2011-09-16 2018-11-06 United Technologies Corporation Thrust bearing system with inverted non-contacting dynamic seals for gas turbine engine

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