GB585331A - Improvements in or relating to internal-combustion turbines - Google Patents

Improvements in or relating to internal-combustion turbines

Info

Publication number
GB585331A
GB585331A GB492341A GB492341A GB585331A GB 585331 A GB585331 A GB 585331A GB 492341 A GB492341 A GB 492341A GB 492341 A GB492341 A GB 492341A GB 585331 A GB585331 A GB 585331A
Authority
GB
United Kingdom
Prior art keywords
air
blades
channel
turbine
compressor
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
GB492341A
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 GB492341A priority Critical patent/GB585331A/en
Publication of GB585331A publication Critical patent/GB585331A/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
    • F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/023—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines the working-fluid being divided into several separate flows ; several separate fluid flows being united in a single flow; the machine or engine having provision for two or more different possible fluid flow paths

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

585,331. Gas turbines. GRIFFITH, A. A. April 15, 1841, No. 4923. [Class 110 (iii)] Gas turbine blades have hollow shroud rings into which cooling air is admitted. In the turbine shown, the inner blades 12, on the independent and oppositely rotating discs 11, form the air compressor and the outer blades 16 are those of the turbine. The turbine blades are secured upon rings forming the shrouding for the compressor blades and these rings are made of parts 14, 15 separated by an annular air space. The air spaces of the several rings form a continuous annular air channel. Air may be admitted to this channel from the compressor delivery and evacuated to atmosphere by a channel 20. Or, it may be left to escape into the compressor and turbine bladings. In the former case, blades may be provided in the annular channel to cause the air to do work. In the latter case, the leakage outlets direct the air suitably into the air and gas streams. Alternatively, a low pressure may be maintained in the annular channel and any gases leaking into it are withdrawn. Specification 583,330 is referred to.
GB492341A 1941-04-15 1941-04-15 Improvements in or relating to internal-combustion turbines Expired GB585331A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB492341A GB585331A (en) 1941-04-15 1941-04-15 Improvements in or relating to internal-combustion turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB492341A GB585331A (en) 1941-04-15 1941-04-15 Improvements in or relating to internal-combustion turbines

Publications (1)

Publication Number Publication Date
GB585331A true GB585331A (en) 1947-02-05

Family

ID=9786407

Family Applications (1)

Application Number Title Priority Date Filing Date
GB492341A Expired GB585331A (en) 1941-04-15 1941-04-15 Improvements in or relating to internal-combustion turbines

Country Status (1)

Country Link
GB (1) GB585331A (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2801789A (en) * 1954-11-30 1957-08-06 Power Jets Res & Dev Ltd Blading for gas turbine engines
US2971745A (en) * 1958-03-21 1961-02-14 Gen Electric Fabricated blade and bucket rotor assembly
US3186166A (en) * 1958-11-26 1965-06-01 Daimler Benz Ag Gas turbine drive unit
EP0021459A1 (en) * 1979-04-10 1981-01-07 Hendrik Janus Bakker Turbinedriven turbocompressor
FR2597547A1 (en) * 1985-05-29 1987-10-23 Chanay Paul Air supercharger for combustion engines
EP0803640A1 (en) * 1996-04-24 1997-10-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Double flow turbomachine
EP0900920A3 (en) * 1997-09-08 2000-03-22 General Electric Company Sealing device between a blade platform and two stator shrouds
US6454535B1 (en) 2000-10-31 2002-09-24 General Electric Company Blisk
RU2634509C2 (en) * 2016-03-22 2017-10-31 Публичное акционерное общество "Уфимское моторостроительное производственное объединение" ПАО "УМПО" Three-tier working blade of turbo-fan

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2801789A (en) * 1954-11-30 1957-08-06 Power Jets Res & Dev Ltd Blading for gas turbine engines
US2971745A (en) * 1958-03-21 1961-02-14 Gen Electric Fabricated blade and bucket rotor assembly
US3186166A (en) * 1958-11-26 1965-06-01 Daimler Benz Ag Gas turbine drive unit
EP0021459A1 (en) * 1979-04-10 1981-01-07 Hendrik Janus Bakker Turbinedriven turbocompressor
FR2597547A1 (en) * 1985-05-29 1987-10-23 Chanay Paul Air supercharger for combustion engines
EP0803640A1 (en) * 1996-04-24 1997-10-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Double flow turbomachine
FR2748063A1 (en) * 1996-04-24 1997-10-31 Snecma DOUBLE FLOW TURBOMACHINE
US5822975A (en) * 1996-04-24 1998-10-20 Societe National D'etude Et De Auction De Moteurs D'aviation "Snecma" Bypass engine with means for limiting gas leakage
EP0900920A3 (en) * 1997-09-08 2000-03-22 General Electric Company Sealing device between a blade platform and two stator shrouds
US6454535B1 (en) 2000-10-31 2002-09-24 General Electric Company Blisk
RU2634509C2 (en) * 2016-03-22 2017-10-31 Публичное акционерное общество "Уфимское моторостроительное производственное объединение" ПАО "УМПО" Three-tier working blade of turbo-fan

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