GB585342A - Compound internal-combustion turbine plant - Google Patents

Compound internal-combustion turbine plant

Info

Publication number
GB585342A
GB585342A GB1362942A GB1362942A GB585342A GB 585342 A GB585342 A GB 585342A GB 1362942 A GB1362942 A GB 1362942A GB 1362942 A GB1362942 A GB 1362942A GB 585342 A GB585342 A GB 585342A
Authority
GB
United Kingdom
Prior art keywords
rings
jet
turbine plant
combustion 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
GB1362942A
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.)
Armstrong Siddeley Motors Ltd
Original Assignee
Armstrong Siddeley Motors 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 Armstrong Siddeley Motors Ltd filed Critical Armstrong Siddeley Motors Ltd
Priority to GB1362942A priority Critical patent/GB585342A/en
Publication of GB585342A publication Critical patent/GB585342A/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
    • 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
    • F02C3/067—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 having counter-rotating rotors
    • 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
    • F02K3/072—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 counter-rotating, e.g. fan rotors

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

585,342. Gas turbines. ARMSTRONG SIDDELEY MOTORS, Ltd., and HEPPNER, F. A. M. Sept. 29, 1942, No. 13629. [Class 110 (iii)] The blade rings 17, 18, 19 of a contrarotational turbine are carried by independently mounted stage motors 20, 21, 22 of the associated air-compressor. The rings 18, 19 and the corresponding end' rings on the compressor stages 21, 22 are separated by stationary blade rings. The designed speeds of the compressor stages diminish progressively from the highpressure to the low-pressure. The outer turbine rotor 13 may be geared as shown to drive a' shaft 44 or may carry the running blades of a jet-augmenter for use in the jet-propulsion of aircraft. Specifications 585,340 and 585,343 are referred to.
GB1362942A 1942-09-29 1942-09-29 Compound internal-combustion turbine plant Expired GB585342A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1362942A GB585342A (en) 1942-09-29 1942-09-29 Compound internal-combustion turbine plant

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1362942A GB585342A (en) 1942-09-29 1942-09-29 Compound internal-combustion turbine plant

Publications (1)

Publication Number Publication Date
GB585342A true GB585342A (en) 1947-02-05

Family

ID=10026494

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1362942A Expired GB585342A (en) 1942-09-29 1942-09-29 Compound internal-combustion turbine plant

Country Status (1)

Country Link
GB (1) GB585342A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2606081A1 (en) * 1986-10-29 1988-05-06 Snecma PROPULSION ENGINE WITH CONTRAROTATING WORKING TURBINES
EP0395497A1 (en) * 1989-04-26 1990-10-31 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Counter rotating prop-fan engine

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2606081A1 (en) * 1986-10-29 1988-05-06 Snecma PROPULSION ENGINE WITH CONTRAROTATING WORKING TURBINES
EP0270403A1 (en) * 1986-10-29 1988-06-08 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Propulsion engine with contrarotating power turbines
US4765135A (en) * 1986-10-29 1988-08-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Gas turbine engine
EP0395497A1 (en) * 1989-04-26 1990-10-31 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Counter rotating prop-fan engine
FR2646473A1 (en) * 1989-04-26 1990-11-02 Snecma ENGINE WITH TRACTRIC CONTROTOTATIVE BLOWERS
US5105618A (en) * 1989-04-26 1992-04-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Counterrotating fan engine

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