GB650661A - Jet reaction propulsion unit for aircraft - Google Patents

Jet reaction propulsion unit for aircraft

Info

Publication number
GB650661A
GB650661A GB819/41A GB81941A GB650661A GB 650661 A GB650661 A GB 650661A GB 819/41 A GB819/41 A GB 819/41A GB 81941 A GB81941 A GB 81941A GB 650661 A GB650661 A GB 650661A
Authority
GB
United Kingdom
Prior art keywords
turbine
compressor
driven
jet
stage
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
GB819/41A
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.)
Rateau SA
Original Assignee
Rateau SA
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 Rateau SA filed Critical Rateau SA
Publication of GB650661A publication Critical patent/GB650661A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16Control of working fluid flow
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K3/00Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02Plants 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
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient propulsion technologies, e.g. for aircraft

Landscapes

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

Abstract

650,661. Jet propulsion plant; axial-flow compressors. SOC. RATEAU, and ANXIONNAZ, R. Jan. 21,1941, No. 819. Convention date, Dec. 4, 1939. '[Classes 110(i) and 1l0(iii)] [Also in Group XXXIII] A jet reaction propulsion unit has a fore and aft casing with its inlet at the forward end arranged so that the velocity of the air is reduced on entry before reaching the blades of an axially arranged axial flow compressor. The compressor is driven either by a gas turbine 34 or by a piston engine, and the compressed gas may be heated by burners 31 or by the engine oil and water coolers or the exhaust of the turbine or engine. The compressor may have two stages, Fig. 15, each stage being driven by a separate turbine 46, 48, only part of the output of the first stage 40 passing to the second stage and the combustion chamber 32. In a further modification both stages are driven by the same turbine and the initial stage driven at a lower speed through reduction gearing.' The exhaust gas may be cooled by air admitted through the side inlet 36, Fig. 12. The turbine is started by the engine 64 or by injecting and burning air from compressed air bottles in the combustion chamber. To vary the operating conditions of the compressor a row of blading 65, Fig. 3a, may be held stationary by brakes 70 or may be freed to run idly. Adjustable deflecting blades can be fitted in the outlet to varying the. direction of the jet thrust, or for using the jet to brake the aircraft. Specifications 471,368 and 650,710 are referred to. Reference has been directed by the Comptroller to Specification 471.368.
GB819/41A 1939-12-04 1941-01-21 Jet reaction propulsion unit for aircraft Expired GB650661A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR650661X 1939-12-04

Publications (1)

Publication Number Publication Date
GB650661A true GB650661A (en) 1951-02-28

Family

ID=9004117

Family Applications (1)

Application Number Title Priority Date Filing Date
GB819/41A Expired GB650661A (en) 1939-12-04 1941-01-21 Jet reaction propulsion unit for aircraft

Country Status (1)

Country Link
GB (1) GB650661A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2148395A (en) * 1983-10-24 1985-05-30 Mannesmann Ag Brakes for multistage compressors
EP1160432A1 (en) 2000-05-31 2001-12-05 Daniel Bregentzer Gas turbine engine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2148395A (en) * 1983-10-24 1985-05-30 Mannesmann Ag Brakes for multistage compressors
EP1160432A1 (en) 2000-05-31 2001-12-05 Daniel Bregentzer Gas turbine engine

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