GB1126707A - By-pass gas turbine jet propulsion engine - Google Patents

By-pass gas turbine jet propulsion engine

Info

Publication number
GB1126707A
GB1126707A GB3803766A GB3803766A GB1126707A GB 1126707 A GB1126707 A GB 1126707A GB 3803766 A GB3803766 A GB 3803766A GB 3803766 A GB3803766 A GB 3803766A GB 1126707 A GB1126707 A GB 1126707A
Authority
GB
United Kingdom
Prior art keywords
engine
turbine
pass
compressor
combustion equipment
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
GB3803766A
Inventor
John Bertram Holliday
Herbert Frank Smith
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB3803766A priority Critical patent/GB1126707A/en
Publication of GB1126707A publication Critical patent/GB1126707A/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
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/105—Heating the by-pass flow
    • F02K3/11—Heating the by-pass flow by means of burners or combustion chambers

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Abstract

1,126,707. Gas turbine by-pass type jet engines. ROLLS-ROYCE Ltd. Aug. 17, 1967 [Aug. 24, 1966], No.38037/66. Addition to 1,069,033. Headings F1J and F1L. The invention relates to a gas turbine jet propulsion engine in which a portion of the air compressed by the compressor system of the engine is arranged to by-pass the high pressure compressor, combustion equipment and high pressure turbine system of the engine, the by-pass air flow being passed to a low pressure turbine of the engine, combustion equipment being provided in the bypass air flow duct. Means are provided for rotating the combustion equipment in the by-pass duct, and control means are provided for varying the amount of fuel supplied to the combustion equipment in the by-pass duct so as to vary the effective by-pass ratio of the engine. In the embodiment shown the engine comprises LP compressor 10, HP compressor 4, combustion equipment 5, HP turbine 6, IP turbine 11 and LP turbine 12, the HP turbine being connected to drive the HP compressor through shaft 7, and the IP and LP turbines being connected together and connected through shaft 13 to drive the LP compressor. A portion of air from the LP compressor passes through the by-pass duct 3 to act on the radially outer part of the LP turbine 12, there being combustion equipment in the by-pass duct. The combustion equipment in the by-pass duct comprises a series of angularly-spaced apart combustion stabilizing gutter means 20 and associated fuel injectors 22, which assembly is rotatable about the engine axis. The rotary assembly comprises a shaft 16 which carries a hub member 17 and a series of blades 21, the blades each being formed integrally with a gutter member 20, the blades 21 being located in the air flow duct between the LP and HP compressors whereby the assembly is rotated. Fuel is supplied to an annular recess 23 within the hub member 17 and then flows through passages 27 in the blades and gutters to the injectors 22. Fuel flow to the assembly is controlled by a valve 26. The arrangement is such that no fuel is supplied to the injectors 22 until the engine has been brought to full operation, the number of injectors 22 supplied with fuel always depending upon the rotational speed of the engine.
GB3803766A 1966-08-24 1966-08-24 By-pass gas turbine jet propulsion engine Expired GB1126707A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3803766A GB1126707A (en) 1966-08-24 1966-08-24 By-pass gas turbine jet propulsion engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3803766A GB1126707A (en) 1966-08-24 1966-08-24 By-pass gas turbine jet propulsion engine

Publications (1)

Publication Number Publication Date
GB1126707A true GB1126707A (en) 1968-09-11

Family

ID=10400751

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3803766A Expired GB1126707A (en) 1966-08-24 1966-08-24 By-pass gas turbine jet propulsion engine

Country Status (1)

Country Link
GB (1) GB1126707A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0022692A1 (en) * 1979-07-16 1981-01-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Turbofan with variable by-pass ratio

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0022692A1 (en) * 1979-07-16 1981-01-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Turbofan with variable by-pass ratio
FR2461820A1 (en) * 1979-07-16 1981-02-06 Snecma MULTIFLUX TURBOREACTOR WITH A DILUTION RATE

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