GB851153A - Gas turbine jet-propulsion engine of the by-pass type - Google Patents

Gas turbine jet-propulsion engine of the by-pass type

Info

Publication number
GB851153A
GB851153A GB826258A GB826258A GB851153A GB 851153 A GB851153 A GB 851153A GB 826258 A GB826258 A GB 826258A GB 826258 A GB826258 A GB 826258A GB 851153 A GB851153 A GB 851153A
Authority
GB
United Kingdom
Prior art keywords
pass
pipes
turbine
air
gas turbine
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
GB826258A
Inventor
John Gregory Keenan
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 GB826258A priority Critical patent/GB851153A/en
Publication of GB851153A publication Critical patent/GB851153A/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
    • F02K3/02—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
    • F02K3/06—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 front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/52—Nozzles specially constructed for positioning adjacent to another nozzle or to a fixed member, e.g. fairing
    • 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)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)

Abstract

851.153. Gas turbine jet propulsion engines. ROLLS-ROYCE Ltd. Dec. 9, 1958 [March 14, 1958], No. 8262/58. Class 110 (3). In a gas turbine jet propulsion plant containing a compressor, combustion apparatus and a turbine, having a main conduit, a by-pass duct branching from the main conduit on the upstream side of the combustion chambers so as to by-pass the combustion chamber and the turbine, the by-pass duct 19 comprises two spaced apart by-pass pipes which are arranged to receive the whole of the by-pass air, the bypass pipes extending longitudinally of the main jet pipe 16 and terminating short of the downstream end thereof. The by-pass pipes are of arcuate shape in section and are arranged to fit closely about the main jet pipe. As shown the by-pass pipes are supplied with air from a compressor 11 which is driven by a low pressure turbine 15, and which also supplies air to a high pressure compressor 12, driven by a high pressure turbine 14. The by-pass pipes are provided with means 23 to heat the by-pass air when additional thrust is required, and have variable area nozzles 25 and eyelid type thrust reversers 26. Specification 745,649 is referred to.
GB826258A 1958-03-14 1958-03-14 Gas turbine jet-propulsion engine of the by-pass type Expired GB851153A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB826258A GB851153A (en) 1958-03-14 1958-03-14 Gas turbine jet-propulsion engine of the by-pass type

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB826258A GB851153A (en) 1958-03-14 1958-03-14 Gas turbine jet-propulsion engine of the by-pass type

Publications (1)

Publication Number Publication Date
GB851153A true GB851153A (en) 1960-10-12

Family

ID=9849126

Family Applications (1)

Application Number Title Priority Date Filing Date
GB826258A Expired GB851153A (en) 1958-03-14 1958-03-14 Gas turbine jet-propulsion engine of the by-pass type

Country Status (1)

Country Link
GB (1) GB851153A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3176463A (en) * 1960-09-27 1965-04-06 Snecma Flight control and stabilization by hot jets, applicable in particular to aircraft taking off vertically without change of attitude
US3181293A (en) * 1961-03-06 1965-05-04 Bristol Siddeley Engines Ltd Fluid fuel burning equipment
US3292374A (en) * 1963-03-29 1966-12-20 Rolls Royce Gas turbine engine and aircraft provided therwith
US3349560A (en) * 1967-10-31 Gas turbine by-pass jet engine
US3517898A (en) * 1966-12-30 1970-06-30 Sud Aviat Soc Nationale De Con Lift and propulsion device for a jet aircraft of the hybrid helicopter-autogyro type
US3601990A (en) * 1968-06-24 1971-08-31 Rolls Royce Gas turbine jet propulsion engine
RU2716651C2 (en) * 2018-03-30 2020-03-13 Артём Георгиевич Арутюнов Double-flow turbojet engine nozzles system

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3349560A (en) * 1967-10-31 Gas turbine by-pass jet engine
US3176463A (en) * 1960-09-27 1965-04-06 Snecma Flight control and stabilization by hot jets, applicable in particular to aircraft taking off vertically without change of attitude
US3181293A (en) * 1961-03-06 1965-05-04 Bristol Siddeley Engines Ltd Fluid fuel burning equipment
US3292374A (en) * 1963-03-29 1966-12-20 Rolls Royce Gas turbine engine and aircraft provided therwith
US3517898A (en) * 1966-12-30 1970-06-30 Sud Aviat Soc Nationale De Con Lift and propulsion device for a jet aircraft of the hybrid helicopter-autogyro type
US3601990A (en) * 1968-06-24 1971-08-31 Rolls Royce Gas turbine jet propulsion engine
RU2716651C2 (en) * 2018-03-30 2020-03-13 Артём Георгиевич Арутюнов Double-flow turbojet engine nozzles system

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