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GB1028296A - Improvements in or relating to by-pass turbojets - Google Patents

Improvements in or relating to by-pass turbojets

Info

Publication number
GB1028296A
GB1028296A GB30491/63A GB3049163A GB1028296A GB 1028296 A GB1028296 A GB 1028296A GB 30491/63 A GB30491/63 A GB 30491/63A GB 3049163 A GB3049163 A GB 3049163A GB 1028296 A GB1028296 A GB 1028296A
Authority
GB
United Kingdom
Prior art keywords
pass
turbine
manifolds
temperature
flow
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
GB30491/63A
Inventor
Louis Jules Bauger
Marcel Jean Baraut
Pierre Marcel Phelipon
Armand Jean-Baptiste Lacroix
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of GB1028296A publication Critical patent/GB1028296A/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
    • 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
    • F02K3/10—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof by after-burners

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,028,296. Gas turbine jet engines. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Aug. 1, 1963 [Aug. 4, 1962], No. 30491/63. Heading F1J. In a gas turbine jet engine of the by-pass type a heating device is provided whereby the flow of bypass air may be heated upstream of the zone where the main hot gas flow and the by-pass air flow meet, whereby the temperature of the bypass air flow is increased so as to be substantially equal to that of the main hot gas flow discharged by the turbine. Temperature detecting devices are located within the main and by-pass ducts just upstream of the mixing zone, the temperature signals being communicated to a control unit which regulates the fuel supply to the preheat device. The engine shown comprises a first stage compressor 2, 1, a second stage compressor 4, combustion equipment 6, a high pressure turbine 5 which drives the compressor 4, and a low pressure turbine 3 which drives the compressor 2, 1. A portion of the air delivered by the first portion 2 of the compressor 2, 1 flows through the by-pass passage 8 and combustion equipment 12 is provided in this passage whereby the by-pass air is heated to substantially the same temperature as the main gas flow discharging from the turbine 3. The mixture of turbine exhaust gases and by-pass air flow through the jet pipe 9 and propulsion nozzle 11, reheat equipment 13, 14, 15 being provided in the jet pipe in the region where the flows mix. The reheat equipment also comprises fuel ring manifolds 16, 17 which have no flame stabilizing devices associated therewith. Two control devices R 1 , R 2 are provided, the device R 1 receiving signals α responsive to control lever M, # 1 responsive to temperature of the main gas stream adjacent the mixing region, and # 2 responsive to temperature of the by-pass air flow also adjacent the mixing region, and controlling fuel flow to the manifolds 12, 13 and 16, a pressure difference #P being maintained between the manifolds 13 and 16. The control device R 2 is also responsive to movement of the control lever M and controls supply of fuel to the manifolds 14, 15 and 17, a pressure difference #P being maintained between the manifolds 14 and 17.
GB30491/63A 1962-08-04 1963-08-01 Improvements in or relating to by-pass turbojets Expired GB1028296A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR906141A FR1339601A (en) 1962-08-04 1962-08-04 Improvement in bypass reactors

Publications (1)

Publication Number Publication Date
GB1028296A true GB1028296A (en) 1966-05-04

Family

ID=8784645

Family Applications (1)

Application Number Title Priority Date Filing Date
GB30491/63A Expired GB1028296A (en) 1962-08-04 1963-08-01 Improvements in or relating to by-pass turbojets

Country Status (3)

Country Link
US (1) US3204404A (en)
FR (1) FR1339601A (en)
GB (1) GB1028296A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2161717C2 (en) * 1997-01-06 2001-01-10 Артамонов Александр Сергеевич Device to increase efficiency of heat engine
RU2273814C1 (en) * 2004-09-01 2006-04-10 Федеральное государственное унитарное предприятие Конструкторское бюро транспортного машиностроения Universal generating set of heat gas flow on tank chassis
RU2273816C1 (en) * 2004-09-01 2006-04-10 Федеральное государственное унитарное предприятие Конструкторское бюро транспортного машиностроения Universal generating set of heat gas flow on tank chassis
RU2273817C1 (en) * 2004-09-01 2006-04-10 Федеральное государственное унитарное предприятие Конструкторское бюро транспортного машиностроения Universal generating set of heat gas flow on tank chassis

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1126163A (en) * 1967-06-16 1968-09-05 Rolls Royce Gas turbine by-pass engine
US3630029A (en) * 1970-01-14 1971-12-28 Lucas Industries Ltd Fuel controls for reheat systems of gas turbine engines
US4244183A (en) * 1978-04-27 1981-01-13 United Technologies Corporation Control means for an augmentor for a gas turbine engine
DE3543908C1 (en) * 1985-12-12 1987-01-29 Mtu Muenchen Gmbh Device for controlling the fuel supply to the afterburner of a bypass gas turbine jet engine
DE4324794C2 (en) * 1993-07-23 1997-10-16 Alexander Schaefer Nozzle drive
GB2610569A (en) 2021-09-08 2023-03-15 Rolls Royce Plc An improved gas turbine engine
GB2610570A (en) * 2021-09-08 2023-03-15 Rolls Royce Plc An improved gas turbine engine
GB2610567A (en) 2021-09-08 2023-03-15 Rolls Royce Plc An improved gas turbine engine
GB2610568A (en) 2021-09-08 2023-03-15 Rolls Royce Plc An improved gas turbine engine
GB2610572A (en) 2021-09-08 2023-03-15 Rolls Royce Plc An improved gas turbine engine
GB2610565A (en) 2021-09-08 2023-03-15 Rolls Royce Plc An improved gas turbine engine

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2955414A (en) * 1957-09-03 1960-10-11 United Aircraft Corp Combined power plant
US3054254A (en) * 1959-01-27 1962-09-18 United Aircraft Corp Turbofan afterburner fuel control improvement

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2161717C2 (en) * 1997-01-06 2001-01-10 Артамонов Александр Сергеевич Device to increase efficiency of heat engine
RU2273814C1 (en) * 2004-09-01 2006-04-10 Федеральное государственное унитарное предприятие Конструкторское бюро транспортного машиностроения Universal generating set of heat gas flow on tank chassis
RU2273816C1 (en) * 2004-09-01 2006-04-10 Федеральное государственное унитарное предприятие Конструкторское бюро транспортного машиностроения Universal generating set of heat gas flow on tank chassis
RU2273817C1 (en) * 2004-09-01 2006-04-10 Федеральное государственное унитарное предприятие Конструкторское бюро транспортного машиностроения Universal generating set of heat gas flow on tank chassis

Also Published As

Publication number Publication date
US3204404A (en) 1965-09-07
FR1339601A (en) 1963-10-11

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