GB798704A - Improvements in or relating to a unit for starting aircraft gas turbine engines - Google Patents

Improvements in or relating to a unit for starting aircraft gas turbine engines

Info

Publication number
GB798704A
GB798704A GB35002/55A GB3500255A GB798704A GB 798704 A GB798704 A GB 798704A GB 35002/55 A GB35002/55 A GB 35002/55A GB 3500255 A GB3500255 A GB 3500255A GB 798704 A GB798704 A GB 798704A
Authority
GB
United Kingdom
Prior art keywords
compressor
engine
gas turbine
valves
air
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
GB35002/55A
Inventor
Marcel Joseph Tournere
Alfred Julien Lafond
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 GB798704A publication Critical patent/GB798704A/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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/275—Mechanical drives
    • F02C7/277—Mechanical drives the starter being a separate turbine
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/262—Restarting after flame-out

Abstract

798,704. Generating combustion products under pressure. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Dec. 6, 1955 [Dec. 23, 1954], No. 35002/55. Class 51 (1). [Also in Groups XXVI and XXIX] A device associated with a gas turbine propulsion engine for starting-up the engine comprises a reversible-flow, bladed wheel which can operate either as a turbine for starting-up the engine when supplied with fluid under pressure from an external source, or as a compressor for supplying air at high pressure which is utilized to improve combustion in the combustion chamber of the gas turbine engine. The device is shown in Fig. 1 adapted to operate as a starter turbine and comprises a radial-flow wheel 1 adapted to rotate a gas turbine engine, not shown, through gearing 4 and a clutch 5. The turbine wheel 1 is supplied with combustion gases from an auxiliary combustion chamber 10 which receives air from a reservoir. The gases flow through the duct 9 and inlet nozzle guide vanes 6a on to the rotor blades and finally exhaust through the duct 8. The gas supplied to the turbine could alternatively be unheated air under pressure. Valves 15 and 12 are open and valves 13 and 15a are closed during operation as a turbine. The device is shown in Fig. 2 when operating as a high-pressure compressor. Air tapped from the outlet 14 of the compressor 14a of the gas turbine engine passes through duct 11 to the centre of the wheel 1 which is now operating as a centrifugal compressor. The air is thus further compressed and passes through duct 9a to a small auxiliary combustion chamber 16 which is disposed within the main combustion equipment 16a of the gas turbine engine and which is adapted to ensure reignition in the main combustion equipment during conditions of low ambient pressure. Valves 13 and 15a are open and valves 12 and 15 are closed during this operation. The air supply to the compressor 1 may be from a source other than from the outlet of the main compressor 14a. A control device comprising a governor which is dependent on engine speed and a barometric capsule responsive to the pressure difference between atmospheric pressure at ground level and at the operating altitude is provided to operate the various valves, the vanes 6a if they are of the adjustable type and the clutch 5. Specification 768,370 is referred to.
GB35002/55A 1954-12-23 1955-12-06 Improvements in or relating to a unit for starting aircraft gas turbine engines Expired GB798704A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR798704X 1954-12-23

Publications (1)

Publication Number Publication Date
GB798704A true GB798704A (en) 1958-07-23

Family

ID=9236347

Family Applications (1)

Application Number Title Priority Date Filing Date
GB35002/55A Expired GB798704A (en) 1954-12-23 1955-12-06 Improvements in or relating to a unit for starting aircraft gas turbine engines

Country Status (1)

Country Link
GB (1) GB798704A (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3107489A (en) * 1959-11-26 1963-10-22 Rolls Royce Gas turbine engine
US3157993A (en) * 1960-11-26 1964-11-24 Daimler Benz Ag Starter arrangement
US5054284A (en) * 1989-03-17 1991-10-08 Sundstrand Corporation Combustion heated air turbine starter system
US5160069A (en) * 1989-09-21 1992-11-03 Allied-Signal Inc. Integrated power unit combustion apparatus and method
US5161363A (en) * 1989-09-21 1992-11-10 Allied-Signal Inc. Integrated power unit
US5235812A (en) * 1989-09-21 1993-08-17 Allied-Signal Inc. Integrated power unit
US5274992A (en) * 1989-09-21 1994-01-04 Allied-Signal, Inc. Integrated power unit combustion apparatus and method
EP2886833A1 (en) * 2013-12-23 2015-06-24 Boge Kompressoren Otto Boge GmbH & Co. KG Device for the production of compressed air or other gases
CN108197354A (en) * 2017-12-18 2018-06-22 西北工业大学 A kind of parameter perturbation analysis method of high speed compressor under And of Varying Depth

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3107489A (en) * 1959-11-26 1963-10-22 Rolls Royce Gas turbine engine
US3157993A (en) * 1960-11-26 1964-11-24 Daimler Benz Ag Starter arrangement
US5054284A (en) * 1989-03-17 1991-10-08 Sundstrand Corporation Combustion heated air turbine starter system
US5160069A (en) * 1989-09-21 1992-11-03 Allied-Signal Inc. Integrated power unit combustion apparatus and method
US5161363A (en) * 1989-09-21 1992-11-10 Allied-Signal Inc. Integrated power unit
US5235812A (en) * 1989-09-21 1993-08-17 Allied-Signal Inc. Integrated power unit
US5274992A (en) * 1989-09-21 1994-01-04 Allied-Signal, Inc. Integrated power unit combustion apparatus and method
EP2886833A1 (en) * 2013-12-23 2015-06-24 Boge Kompressoren Otto Boge GmbH & Co. KG Device for the production of compressed air or other gases
CN108197354A (en) * 2017-12-18 2018-06-22 西北工业大学 A kind of parameter perturbation analysis method of high speed compressor under And of Varying Depth

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