GB1097632A - Gas turbine power plant - Google Patents

Gas turbine power plant

Info

Publication number
GB1097632A
GB1097632A GB49289/65A GB4928965A GB1097632A GB 1097632 A GB1097632 A GB 1097632A GB 49289/65 A GB49289/65 A GB 49289/65A GB 4928965 A GB4928965 A GB 4928965A GB 1097632 A GB1097632 A GB 1097632A
Authority
GB
United Kingdom
Prior art keywords
turbine
bevel gear
gear
shaft
engages
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
GB49289/65A
Inventor
Derek Aubrey Roberts
George Frederick Clarke
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.)
Bristol Siddeley Engines Ltd
Original Assignee
Bristol Siddeley Engines Ltd
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 Bristol Siddeley Engines Ltd filed Critical Bristol Siddeley Engines Ltd
Priority to GB49289/65A priority Critical patent/GB1097632A/en
Priority to DE1476735A priority patent/DE1476735C3/en
Priority to FR84143A priority patent/FR1499830A/en
Publication of GB1097632A publication Critical patent/GB1097632A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
    • F02C3/113—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission with variable power transmission between rotors
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/13—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having variable working fluid interconnections between turbines or compressors or stages of different rotors
    • 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
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user

Abstract

1,097,632. Propelling aircraft; air cushion vehicles. BRISTOL SIDDELEY ENGINES Ltd. Nov. 18, 1966 [Nov. 19, 1965], No. 49289/65. Headings B7G and B7K. [Also in Division F1]. A gas turbine power plant which provides propulsive thrust and drives a helicopter rotor or an aircraft ducted lift fan or a fan supplying cushion air for an air cushion vehicle comprises compressor, combustion equipment, a first turbine 1 arranged to drive the compressor, a second turbine 4 and a third turbine 6 all disposed in series flow, there being control means for regulating the gas flow between the second and third turbine rotors thus regulating the relative power outputs of these two turbines, also differential gearing comprising two input elements arranged to be driven respectively by the second and third turbines and an output element which constitutes a power output member. In the embodiment shown, the control means between the second and third turbines comprises a series of adjustable guide blades 7. The exhaust gases discharging from the turbine 6 pass through a duct 15 to a propulsion nozzle 14. The third turbine 6 is arranged to drive a ducted fan 10 which is disposed in a duct 11, the air discharging through a propulsion nozzle 13. The second turbine 4 is mounted on a shaft 3 which is connected at its downstream end to an internal ring gear 18, while the third turbine 6 is mounted on a shaft 5 which carries at its downstream end a sun gear 17, a series of planet gears 20 carried on a planet carrier 21, engaging with the sun gear 17 and the internal ring gear 18. The planet carrier 21 carries a bevel gear 23 which engages with a bevel gear 24 mounted on the output shaft 26. A further bevel gear 27 also engages the gear 23 and transmits drive to a further bevel gear 28 which also engages the bevel gear 24. The engine shown is suitable for a helicopter. The shaft 26 drives the fans or rotor and the jet nozzles 13, 14 provide the propulsive thrust.
GB49289/65A 1965-11-19 1965-11-19 Gas turbine power plant Expired GB1097632A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB49289/65A GB1097632A (en) 1965-11-19 1965-11-19 Gas turbine power plant
DE1476735A DE1476735C3 (en) 1965-11-19 1966-11-18 Gas turbine engine with two power takeoff devices
FR84143A FR1499830A (en) 1965-11-19 1966-11-18 Gas turbine engine group

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB49289/65A GB1097632A (en) 1965-11-19 1965-11-19 Gas turbine power plant

Publications (1)

Publication Number Publication Date
GB1097632A true GB1097632A (en) 1968-01-03

Family

ID=10451828

Family Applications (1)

Application Number Title Priority Date Filing Date
GB49289/65A Expired GB1097632A (en) 1965-11-19 1965-11-19 Gas turbine power plant

Country Status (3)

Country Link
DE (1) DE1476735C3 (en)
FR (1) FR1499830A (en)
GB (1) GB1097632A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2174762A (en) * 1985-05-01 1986-11-12 Gen Electric Counter rotation power turbine
GB2225297A (en) * 1988-11-28 1990-05-30 Gen Electric Auxiliary power take-off in an unducted fan gas turbine engine
US10018119B2 (en) 2012-04-02 2018-07-10 United Technologies Corporation Geared architecture with inducer for gas turbine engine
EP3460219A1 (en) * 2017-09-20 2019-03-27 General Electric Company Turbomachine with a gearbox and integrated electric machine assembly
US10669946B2 (en) 2015-06-05 2020-06-02 Raytheon Technologies Corporation Geared architecture for a gas turbine engine
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE401710B (en) * 1976-09-24 1978-05-22 Kronogard Sven Olof GASTURBINE TRANSMISSION FACILITY
CN112727635B (en) * 2020-12-31 2022-04-26 中国航空发动机研究院 Double-culvert engine

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2174762A (en) * 1985-05-01 1986-11-12 Gen Electric Counter rotation power turbine
GB2174762B (en) * 1985-05-01 1990-04-04 Gen Electric Counter rotation power turbine
GB2225297A (en) * 1988-11-28 1990-05-30 Gen Electric Auxiliary power take-off in an unducted fan gas turbine engine
FR2639609A1 (en) * 1988-11-28 1990-06-01 Gen Electric POWER TAKE-OFF DEVICE FOR CONVERTING THE POWER DEVELOPED BY THE ROTORS OF A GAS TURBINE ENGINE WITH NON-FAIRED BLOWER INTO A TRANSVERSE PUSH
GB2225297B (en) * 1988-11-28 1992-09-02 Gen Electric Auxiliary power take-off in an unducted fan gas turbine engine
US10018119B2 (en) 2012-04-02 2018-07-10 United Technologies Corporation Geared architecture with inducer for gas turbine engine
US10584642B2 (en) 2012-04-02 2020-03-10 United Technologies Corporation Geared architecture with inducer for gas turbine engine
US10669946B2 (en) 2015-06-05 2020-06-02 Raytheon Technologies Corporation Geared architecture for a gas turbine engine
EP3460219A1 (en) * 2017-09-20 2019-03-27 General Electric Company Turbomachine with a gearbox and integrated electric machine assembly
US11008883B2 (en) 2017-09-20 2021-05-18 General Electric Company Turbomachine with a gearbox and integrated electric machine assembly
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly

Also Published As

Publication number Publication date
DE1476735A1 (en) 1969-06-26
DE1476735B2 (en) 1974-05-30
DE1476735C3 (en) 1975-01-23
FR1499830A (en) 1967-10-27

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