GB744923A - Improvements relating to gas turbine engines - Google Patents

Improvements relating to gas turbine engines

Info

Publication number
GB744923A
GB744923A GB14092/53A GB1409253A GB744923A GB 744923 A GB744923 A GB 744923A GB 14092/53 A GB14092/53 A GB 14092/53A GB 1409253 A GB1409253 A GB 1409253A GB 744923 A GB744923 A GB 744923A
Authority
GB
United Kingdom
Prior art keywords
compressor
engine
turbine
auxiliary
gas
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
GB14092/53A
Inventor
Nelson Hector Kent
Cyril Armer
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 GB14092/53A priority Critical patent/GB744923A/en
Publication of GB744923A publication Critical patent/GB744923A/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
    • F02C7/22—Fuel supply systems
    • 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
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

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

Abstract

744,923. Turning gear. ROLLS-ROYCE Ltd. May 19, 1954 [May 19, 1953], No. 14092/53. Class 7(5) [Also in Group XXVI] A gas turbine plant has an auxiliary tur- .bine which drives a compressor and turbine rotor system during starting and additionally drives a fuel pump during ,normal running of the engine. A compressor rotor 10 connected to a. turbine rotor (not shown) is driven during starting by an auxiliary turbine 20 through epicyclic gearing 23, 26, 30, bevel gearing 31, 33, a freewheel clutch 35. 39. 38d and spur gearing 38, 40. The freewheel clutch allows the compressor shaft 10 to overrun the auxiliary turbine shaft 22 when the engine has started. The auxiliary turbine 20 is supplied with gas under pressure from a source 54 through a duct 55. The source of gas under pressure may be derived from the combustion of fuel in compressed air .or other combustion or chemical process. Cordite and Isopropyl nitrates are commonly used for this purpose. The duct 55 has a valve 56 by means of which the duct 55 can be connected to a pipeline 57 connected to the compressor of the engine when the engine has started. The valve 56 may be replaced by two separate valves. The auxiliary turbine 20, is also connected to the impeller 60 of a centrifugal fuel pump feeding the main combustion equipment of the plant. The valve 56 may be automatically controlled as by a centrifugal speed-sensitive device driven by the compressor rotor or by a time-sensitive device. The auxiliary turbine 20 may be of the radial flow type. Where the gas pressure source 54 comprises an auxiliary compressor, e.g. a small self-contained gas turbine engine, the fuel supply to,this gas turbine engine may be controlled after starting, in accordance with the fuel requirements of the plant. The tapping from the main engine air compressor may then be dispensed with. When air is tapped from the main engine compressor, it may be heated in an auxiliary combustion chamber.
GB14092/53A 1953-05-19 1953-05-19 Improvements relating to gas turbine engines Expired GB744923A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB14092/53A GB744923A (en) 1953-05-19 1953-05-19 Improvements relating to gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB14092/53A GB744923A (en) 1953-05-19 1953-05-19 Improvements relating to gas turbine engines

Publications (1)

Publication Number Publication Date
GB744923A true GB744923A (en) 1956-02-15

Family

ID=10034845

Family Applications (1)

Application Number Title Priority Date Filing Date
GB14092/53A Expired GB744923A (en) 1953-05-19 1953-05-19 Improvements relating to gas turbine engines

Country Status (1)

Country Link
GB (1) GB744923A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2659389A1 (en) * 1990-03-06 1991-09-13 Gen Electric LIMIT LAYER DISCHARGE SYSTEM INTEGRATED INTO THE STARTER OF AN AIRCRAFT ENGINE.
US5125597A (en) * 1990-06-01 1992-06-30 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed with energy recovery system
US5137230A (en) * 1991-06-04 1992-08-11 General Electric Company Aircraft gas turbine engine bleed air energy recovery apparatus
US5143329A (en) * 1990-06-01 1992-09-01 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed
CN110234856A (en) * 2017-01-30 2019-09-13 赛峰飞机发动机公司 Equipment for driving the petrolift of turbine
EP3712406A3 (en) * 2019-03-20 2021-02-17 United Technologies Corporation Backup system for demand fuel pumping system
US11168618B2 (en) 2019-03-06 2021-11-09 Rolls-Royce Plc Shaft apparatus for a gas turbine engine

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2659389A1 (en) * 1990-03-06 1991-09-13 Gen Electric LIMIT LAYER DISCHARGE SYSTEM INTEGRATED INTO THE STARTER OF AN AIRCRAFT ENGINE.
GB2242235A (en) * 1990-03-06 1991-09-25 Gen Electric Aircraft engine bleed system
US5125597A (en) * 1990-06-01 1992-06-30 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed with energy recovery system
US5143329A (en) * 1990-06-01 1992-09-01 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed
US5137230A (en) * 1991-06-04 1992-08-11 General Electric Company Aircraft gas turbine engine bleed air energy recovery apparatus
CN110234856A (en) * 2017-01-30 2019-09-13 赛峰飞机发动机公司 Equipment for driving the petrolift of turbine
CN110234856B (en) * 2017-01-30 2022-07-26 赛峰飞机发动机公司 Device for driving a fuel pump of a turbomachine
US11168618B2 (en) 2019-03-06 2021-11-09 Rolls-Royce Plc Shaft apparatus for a gas turbine engine
EP3712406A3 (en) * 2019-03-20 2021-02-17 United Technologies Corporation Backup system for demand fuel pumping system

Similar Documents

Publication Publication Date Title
GB749176A (en) Improvements relating to jet propulsion apparatus
GB774695A (en) Improvements relating to internal combustion engines
GB587527A (en) Improvements in or relating to internal combustion turbines
GB1136584A (en) Gas turbine engine accessory drive systems
GB744923A (en) Improvements relating to gas turbine engines
US2613501A (en) Internal-combustion turbine power plant
GB798704A (en) Improvements in or relating to a unit for starting aircraft gas turbine engines
GB881967A (en) Improved propulsion unit for use in vertical take-off aircraft
GB743859A (en) Improvements in or relating to fuel systems for gas-turbine engines
GB923937A (en) Speed governor mechanisms, applicable to gas turbine engines
GB636712A (en) Pump assembly
GB874902A (en) Improvements relating to power units
GB416463A (en) Improvements in constant pressure gas turbine plant
GB741433A (en) Improvements relating to gas turbine engine fuel systems
GB578147A (en) Improvements in or relating to internal combustion engine power plants
GB652048A (en) Improvements relating to exhaust driven turbines on reciprocating internal combustion engines
GB727201A (en) Improvements in fuel supply systems for gas turbine engines
GB851940A (en) Improvements in or relating to power plant including a closed cycle gas turbine engine
GB712346A (en) Gas turbine motor
GB710857A (en) Improvements in or relating to gas-turbine engines having means to facilitate starting
GB885542A (en) Improvements relating to engine starting systems
GB586912A (en) Turbine system
GB586277A (en) Improvements relating to jet-propulsion, internal-combustion, turbine plant
GB684428A (en) Improvements in or relating to a power plant
GB600608A (en) Improvements in or relating to internal combustion turbine power plants