GB744923A - Improvements relating to gas turbine engines - Google Patents
Improvements relating to gas turbine enginesInfo
- 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
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.
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)
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 |
-
1953
- 1953-05-19 GB GB14092/53A patent/GB744923A/en not_active Expired
Cited By (9)
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 |
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