GB1277853A - Gas turbine engines - Google Patents
Gas turbine enginesInfo
- Publication number
- GB1277853A GB1277853A GB5404470A GB5404470A GB1277853A GB 1277853 A GB1277853 A GB 1277853A GB 5404470 A GB5404470 A GB 5404470A GB 5404470 A GB5404470 A GB 5404470A GB 1277853 A GB1277853 A GB 1277853A
- Authority
- GB
- United Kingdom
- Prior art keywords
- shaft
- engine
- gas turbine
- fan
- gearing
- 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
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
1277853 Gas turbine engines; ducted fan engines ROLLS-ROYCE Ltd 13 Nov 1970 54044/70 Heading F1G and F1J A gas turbine engine comprises a power takeoff shaft, one end of which is drivingly connected to the main shaft of the engine and other end of which is adapted for driving connection to an accessory drive mechanism, the power take-off shaft having between its ends windings whereby it constitutes the rotor of an electric machine. The engine shown is a gas turbine ducted fan engine which comprises a fan casing 50 defining with the casing 26, 28 of the gas generator 20 a fan duct 16. A power take-off shaft 32, rotatably mounted in bearings 34, is driven from the shaft 24 of the gas generator through gearing 30, a further shaft 38 being in splined engagement with the outer end of the take-off shaft 32. The shaft 38 is connected through gearing 42 to drive engine accessories 44, 46. The shaft 38 carries windings so that it constitutes the rotor of an electric machine the stator assembly of which is mounted within casing 40. The gearing 42 and accessories 44, 46 are disposed within a hollow strut 18 which extends across the fan duct 16. The engine support pylon 14 also extends across the fan duct 16 diametrically opposite the strut 18.
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB5404470A GB1277853A (en) | 1970-11-13 | 1970-11-13 | Gas turbine engines |
DE19712155882 DE2155882A1 (en) | 1970-11-13 | 1971-11-10 | Gas turbine jet engine |
IT3092271A IT941123B (en) | 1970-11-13 | 1971-11-10 | STARTER GENERATOR |
FR7140542A FR2113941B1 (en) | 1970-11-13 | 1971-11-12 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB5404470A GB1277853A (en) | 1970-11-13 | 1970-11-13 | Gas turbine engines |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1277853A true GB1277853A (en) | 1972-06-14 |
Family
ID=10469756
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB5404470A Expired GB1277853A (en) | 1970-11-13 | 1970-11-13 | Gas turbine engines |
Country Status (4)
Country | Link |
---|---|
DE (1) | DE2155882A1 (en) |
FR (1) | FR2113941B1 (en) |
GB (1) | GB1277853A (en) |
IT (1) | IT941123B (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2005005810A1 (en) * | 2003-07-08 | 2005-01-20 | Rolls-Royce Plc | Aircraft turbine engine arrangement |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4068470A (en) * | 1974-11-08 | 1978-01-17 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Gas turbine engine with convertible accessories |
-
1970
- 1970-11-13 GB GB5404470A patent/GB1277853A/en not_active Expired
-
1971
- 1971-11-10 DE DE19712155882 patent/DE2155882A1/en active Pending
- 1971-11-10 IT IT3092271A patent/IT941123B/en active
- 1971-11-12 FR FR7140542A patent/FR2113941B1/fr not_active Expired
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2005005810A1 (en) * | 2003-07-08 | 2005-01-20 | Rolls-Royce Plc | Aircraft turbine engine arrangement |
US7484354B2 (en) | 2003-07-08 | 2009-02-03 | Rolls-Royce Plc | Aircraft engine arrangement |
Also Published As
Publication number | Publication date |
---|---|
DE2155882A1 (en) | 1972-05-25 |
IT941123B (en) | 1973-03-01 |
FR2113941A1 (en) | 1972-06-30 |
FR2113941B1 (en) | 1975-07-18 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed | ||
PLNP | Patent lapsed through nonpayment of renewal fees |