GB1338499A - Gas turbine engine - Google Patents
Gas turbine engineInfo
- Publication number
- GB1338499A GB1338499A GB5619671A GB5619671A GB1338499A GB 1338499 A GB1338499 A GB 1338499A GB 5619671 A GB5619671 A GB 5619671A GB 5619671 A GB5619671 A GB 5619671A GB 1338499 A GB1338499 A GB 1338499A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbine
- fan
- shaft
- layshaft
- flange
- 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
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/327—Application in turbines in gas turbines to drive shrouded, high solidity propeller
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
- F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
1338499 Gas turbine ducted fan engines ROLLS-ROYCE (1971) Ltd 3 Dec 1971 56196/71 Heading F1J The invention relates to a gas turbine ducted fan engine in which the fan turbine drives the fan by means of a plurality of layshafts connected by gears to the turbine and the fan. The engine comprises LP compressor 11, HP compressor 12, combustion equipment 13, HP turbine 14, LP turbine 15 and a fan driving turbine 16. The turbine 16 is drivingly connected to the fan rotor 19 by means of a plurality of layshafts 21 which extend across the turbine working fluid annulus being enclosed within fairings 23. The fan turbine 16 is secured to a shaft assembly 32 which is supported in a ball bearing 35. The shaft is formed with a flange 36 which carries a driving bevel gear 37. A bevel pinion 38 is mounted on a layshaft 21 by means of a spline connection 43, 44, also by means of a flange 45 on the shaft which engages a flange 47 on the pinion through a ring member 46. A retaining plate 48 engages against the flange 45 and is retained by means of a spring ring 49. The bevel pinion is supported within gear housing 42 by means of a ball bearing 39 and a pair of roller bearings 40, 41. A bevel pinion 57 is mounted at the other end of the layshaft by means of a sleeve 58 which is in splined engagement 59, 60 at one end with the layshaft and in splined engagement 61, 62 at the other end with the bevel pinion. The pinion is rotatably mounted in the housing 51 by means of two roller bearings 63, 64. The bevel pinion engages a bevel gear 70 which is secured to the shaft 71 on which the fan rotor blades 72 are mounted, the shaft being rotatably mounted in a ball bearing 73 which forms the sole support for the fan rotor. The splines 59, 60, and 61, 62 may be of different pitch so as to form a vernier type coupling. The layshaft extends through a tube member 50, the tube member being connected to the gear housing 51 by means of a compression joint 52 which comprises a tube with an internal conical surface at one end and externally screwed at its other end, a sleeve 56 formed with conical surfaces one of which engages the conical surface of the tube 52 and the other of which is engaged by the conical surface of a ring member 55, a nut 54 engaging against the ring member.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB5619671A GB1338499A (en) | 1971-12-03 | 1971-12-03 | Gas turbine engine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB5619671A GB1338499A (en) | 1971-12-03 | 1971-12-03 | Gas turbine engine |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1338499A true GB1338499A (en) | 1973-11-21 |
Family
ID=10476011
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB5619671A Expired GB1338499A (en) | 1971-12-03 | 1971-12-03 | Gas turbine engine |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB1338499A (en) |
Cited By (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2398891A1 (en) * | 1977-07-25 | 1979-02-23 | Gen Electric | TURBOMACHINE WITH REGULATED OPERATING CYCLE |
EP0203881A1 (en) * | 1985-05-29 | 1986-12-03 | United Technologies Corporation | Ducted prop engine |
US4815273A (en) * | 1985-12-31 | 1989-03-28 | Peter Rudolph | Single propeller turboprop propulsion apparatus |
WO2006060011A1 (en) * | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Tip turbine engine comprising a nonrotable compartment |
US7845157B2 (en) | 2004-12-01 | 2010-12-07 | United Technologies Corporation | Axial compressor for tip turbine engine |
US7854112B2 (en) | 2004-12-01 | 2010-12-21 | United Technologies Corporation | Vectoring transition duct for turbine engine |
US7874163B2 (en) | 2004-12-01 | 2011-01-25 | United Technologies Corporation | Starter generator system for a tip turbine engine |
US7883314B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Seal assembly for a fan-turbine rotor of a tip turbine engine |
US7882694B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Variable fan inlet guide vane assembly for gas turbine engine |
US7883315B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Seal assembly for a fan rotor of a tip turbine engine |
US7921635B2 (en) | 2004-12-01 | 2011-04-12 | United Technologies Corporation | Peripheral combustor for tip turbine engine |
US7934902B2 (en) | 2004-12-01 | 2011-05-03 | United Technologies Corporation | Compressor variable stage remote actuation for turbine engine |
US7937927B2 (en) | 2004-12-01 | 2011-05-10 | United Technologies Corporation | Counter-rotating gearbox for tip turbine engine |
US7959532B2 (en) | 2004-12-01 | 2011-06-14 | United Technologies Corporation | Hydraulic seal for a gearbox of a tip turbine engine |
US7959406B2 (en) | 2004-12-01 | 2011-06-14 | United Technologies Corporation | Close coupled gearbox assembly for a tip turbine engine |
US7976272B2 (en) | 2004-12-01 | 2011-07-12 | United Technologies Corporation | Inflatable bleed valve for a turbine engine |
US7980054B2 (en) | 2004-12-01 | 2011-07-19 | United Technologies Corporation | Ejector cooling of outer case for tip turbine engine |
US8024931B2 (en) | 2004-12-01 | 2011-09-27 | United Technologies Corporation | Combustor for turbine engine |
US8083030B2 (en) | 2004-12-01 | 2011-12-27 | United Technologies Corporation | Gearbox lubrication supply system for a tip engine |
US8096753B2 (en) | 2004-12-01 | 2012-01-17 | United Technologies Corporation | Tip turbine engine and operating method with reverse core airflow |
US8561383B2 (en) | 2004-12-01 | 2013-10-22 | United Technologies Corporation | Turbine engine with differential gear driven fan and compressor |
EP2902608A1 (en) * | 2014-01-30 | 2015-08-05 | United Technologies Corporation | Aft shrouded geared turbofan |
WO2017060623A1 (en) * | 2015-10-05 | 2017-04-13 | Safran Aircraft Engines | Turbine engine with fan and reduction of speed on the shaft of the power turbine |
FR3056556A1 (en) * | 2016-09-29 | 2018-03-30 | Safran Aircraft Engines | AIRCRAFT WITH A TURBOMACHINE INTEGRATED WITH REAR FUSELAGE COMPRISING A PROPELLER SURROUNDING AN EXHAUST CASING |
-
1971
- 1971-12-03 GB GB5619671A patent/GB1338499A/en not_active Expired
Cited By (33)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2398891A1 (en) * | 1977-07-25 | 1979-02-23 | Gen Electric | TURBOMACHINE WITH REGULATED OPERATING CYCLE |
EP0203881A1 (en) * | 1985-05-29 | 1986-12-03 | United Technologies Corporation | Ducted prop engine |
US4704862A (en) * | 1985-05-29 | 1987-11-10 | United Technologies Corporation | Ducted prop engine |
US4815273A (en) * | 1985-12-31 | 1989-03-28 | Peter Rudolph | Single propeller turboprop propulsion apparatus |
US7976272B2 (en) | 2004-12-01 | 2011-07-12 | United Technologies Corporation | Inflatable bleed valve for a turbine engine |
US8083030B2 (en) | 2004-12-01 | 2011-12-27 | United Technologies Corporation | Gearbox lubrication supply system for a tip engine |
US7854112B2 (en) | 2004-12-01 | 2010-12-21 | United Technologies Corporation | Vectoring transition duct for turbine engine |
US7874163B2 (en) | 2004-12-01 | 2011-01-25 | United Technologies Corporation | Starter generator system for a tip turbine engine |
US7883314B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Seal assembly for a fan-turbine rotor of a tip turbine engine |
US7882694B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Variable fan inlet guide vane assembly for gas turbine engine |
US7883315B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Seal assembly for a fan rotor of a tip turbine engine |
US7921635B2 (en) | 2004-12-01 | 2011-04-12 | United Technologies Corporation | Peripheral combustor for tip turbine engine |
US7934902B2 (en) | 2004-12-01 | 2011-05-03 | United Technologies Corporation | Compressor variable stage remote actuation for turbine engine |
US7937927B2 (en) | 2004-12-01 | 2011-05-10 | United Technologies Corporation | Counter-rotating gearbox for tip turbine engine |
US7959532B2 (en) | 2004-12-01 | 2011-06-14 | United Technologies Corporation | Hydraulic seal for a gearbox of a tip turbine engine |
US7959406B2 (en) | 2004-12-01 | 2011-06-14 | United Technologies Corporation | Close coupled gearbox assembly for a tip turbine engine |
WO2006060011A1 (en) * | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Tip turbine engine comprising a nonrotable compartment |
US7980054B2 (en) | 2004-12-01 | 2011-07-19 | United Technologies Corporation | Ejector cooling of outer case for tip turbine engine |
US8024931B2 (en) | 2004-12-01 | 2011-09-27 | United Technologies Corporation | Combustor for turbine engine |
US7845157B2 (en) | 2004-12-01 | 2010-12-07 | United Technologies Corporation | Axial compressor for tip turbine engine |
US8096753B2 (en) | 2004-12-01 | 2012-01-17 | United Technologies Corporation | Tip turbine engine and operating method with reverse core airflow |
US8276362B2 (en) | 2004-12-01 | 2012-10-02 | United Technologies Corporation | Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method |
US8561383B2 (en) | 2004-12-01 | 2013-10-22 | United Technologies Corporation | Turbine engine with differential gear driven fan and compressor |
US8757959B2 (en) | 2004-12-01 | 2014-06-24 | United Technologies Corporation | Tip turbine engine comprising a nonrotable compartment |
US8950171B2 (en) | 2004-12-01 | 2015-02-10 | United Technologies Corporation | Counter-rotating gearbox for tip turbine engine |
US9003768B2 (en) | 2004-12-01 | 2015-04-14 | United Technologies Corporation | Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method |
US9541092B2 (en) | 2004-12-01 | 2017-01-10 | United Technologies Corporation | Tip turbine engine with reverse core airflow |
EP2902608A1 (en) * | 2014-01-30 | 2015-08-05 | United Technologies Corporation | Aft shrouded geared turbofan |
WO2017060623A1 (en) * | 2015-10-05 | 2017-04-13 | Safran Aircraft Engines | Turbine engine with fan and reduction of speed on the shaft of the power turbine |
CN108138658A (en) * | 2015-10-05 | 2018-06-08 | 赛峰飞机发动机公司 | The turbogenerator of deceleration device with fan and in power turbine shaft |
CN108138658B (en) * | 2015-10-05 | 2020-11-20 | 赛峰飞机发动机公司 | Turbine engine with fan and reduction gear on power turbine shaft |
US11022043B2 (en) * | 2015-10-05 | 2021-06-01 | Safran Aircraft Engines | Turbine engine with fan and reduction of speed on the shaft of the power turbine |
FR3056556A1 (en) * | 2016-09-29 | 2018-03-30 | Safran Aircraft Engines | AIRCRAFT WITH A TURBOMACHINE INTEGRATED WITH REAR FUSELAGE COMPRISING A PROPELLER SURROUNDING AN EXHAUST CASING |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed | ||
PLNP | Patent lapsed through nonpayment of renewal fees |