GB1338499A - Gas turbine engine - Google Patents

Gas turbine engine

Info

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
Application number
GB5619671A
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 GB5619671A priority Critical patent/GB1338499A/en
Publication of GB1338499A publication Critical patent/GB1338499A/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
    • F02C7/36—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.
GB5619671A 1971-12-03 1971-12-03 Gas turbine engine Expired GB1338499A (en)

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)

* Cited by examiner, † Cited by third party
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

Cited By (33)

* Cited by examiner, † Cited by third party
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