GB1270538A - Mounting for gas turbine jet propulsion engine with fan unit - Google Patents

Mounting for gas turbine jet propulsion engine with fan unit

Info

Publication number
GB1270538A
GB1270538A GB27355/68A GB2735568A GB1270538A GB 1270538 A GB1270538 A GB 1270538A GB 27355/68 A GB27355/68 A GB 27355/68A GB 2735568 A GB2735568 A GB 2735568A GB 1270538 A GB1270538 A GB 1270538A
Authority
GB
United Kingdom
Prior art keywords
engine
fan
turbine
fan assembly
supported
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
GB27355/68A
Inventor
Kenneth William Clark
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 GB27355/68A priority Critical patent/GB1270538A/en
Priority to FR6917686A priority patent/FR2010419A1/fr
Publication of GB1270538A publication Critical patent/GB1270538A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • B64D27/20—Aircraft characterised by the type or position of power plants of jet type within, or attached to, fuselages
    • 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
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • 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
    • F02K3/062—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 with aft fan

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1,270,538. Gas turbine ducted fan engines. ROLLS ROYCE Ltd. June 6, 1969 [June 8, 1968], No. 27355/68. Headings F1G and F1J. An aircraft gas turbine jet engine comprises a gas turbine engine adapted to be mounted on aircraft structure and a fan unit comprising a fandriving turbine arranged to be driven by engine exhaust gases, there being means for connecting the fan unit to aircraft structure independently of the engine and ducting for directing the engine exhaust gases to the fan-driving turbine, the ducting permitting relative movement between the fan unit and the engine. The engine 3 shown in Fig. 2 is a gas turbine by-pass type engine, the efflux of which drives the turbine 21 of a ducted fan assembly. The fan assembly comprises a centre-body 22, an intermediate casing 23 comprising a forward portion 26 and a rearward portion 27, and an outer casing 30, turbine inlet guide vanes 24 and outlet guide vanes 25 extending across the turbine working fluid annulus, and fan inlet guide vanes 31 and outlet guide vanes 32 extending across the fan duct. The fan blades 20 are carried by the tips of the turbine blades. A support ring 33 is mounted at the upstream end of the casing 23. The engine 3 is supported from the aircraft structure by an arcuate member 10 and a ring member 11, the axial thrust of the engine being carried by the member 10 by means of mountings 12 at each side of the engine and part of the weight being carried by member 10 by means of link 9. The remainder of the weight of the engine is carried by the ring member 11 by means of link 13. The support ring 33 of the ducted fan assembly is supported from the ring member 11 by means of a frame structure 34. In place of a frame structure a rigid monocoque structure may be used. A rigid half monocoque structure 14 extends between the arcuate ring 10 and the ring member 11. A device for mixing by-pass air and gas flow is provided, also a thrust reverser 36. In Fig. 3 a casing 50 extending from the fan assembly is connected to the ring member 11 by a universal joint 51. The fan assembly is also connected to the aircraft structure in this embodiment either by a pair of pin-jointed struts 51, Fig. 4, or by a beam 52 and vertical link 53, Fig. 5. In Fig. 6 (not shown), the struts upstream of the fan blades are eliminated, the outer casing being supported from the intermediate casing 23 by the outlet guide vanes 32. The shaft 63 of the turbine and fan assembly is supported by bearings 62 on a member 61 which is carried from the struts 24, 25 by means of struts 60, 64. The fan assembly is supported from the ring member 11 by either of the previously described arrangements.
GB27355/68A 1968-06-08 1968-06-08 Mounting for gas turbine jet propulsion engine with fan unit Expired GB1270538A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB27355/68A GB1270538A (en) 1968-06-08 1968-06-08 Mounting for gas turbine jet propulsion engine with fan unit
FR6917686A FR2010419A1 (en) 1968-06-08 1969-05-30

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB27355/68A GB1270538A (en) 1968-06-08 1968-06-08 Mounting for gas turbine jet propulsion engine with fan unit

Publications (1)

Publication Number Publication Date
GB1270538A true GB1270538A (en) 1972-04-12

Family

ID=10258263

Family Applications (1)

Application Number Title Priority Date Filing Date
GB27355/68A Expired GB1270538A (en) 1968-06-08 1968-06-08 Mounting for gas turbine jet propulsion engine with fan unit

Country Status (2)

Country Link
FR (1) FR2010419A1 (en)
GB (1) GB1270538A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2188987A (en) * 1986-04-09 1987-10-14 Rolls Royce A turbofan gas turbine engine and mountings therefore
US5746391A (en) * 1995-04-13 1998-05-05 Rolls-Royce Plc Mounting for coupling a turbofan gas turbine engine to an aircraft structure
EP1690790A1 (en) 2005-02-11 2006-08-16 ROLLS-ROYCE plc Turbine engine arrangements
US7165744B2 (en) 2004-01-21 2007-01-23 Rolls-Royce Plc Turbine engine arrangements
EP1835147A2 (en) * 2006-03-13 2007-09-19 General Electric Company Turbofan
DE102008060488A1 (en) * 2008-12-05 2010-06-10 Rolls-Royce Deutschland Ltd & Co Kg Method and apparatus for operating a turboprop aircraft engine equipped with thrust propellers

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2188987A (en) * 1986-04-09 1987-10-14 Rolls Royce A turbofan gas turbine engine and mountings therefore
GB2188987B (en) * 1986-04-09 1990-02-14 Rolls Royce A turbofan gas turbine engine and mountings therefor
US5746391A (en) * 1995-04-13 1998-05-05 Rolls-Royce Plc Mounting for coupling a turbofan gas turbine engine to an aircraft structure
US7165744B2 (en) 2004-01-21 2007-01-23 Rolls-Royce Plc Turbine engine arrangements
EP1690790A1 (en) 2005-02-11 2006-08-16 ROLLS-ROYCE plc Turbine engine arrangements
EP1835147A2 (en) * 2006-03-13 2007-09-19 General Electric Company Turbofan
EP1835147A3 (en) * 2006-03-13 2011-03-23 General Electric Company Turbofan
DE102008060488A1 (en) * 2008-12-05 2010-06-10 Rolls-Royce Deutschland Ltd & Co Kg Method and apparatus for operating a turboprop aircraft engine equipped with thrust propellers
US8701385B2 (en) 2008-12-05 2014-04-22 Rolls-Royce Deutschland Ltd & Co Kg Method and apparatus for the operation of a turboprop aircraft engine provided with pusher propellers

Also Published As

Publication number Publication date
FR2010419A1 (en) 1970-02-13

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