GB2215290A - A method of mounting a ducted fan gas turbine engine on an aircraft - Google Patents

A method of mounting a ducted fan gas turbine engine on an aircraft Download PDF

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Publication number
GB2215290A
GB2215290A GB8805527A GB8805527A GB2215290A GB 2215290 A GB2215290 A GB 2215290A GB 8805527 A GB8805527 A GB 8805527A GB 8805527 A GB8805527 A GB 8805527A GB 2215290 A GB2215290 A GB 2215290A
Authority
GB
United Kingdom
Prior art keywords
pylon
gas turbine
turbine engine
ducted fan
aircraft
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.)
Granted
Application number
GB8805527A
Other versions
GB8805527D0 (en
GB2215290B (en
Inventor
Arnold Charles Newton
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 GB8805527A priority Critical patent/GB2215290B/en
Publication of GB8805527D0 publication Critical patent/GB8805527D0/en
Priority to DE3902325A priority patent/DE3902325A1/en
Priority to JP1022468A priority patent/JPH01229799A/en
Priority to FR898901432A priority patent/FR2628388B1/en
Publication of GB2215290A publication Critical patent/GB2215290A/en
Application granted granted Critical
Publication of GB2215290B publication Critical patent/GB2215290B/en
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • 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
    • B64D27/18—Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
    • 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
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B64D27/406—Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Vibration Prevention Devices (AREA)

Abstract

A ducted fan gas turbine engine 12 is fastened to a supporting pylon 14 via links (18) (Fig. 1) and 20 and bolted flanges 30, 32 in rigid, metal to metal contact so as to avoid relative movement therebetween through vibration, whilst the pylon 14 is fastened to aircraft beam structure 38 and 40 via joints which include resilient bushes 46. The arrangement ensures greater stability in the assembly comprising the fan structure and core gas generator. The corrections of the links (18), 20 to the rear of the fan cowl are more widely spaced apart than their connections to the pylons 14. <IMAGE>

Description

I 1 P 1 1 . 1 0 ---;. ---. ' 1 A METHOD OF MOUNTING A DUCTED FAN GAS
TURBINE ENGINE ON AN AIRCRAFT The present invention relates to a method of mounting a ducted fan gas turbine engine on an aircraft in such a manner as to achieve reduced relative vibratory movements between the major casing structures of the engine.
The relative vibratory movements referred to herein, are for the most part generated by the loads exerted by the ambient airflow around the casing structures, during flight of an associated aircraft.
According to the present invention a method of mounting a ducted fan gas turbine engine on an aircraft comprises the steps of rigidly fixing the core gas generator of the ducted fan gas turbine engine to an end of a pylon, rigidly connecting the downstream end face of a cowl which surrounds the fan stage of the ducted fan gas turbine engine via a pair of spaced. apart links to the pylon at positions intermediate the pylon ends and connecting the pylon via resilient vibration absorbing means to a beam structure on the aircraft.
The invention will now be described, by way of example and with reference to the accompanying drawings in which:
Figure 1 is a diagrammatic plan view of an aircraft wing which supports a ducted fan gas turbine engine in a manner which incorporates the present invention.
Figure 2 is a diagrammatic part cross-sectional view on Figure 1 in the direction of arrow 2.
Figure 3 is an enlarged cross-sectional view of a pylon/aircraft structure connection in accordance with an. embodiment of the present invention.
Referring to Figure 1. An aircraft wing 10 supports a ducted fan gas turbine engines 12 from a position thereunder. The support is via a pylon 14 shown in dashed lines.
The pylon 14 has a pair of lugs 16 formed thereon, each of which has one end of a respective link of a pair of links 18, 20 fastened to it. The other ends of the links 18 and 20 are fastened to the downstream face of an annular box structure 22 which provides a shroud for a stage of fan outlet guide vanes 24, (Figure 2), the radially inner ends t 2 (not shown) of which are fixed to the core gas generator 25 within a casing 26. It should be noted that those ends of the links 18,20 which are fastened to the annular box structure 22, are more widely spaced than their other ends. Further, the connections between links 18 and 20 and the pylon 14 are metal to metal. The lack of resilient means at the junctions ensuring obviation of relative movement through vibration.
Each of the links 18 and 20 has a length adjusting device 28 of any known, suitable kind, whereby after connection of the respective ends of the links to the pylon 14 and the box structure 22, the lengths of the links can be adjusted so as to ensure that they are always in tension.
Referring now to Figure 2. The pylon 14 extends forwardly and radially inwardly of its link connection lugs 16, and its upstream extremity 30 has a flange 32 formed thereon, which is bolted to a flange portion 34 on the compressor casing 36 of the core gas generator. Again the bolted joint is rigid, there being no resilient means to absorb vibration. It follows that the assembly consisting of the pylon 14, the links 18 and 20 and the ducted fan gas turbine engine 12 is effectively a one piece unit which has no junctions at which movements of the parts relative to each other can occur.
The assembly of pylon 14 and ducted fan gas turbine engine 12 is joined to an aircraft via the main beams 38 and 40, in the-wing 10.
Referring now to Figure 3. The means used for maintaining the engine in situ in the present example consists of bolts 42 which clamp flanges 44 on the pylon 14 to flanges 39 on the main beams 38 and 40. It is at this junction of pylon 14 to the main beams 38 and 40, where vibration absorbing structure may be used.
The vibration absorbing structure may comprise by way of example, rubber bushes 46 or compressed wire bushes, both of which are well -known as vibration absorbers in the joints of jointed assemblies. The rubber bushes 46 may have metal sleeves 48 and 50 bonded thereto.
11 c, 1 0 3 Y -1 In an alternative embodiment (not shown) the main beams 38 and 40 and the pylon 14 may have cooperating flanges (not shown) through which the bolts 42 would pass horizontally and the resilient bushes would reside therein in a similar altitude (not shown) i.e. with their axes horizontal.
4

Claims (4)

Claims:-
1. A method of mounting a ducted fan gas turbine engine on an aircraft comprising the steps of rigidly fixing the core gas generator of the ducted fan gas turbine engine to an end of a pylon, rigidly connecting the downstream end face of a cowl which surrounds the fan stage of the ducted fan gas turbine engine via a pair of spaced apart links to the pylon at positions intermediate the pylon ends and connecting the pylon via resilient vibration absorbing means to a beam structure on the aircraft.
2. A method of mounting a ducted fan gas turbine engine to an aircraft as claimed in claim 1 wherein those ends of said links which are connected to the downstream end face of said cowl, are more widely spaced than the other ends thereof.
3. A method of-mounting a ducted fan gas turbine engine on an aircraft as claimed in claim 2 wherein the step of connecting the pylon to said beam structure includes the step of clamping rubber bushes between the pylon and said beam structure.
4. A method of mounting a ducted fan gas turbine engine substantially as described in this specification with reference to the drawings.
Published 1989 atThe Patent Office. State House, 68.171 High Holborn, London WClR 4TP. Purther Copies maybe obtained from The Patent Oface. Sales Branch, St Mary Cray, OrpInjjton. Kent BR5 3RD. Printed by Multiplex techniques ltd, St Mary Cray, Kent, Con. 1/87 11
GB8805527A 1988-03-08 1988-03-08 A method of mounting a ducted fan gas turbine engine on an aircraft Expired - Fee Related GB2215290B (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB8805527A GB2215290B (en) 1988-03-08 1988-03-08 A method of mounting a ducted fan gas turbine engine on an aircraft
DE3902325A DE3902325A1 (en) 1988-03-08 1989-01-26 Method for attaching a bypass fan gas-turbine engine to an aircraft
JP1022468A JPH01229799A (en) 1988-03-08 1989-01-31 Method of loading ducted fan-gas turbine engine on aircraft
FR898901432A FR2628388B1 (en) 1988-03-08 1989-02-03 METHOD FOR MOUNTING A GAS TURBINE ENGINE WITH A FAIRED PROPELLER

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB8805527A GB2215290B (en) 1988-03-08 1988-03-08 A method of mounting a ducted fan gas turbine engine on an aircraft

Publications (3)

Publication Number Publication Date
GB8805527D0 GB8805527D0 (en) 1988-04-07
GB2215290A true GB2215290A (en) 1989-09-20
GB2215290B GB2215290B (en) 1991-09-04

Family

ID=10633071

Family Applications (1)

Application Number Title Priority Date Filing Date
GB8805527A Expired - Fee Related GB2215290B (en) 1988-03-08 1988-03-08 A method of mounting a ducted fan gas turbine engine on an aircraft

Country Status (4)

Country Link
JP (1) JPH01229799A (en)
DE (1) DE3902325A1 (en)
FR (1) FR2628388B1 (en)
GB (1) GB2215290B (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2275308A (en) * 1993-02-20 1994-08-24 Rolls Royce Plc A mounting for coupling a turbofan gas turbine engine to an aircraft structure.
GB2312251A (en) * 1996-04-18 1997-10-22 Rolls Royce Plc Ducted fan gas turbine engine mounting
US7451947B2 (en) * 2003-11-25 2008-11-18 Airbus France Engine mounting structure under an aircraft wing
WO2013050715A1 (en) * 2011-10-06 2013-04-11 Aircelle Aircraft propulsion assembly
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2885878B1 (en) * 2005-05-23 2007-06-29 Airbus France Sas AIRCRAFT ENGINE ASSEMBLY
FR2885877B1 (en) * 2005-05-23 2008-12-12 Airbus France Sas AIRBORNE TURBOJET ENGINEERING MACHINE
FR2891246B1 (en) * 2005-09-26 2007-10-26 Airbus France Sas ENGINE ASSEMBLY FOR AN AIRCRAFT COMPRISING AN ENGINE AND A DEVICE FOR HITCHING SUCH AN ENGINE
US10266273B2 (en) 2013-07-26 2019-04-23 Mra Systems, Llc Aircraft engine pylon

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2151995A (en) * 1983-12-27 1985-07-31 Sabena Apparatus for the suspension of an aircraft engine cowling

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1318748A (en) * 1970-08-11 1973-05-31 Secr Defence Gas turgine ducted fan engines for aircraft
GB1521847A (en) * 1976-04-30 1978-08-16 Rolls Royce Attachment for attaching jet propulsion engines to vehicle structure
GB2061389B (en) * 1979-10-23 1983-05-18 Rolls Royce Rod installation for a gas turbine engine
US4361296A (en) * 1980-03-10 1982-11-30 The Boeing Company Uniflange coupling assembly
US4458863A (en) * 1980-03-10 1984-07-10 The Boeing Company Strut supported inlet
GB2119857A (en) * 1982-04-30 1983-11-23 Rolls Royce Ducted fan gas turbine engine
JPS5945559A (en) * 1982-09-08 1984-03-14 Toshiba Corp Control device
US4603821A (en) * 1983-12-30 1986-08-05 The Boeing Company System for mounting a jet engine
JPS6112134A (en) * 1984-06-27 1986-01-20 Mitsubishi Electric Corp Radio receiver

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2151995A (en) * 1983-12-27 1985-07-31 Sabena Apparatus for the suspension of an aircraft engine cowling

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2275308A (en) * 1993-02-20 1994-08-24 Rolls Royce Plc A mounting for coupling a turbofan gas turbine engine to an aircraft structure.
US5409184A (en) * 1993-02-20 1995-04-25 Rolls-Royce Plc Mounting for coupling a turbofan gas turbine engine to an aircraft structure
GB2275308B (en) * 1993-02-20 1997-02-26 Rolls Royce Plc A mounting for coupling a turbofan gas turbine engine to an aircraft structure
GB2312251A (en) * 1996-04-18 1997-10-22 Rolls Royce Plc Ducted fan gas turbine engine mounting
FR2747735A1 (en) * 1996-04-18 1997-10-24 Rolls Royce Plc SUPPORT OF A GAS TURBINE ENGINE WITH A CHANNEL BLOWER
US5860276A (en) * 1996-04-18 1999-01-19 Rolls-Royce Plc Ducted fan gas turbine engine mounting
GB2312251B (en) * 1996-04-18 1999-10-27 Rolls Royce Plc Ducted fan gas turbine engine mounting
US7451947B2 (en) * 2003-11-25 2008-11-18 Airbus France Engine mounting structure under an aircraft wing
WO2013050715A1 (en) * 2011-10-06 2013-04-11 Aircelle Aircraft propulsion assembly
FR2981046A1 (en) * 2011-10-06 2013-04-12 Aircelle Sa PROPELLANT AIRCRAFT ASSEMBLY
CN103842252A (en) * 2011-10-06 2014-06-04 埃尔塞乐公司 Aircraft propulsion assembly
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly

Also Published As

Publication number Publication date
JPH01229799A (en) 1989-09-13
FR2628388A1 (en) 1989-09-15
GB8805527D0 (en) 1988-04-07
GB2215290B (en) 1991-09-04
DE3902325A1 (en) 1989-09-21
FR2628388B1 (en) 1991-10-18

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Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee

Effective date: 20000308