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WO1993006008A1 - Procede et appareil permettant de deposer et de reposer une ou plusieurs pieces situees dans un groupe motopropulseur a turboreacteur - Google Patents

Procede et appareil permettant de deposer et de reposer une ou plusieurs pieces situees dans un groupe motopropulseur a turboreacteur Download PDF

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Publication number
WO1993006008A1
WO1993006008A1 PCT/GB1992/001369 GB9201369W WO9306008A1 WO 1993006008 A1 WO1993006008 A1 WO 1993006008A1 GB 9201369 W GB9201369 W GB 9201369W WO 9306008 A1 WO9306008 A1 WO 9306008A1
Authority
WO
WIPO (PCT)
Prior art keywords
powerplant
parts
gas turbine
turbine engine
aircraft
Prior art date
Application number
PCT/GB1992/001369
Other languages
English (en)
Inventor
Arnold Charles Newton
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
Publication of WO1993006008A1 publication Critical patent/WO1993006008A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/40—Maintaining or repairing aircraft

Definitions

  • This invention relates to a method of and apparatus for the removal and replacement of a part or parts of a gas turbine engine powerplant and in particular to such a powerplant mounted on an aircraft.
  • a common and convenient way of mounting a gas turbine engine powerplant on an aircraft is to suspend the powerplant from a pylon mounted on the underside of the aircraft wing. It is inevitable that at some time, a part or parts of the powerplant will have to be removed for repair or replacement. Frequently this involves the removal of the whole powerplant from the aircraft whereupon it is taken away for dissembly. Modern gas turbine engine powerplants are frequently built on a modular basis.
  • a method of removing and replacing a part of a gas turbine engine powerplant on an aircraft comprises the steps of temporarily attaching support structure to said aircraft at a position adjacent said gas turbine engine powerplant, attaching those parts of said powerplant which are not required to be removed from said aircraft to said support structure, attaching those portions of said powerplant to be removed to a crane, hoist or the like, disconnecting from the remainder of said powerplant and said aircraft said powerplant parts to be removed so that the remaining powerplant parts are solely supported from said aircraft by said temporary support structure, removing said disconnected powerplant parts from said powerplant using said crane, hoist or the like, replacing said removed powerplant parts on said powerplant and connecting them thereto and to said aircraft, and subsequently removing said temporary support structure.
  • apparatus for use in the removal and replacement of a part of a gas turbine engine powerplant mounted on an aircraft comprises support means for temporary attachment to said aircraft, means for attaching said support structure to those parts of said powerplant which are not to be removed and replaced, and a crane, hoist or the like for use in the removal and replacement of those parts of said powerplant which are to be removed and replaced.
  • Figure 1 is a side view of a gas turbine engine powerplant, part of which is removable in accordance with the method of the present invention.
  • Figure 2 is a view on section line A-A of Figure 1.
  • Figure 3 is a view on section line B-B of Figure 2.
  • Figure 4 is a perspective view of the gas turbine engine powerplant shown in Figure 1 indicating how part of the nacelle of the powerplant is pivotally mounted on the remainder of the nacelle.
  • FIG 5 is a side view of the gas turbine engine powerplant shown in Figure 1 in a partially dissembled state indicating the manner in which part of the powerplant is removable in accordance with the method of the present invention and showing apparatus in accordance with the present invention.
  • Figure 6 is a view on section line C-C of Figure 5.
  • a gas turbine engine powerplant generally indicated at 10 comprises a nacelle 11 which encloses a ducted fan gas turbine engine 12 (shown in interrupted lines).
  • the powerplant 12 is suspended by means of a pylon 13 from an aircraft wing 14.
  • the ducted fan gas turbine engine 12 is of conventional configuration. It will not, therefore, be described in any further detail.
  • the pylon 13 is likewise of generally conventional configuration. However a part 15 of the nacelle 11 is structurally integral with the pylon 13. Specifically the nacelle part 15 is a part of the upper half of the nacelle 11 which is located in the mid-region of the nacelle 11. It is of inverted generally u-shaped cross-section and interconnects the fully annular parts 16 and 17 of the nacelle 11 which define the powerplant intake and final nozzle. The intake 16 and 17 are attached to the nacelle part 15 by conventional bolted joints.
  • the lower half of the nacelle 11 immediately below the nacelle part 15 is interposed between but is no ⁇ _r attached to the intake 16 and nozzle 17.
  • the lower nacelle half 18 is constituted by two similar access doors 19, one of which can be seen in Figures 1 and 4. Each access door 19 is pivotally attached to the nacelle part 15 so that it can be pivoted away from the remainder of the nacelle 11, as can be seen in Figure 4 to provide maintenance access to the ducted fan gas turbine engine 12. Additionally, the access doors 19 are removable from the nacelle part 15 to facilitate at least partial powerplant removal in accordance with the method of the present invention.
  • Each of the access doors 19 and the nacelle part 15 is provided with a pivotable flap 20.
  • the flaps 20 block correspondingly shaped apertures in the nacelle part 15 and the access doors 19.
  • the flaps 20 pivot open. They pivot in such a way as to divert at least some of the fan by-pass air passing through the engine 12 in a generally forwards direction.
  • nacelle 11 is either directly or indirectly carried by the pylon 13; the nacelle part 15 being structurally integral with the pylon 13 while the remainder of the nacelle 11 is carried by the nacelle part 15. None of the nacelle 11 is carried by the ducted fan gas turbine engine 12.
  • the ducted fan gas turbine engine 12 is supported within the nacelle 11 at four locations: one at the rear of the engine and three at the front.
  • the rear engine mounting 21 can be seen in Figure 3. It is of conventional configuration and interconnects the turbine casing of the engine 12 and the pylon 13.
  • the front of the engine 12 is supported by three mountings 22,23 and 24 which can be seen in Figure 2.
  • the mountings 22 and 24 are located in a horizontal plane containing the longitudinal axis of the engine 12 and interconnect the fan casing of the ducted fan engine 12 with "the nacelle part 15.
  • the mounting 23 is located at the top of the fan casing and interconnects the fan casing with the pylon 13.
  • the fan casing is the largest diameter part of the engine 12 and surrounds the engines' fan blades 25 visible in Figure 4. All of the mountings 22,23 and 24 are of the same general type and, together with the rear mounting 21, are readily releasable to permit the removal of the engine 12 from the pylon 13.
  • the present invention is concerned with a method of achieving this end without the total removal of the powerplant 10 from the pylon 13.
  • Two similar beams 25, which can be seen in Figures 5 and 6, are temporarily attached to the pylon 13. Specifically one beam 25 is positioned each side of the pylon 13 so that the beams 25 are parallel with each other and located horizontally above the powerplant 10.
  • the beams 25 are interconnected by a series of bars, one of which 26 can be seen in Figure 6, which pass through suitable bushes 27 provided in the pylon 13.
  • the pylon 13 therefore supports the beams 25.
  • the beams 25 each carry two carriages 28 and 29.
  • the carriages 28 and 29 are adapted to translate along their respective beams 25 and are provided with support cables 30.
  • the support cables 30 are attached to the intake 16 and nozzle 17 so that the intake 16 is interconnected with the carriage 28 and the carriage 29 interconnected with the nozzle 17.
  • the intake 16 and nozzle 17 are then disconnected from the nacelle part 15 and the carriages 28 and 29 translated to the positions shown in Figure 5 where they are clear of the engine 12.
  • the access doors 19 are then removed although it may be possible to merely pivot them to their fully open position.
  • Four cables 31 (shown in interrupted lines in Figure 5 and also visible in Figure 6) are then attached to suitable lugs
  • the cables 31 pass through apertures in the nacelle part 15 to be attached to a suitable winding mechanism 33 positioned on the beams 25. It will be appreciated however that different winding or hoist mechanisms could be employed if desired. Indeed it may be desirable under certain circumstances to employ a free-standing crane (not shown) which is not directly attached to the beams 25. The engine mountings 21-24 are then disconnected to permit the engine 12 to be lowered by the winding mechanism
  • a replacement engine 12 on a cradle 24 is then positioned immediately below the pylon 13 and the cables 31 attached to it.
  • the engine is then raised by the operation of the winding mechanism 33 until it is appropriately positioned for its attachment by the mountings 21-24 to the nacelle part 15 and the pylon 13.
  • the access doors 19 are then re-attached and the carriages 28 and 29 translated along the beams 25 to position the intake 16 and nozzle 17 for attachment to the nacelle part 15.
  • the method of the present invention facilitates the rapid replacement of gas turbine engine powerplant parts without the time and expense involved in removing the whole powerplant from the aircraft upon which it is mounted.

Landscapes

  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Procédé et appareil permettant de déposer et de reposer une pièce située dans un groupe motopropulseur à turboréacteur (10). Deux poutres (25) sont fixées au pylône (13) par l'intermédiaire duquel le groupe motopropulseur (10) est suspendu à l'aéronef. Les parties du groupe motopropulseur (10) qui n'ont pas besoin d'être retirées sont suspendues à des chariots (28, 29) pouvant effectuer un mouvement de translation le long des poutres (25) lors du désassemblage des pièces devant être retirées de la partie restante du groupe motopropulseur (10). Les chariots (28, 29) ainsi que les pièces qu'ils portent sont déplacés vers une position permettant la dépose des pièces restantes. Les modes opératoires de repose des pièces sont essentiellement l'inverse des modes opératoires mis en ÷uvre pour leur démontage. Le procédé permet de réduire le temps nécessaire à la dépose/repose des pièces du groupe motopropulseur.
PCT/GB1992/001369 1991-09-17 1992-07-24 Procede et appareil permettant de deposer et de reposer une ou plusieurs pieces situees dans un groupe motopropulseur a turboreacteur WO1993006008A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB9119853.1 1991-09-17
GB919119853A GB9119853D0 (en) 1991-09-17 1991-09-17 Method of and apparatus for removing and replacing a part or parts of a gas turbine engine powerplant

Publications (1)

Publication Number Publication Date
WO1993006008A1 true WO1993006008A1 (fr) 1993-04-01

Family

ID=10701547

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB1992/001369 WO1993006008A1 (fr) 1991-09-17 1992-07-24 Procede et appareil permettant de deposer et de reposer une ou plusieurs pieces situees dans un groupe motopropulseur a turboreacteur

Country Status (2)

Country Link
GB (1) GB9119853D0 (fr)
WO (1) WO1993006008A1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2851226A1 (fr) * 2003-02-19 2004-08-20 Snecma Moteurs Structure porteuse pour un turbopropulseur et ensemble comportant une telle structure porteuse
WO2007137812A1 (fr) * 2006-05-30 2007-12-06 Airbus Deutschland Gmbh Pylône avec assemblage de moteur
US7941905B2 (en) 2005-08-04 2011-05-17 Airbus Operations Limited Method of removing a component from an aircraft
CN102101531A (zh) * 2009-12-22 2011-06-22 尤洛考普特德国有限公司 用于更换直升机型飞机的动态或静态部件的提升设备
EP3109170A1 (fr) * 2015-06-23 2016-12-28 Rohr, Inc. Installation ou retrait de moteurs d'avion
EP3572335A1 (fr) * 2018-05-24 2019-11-27 Rolls-Royce plc Système et procédé de montage pour moteur à turbine à gaz d'aéronef
CN110525682A (zh) * 2018-05-24 2019-12-03 劳斯莱斯有限公司 用于气体涡轮飞机引擎的安装系统和安装方法
US10899463B2 (en) 2017-05-16 2021-01-26 Rohr, Inc. Segmented pylon for an aircraft propulsion system
US20220349361A1 (en) * 2021-03-03 2022-11-03 Whisper Aero Inc. Propulsor wing trailing edge exhaust area control
US12291977B2 (en) 2021-03-03 2025-05-06 Whisper Aero Inc. Propulsor fan array

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2455547A1 (fr) * 1979-05-02 1980-11-28 Boeing Co Groupe-moteur pour avion
GB2069427A (en) * 1981-02-12 1981-08-26 British Aerospace Aircraft powerplant housings
GB2151995A (en) * 1983-12-27 1985-07-31 Sabena Apparatus for the suspension of an aircraft engine cowling

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2455547A1 (fr) * 1979-05-02 1980-11-28 Boeing Co Groupe-moteur pour avion
GB2069427A (en) * 1981-02-12 1981-08-26 British Aerospace Aircraft powerplant housings
GB2151995A (en) * 1983-12-27 1985-07-31 Sabena Apparatus for the suspension of an aircraft engine cowling

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
FLIGHT INTERNATIONAL vol. 98, no. 3217, 5 November 1970, LONDON pages 708 - 714 P. MIDDLETON 'RB.211: transatlantic bridgehead' *

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1449766A1 (fr) * 2003-02-19 2004-08-25 Snecma Moteurs Structure porteuse pour un turbopropulseur et ensemble comportant une telle structure porteuse
US7100869B2 (en) 2003-02-19 2006-09-05 Snecma Moteurs Turboprop carrier structure and an assembly including such a carrier structure
FR2851226A1 (fr) * 2003-02-19 2004-08-20 Snecma Moteurs Structure porteuse pour un turbopropulseur et ensemble comportant une telle structure porteuse
US20110185553A1 (en) * 2005-08-04 2011-08-04 Airbus Uk Limited Removal of components from aircraft
US7941905B2 (en) 2005-08-04 2011-05-17 Airbus Operations Limited Method of removing a component from an aircraft
US8850682B2 (en) 2005-08-04 2014-10-07 Airbus Operations Limited Removal of components from aircraft
WO2007137812A1 (fr) * 2006-05-30 2007-12-06 Airbus Deutschland Gmbh Pylône avec assemblage de moteur
CN102101531B (zh) * 2009-12-22 2014-10-08 空客直升机德国有限公司 用于更换直升机型飞机的动态或静态部件的提升设备
EP2338794A1 (fr) * 2009-12-22 2011-06-29 Eurocopter Deutschland GmbH Dispositif de levage pour le remplacement des composants dynamiques et statiques d'un aéronef de type helicoptère
CN102101531A (zh) * 2009-12-22 2011-06-22 尤洛考普特德国有限公司 用于更换直升机型飞机的动态或静态部件的提升设备
US8695817B2 (en) 2009-12-22 2014-04-15 Airbus Helicopters Deutschland GmbH Lifting device for replacing dynamic or static components of helicopter-type aircraft
EP3696095A1 (fr) * 2015-06-23 2020-08-19 Rohr, Inc. Installation ou retrait de moteurs d'avion
EP3109170A1 (fr) * 2015-06-23 2016-12-28 Rohr, Inc. Installation ou retrait de moteurs d'avion
CN106275505A (zh) * 2015-06-23 2017-01-04 罗尔公司 安装或移除飞机发动机
US9783313B2 (en) 2015-06-23 2017-10-10 Rohr, Inc. Installing or removing aircraft engines
US10899463B2 (en) 2017-05-16 2021-01-26 Rohr, Inc. Segmented pylon for an aircraft propulsion system
CN110525682A (zh) * 2018-05-24 2019-12-03 劳斯莱斯有限公司 用于气体涡轮飞机引擎的安装系统和安装方法
EP3572335A1 (fr) * 2018-05-24 2019-11-27 Rolls-Royce plc Système et procédé de montage pour moteur à turbine à gaz d'aéronef
US11254447B2 (en) 2018-05-24 2022-02-22 Rolls-Royce Plc Mounting system and mounting method for gas turbine aero engine
CN110525682B (zh) * 2018-05-24 2023-04-18 劳斯莱斯有限公司 用于气体涡轮飞机引擎的安装系统和安装方法
US20220349361A1 (en) * 2021-03-03 2022-11-03 Whisper Aero Inc. Propulsor wing trailing edge exhaust area control
US12006891B2 (en) * 2021-03-03 2024-06-11 Whisper Aero Inc. Propulsor wing trailing edge exhaust area control
US12291977B2 (en) 2021-03-03 2025-05-06 Whisper Aero Inc. Propulsor fan array

Also Published As

Publication number Publication date
GB9119853D0 (en) 1991-10-30

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