WO1993006008A1 - Method of and apparatus for removing and replacing a part or parts of a gas turbine engine powerplant - Google Patents
Method of and apparatus for removing and replacing a part or parts of a gas turbine engine powerplant Download PDFInfo
- 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
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- WO
- WIPO (PCT)
- Prior art keywords
- powerplant
- parts
- gas turbine
- turbine engine
- aircraft
- Prior art date
Links
- 238000000034 method Methods 0.000 title claims abstract description 17
- 238000013519 translation Methods 0.000 claims 2
- 230000014616 translation Effects 0.000 claims 2
- 230000007246 mechanism Effects 0.000 description 5
- 238000004804 winding Methods 0.000 description 5
- 230000002950 deficient Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 1
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.
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- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A method of and apparatus for the removal and replacement of part of a gas turbine engine powerplant (10). Two beams (25) are attached to the pylon (13) from which the powerplant (10) is suspended from an aircraft. Those parts of the powerplant (10) which are not required to be moved are suspended from carriages (28, 29) which are translatable along the beams (25) when the parts which are to be removed are disconnected from the remainder of the power plant (10). The carriages (28, 29) together with the parts which they carry are then translated to a position which permits the removal of the remaining parts. Replacement of the removed part is essentially the reverse of the procedures for parts removed. The method reduces the time taken to replace powerplant parts.
Description
METHOD OF AND APPARATUS FOR REMOVING AND REPLACING
A PART OR PARTS OF A GAS TURBINE ENGINE POWERPLANT
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. If the particular problem with a powerplant is limited to a particular module or group of modules, it is clearly not efficient to remove all of the modules from the aircraft to solve the problem. It would be far more desirable to be able to remove the defective module or modules from the aircraft while leaving the remaining modules on the aircraft. This would enable only the defective module or modules to be replaced, thereby ensuring rapid re-entry into service of the aircraft.
It is an object of the present invention to provide a method of removing a gas turbine engine powerplant, or part thereof, from an aircraft and to its replacement which substantially avoids the aforementioned difficulties.
It is a further object of the present invention to provide apparatus for carrying out such a method.
According to the present invention, 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. According to a further aspect of the present invention, 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. The present invention will now be described, by way of example, with reference to the accompanying drawings in which:
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.
Figure 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. Referring to Figure 1, 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 noτ_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. During normal operation of the ducted fan gas turbine engine 12, the flaps 20 block correspondingly shaped apertures in the nacelle part 15 and the access doors 19. However when reverse thrust of the engine 12 is required for braking purposes, 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.
It will be seen therefore that all of the 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.
It is sometimes necessary to remove and replace part of the powerplant 10. The present invention is concerned with a method of achieving this end without the total removal of the powerplant 10 from the pylon 13.
When it is desired, for instance, to remove and replace the ducted fan gas turbine engine 12 but not the intake 16 and nozzle 17, the following procedure is followed:
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
32 on the engine 12. 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
33 on to a suitable cradle 34 as shown in interrupted lines in Figure 5. The cables 31 can then be disconnected from the engine 12 to permit it to be taken away for repair or maintenance work.
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.
Following the attachment of the intake 16 and the nozzle 17 to the nacelle part 15 all the various services to the engine 12 are attached. Finally the beams 25, together with the carriages 28 and 29 and the winding mechanism 33 are removed from the pylon 13.
It will be appreciated that under other circumstances, it may be desirable to remove only part of the gas turbine engine 12. Thus for instance, it may be desirable to remove the core of the engine 12, but not its fan assembly. Under these circumstances, the engine fan assembly would be supported from the beams 25 together with the intake 16 and nozzle 17 while the engine core is removed. It will be readily apparent to those skilled in the art that other powerplant parts could be removed whilst leaving the remainder effectively attached to the pylon 13.
It will be seen therefore that 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.
Although the present invention has been described with reference to a particular type of powerplant mounting, it will be apparent that it is also applicable to powerplants with different types of mounting.
Claims
1. A method of removing and replacing a part of a gas turbine engine powerplant (10) on an aircraft structure (13) characterised by the steps of temporarily attaching support structure (25) to said aircraft structure (13) at a position adjacent said gas turbine engine powerplant (10), attaching those parts of said powerplant (10) which are not required to be removed from said aircraft structure (13) to said temporary support structure (25), attaching those portions of said powerplant (10) to be removed to a crane, hoist or the like (33), disconnecting from the remainder of said powerplant and from said aircraft structure (13) said powerplant parts to be removed so that the remaining powerplant parts are solely supported from said aircraft structure (13) by said temporary support structure (25), removing said disconnected powerplant parts from said powerplant (10) using said crane, hoist or the like (33), replacing said removed powerplant parts on said powerplant (10) and connecting them thereto and to said aircraft structure (13) and subsequently removing said temporary support structure.
2_ A method of removing and replacing a part of a gas turbine engine powerplant as claimed in claim 1 characterised in that said powerplant parts which are not required to be removed from said aircraft structure (13) are translated to positions which permit the removal and replacement of the remainder of said powerplant parts, said temporary support structure (25) including means (28,29) to facilitate such translations.
3. Apparatus for use in the removal and replacement of a part of a gas turbine engine (10) powerplant mounted on an aircraft structure (13) characterised in that said apparatus comprises support means (25) for temporary attachment to said aircraft structure (13), means (28,29) for attaching to said temporary support structure (25) those parts of said powerplant (10) which are hot be removed and replaced, and a crane, hoist or the like (33) for use in the removal and replacement of those parts of said powerplant (10) which are to be removed and replaced.
4. Apparatus as claimed in claim 3 characterised in that said temporary support structure (25) comprises at least one beam.
5. Apparatus as claimed in claim 4 characterised in that said at least one beam (25) is adapted to be temporarily attached to a pylon (13) which supports said gas turbine engine powerplant (10).
6. Apparatus as claimed in claim 4 or claim 5 characterised in that one or more carriages (28,29) are mounted for translation along said beams (25), said one or more carriages (25) being adapted to support said parts of said powerplant which are not to be removed and replaced and translate those parts to positions which permit the removal and replacement of the remainder of said powerplant parts.
7. Apparatus as claimed in any one of claims 3 to 6 characterised in that said crane, hoist or the like (33) is mounted on said support structure (25).
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 (en) | 1993-04-01 |
Family
ID=10701547
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/GB1992/001369 WO1993006008A1 (en) | 1991-09-17 | 1992-07-24 | Method of and apparatus for removing and replacing a part or parts of a gas turbine engine powerplant |
Country Status (2)
| Country | Link |
|---|---|
| GB (1) | GB9119853D0 (en) |
| WO (1) | WO1993006008A1 (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2851226A1 (en) * | 2003-02-19 | 2004-08-20 | Snecma Moteurs | Carrier structure for turbo-propeller, has lower part that is fixed in dismountable way on upper part by pin, cavity, and bore, where lower part has girders extending in longitudinal direction and connecting lower arches |
| WO2007137812A1 (en) * | 2006-05-30 | 2007-12-06 | Airbus Deutschland Gmbh | Pylon with engine assembly |
| US7941905B2 (en) | 2005-08-04 | 2011-05-17 | Airbus Operations Limited | Method of removing a component from an aircraft |
| CN102101531A (en) * | 2009-12-22 | 2011-06-22 | 尤洛考普特德国有限公司 | Lift device for replacing dynamic or static components of helicopter-type aircraft |
| EP3109170A1 (en) * | 2015-06-23 | 2016-12-28 | Rohr, Inc. | Installing or removing aircraft engines |
| EP3572335A1 (en) * | 2018-05-24 | 2019-11-27 | Rolls-Royce plc | Mounting system and mounting method for gas turbine aero engine |
| CN110525682A (en) * | 2018-05-24 | 2019-12-03 | 劳斯莱斯有限公司 | Installation system and installation method for gas-turbine aeroengine |
| 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 |
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|---|---|---|---|---|
| FR2455547A1 (en) * | 1979-05-02 | 1980-11-28 | Boeing Co | Engine installation for aircraft gas turbine - has cowling linked to upper support by jack-screws permit removal for maintenance |
| 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 |
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1991
- 1991-09-17 GB GB919119853A patent/GB9119853D0/en active Pending
-
1992
- 1992-07-24 WO PCT/GB1992/001369 patent/WO1993006008A1/en active Application Filing
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2455547A1 (en) * | 1979-05-02 | 1980-11-28 | Boeing Co | Engine installation for aircraft gas turbine - has cowling linked to upper support by jack-screws permit removal for maintenance |
| 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)
| Title |
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| FLIGHT INTERNATIONAL vol. 98, no. 3217, 5 November 1970, LONDON pages 708 - 714 P. MIDDLETON 'RB.211: transatlantic bridgehead' * |
Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1449766A1 (en) * | 2003-02-19 | 2004-08-25 | Snecma Moteurs | Structural frame for a turbo-prop and assembly including such a structural frame |
| US7100869B2 (en) | 2003-02-19 | 2006-09-05 | Snecma Moteurs | Turboprop carrier structure and an assembly including such a carrier structure |
| FR2851226A1 (en) * | 2003-02-19 | 2004-08-20 | Snecma Moteurs | Carrier structure for turbo-propeller, has lower part that is fixed in dismountable way on upper part by pin, cavity, and bore, where lower part has girders extending in longitudinal direction and connecting lower arches |
| 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 (en) * | 2006-05-30 | 2007-12-06 | Airbus Deutschland Gmbh | Pylon with engine assembly |
| CN102101531B (en) * | 2009-12-22 | 2014-10-08 | 空客直升机德国有限公司 | Lift device for replacing dynamic or static components of helicopter-type aircraft |
| EP2338794A1 (en) * | 2009-12-22 | 2011-06-29 | Eurocopter Deutschland GmbH | Lift device for replacing dynamic or static components of helicopter-type aircraft |
| CN102101531A (en) * | 2009-12-22 | 2011-06-22 | 尤洛考普特德国有限公司 | Lift device for replacing dynamic or static components of helicopter-type aircraft |
| 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 (en) * | 2015-06-23 | 2020-08-19 | Rohr, Inc. | Installing or removing aircraft engines |
| EP3109170A1 (en) * | 2015-06-23 | 2016-12-28 | Rohr, Inc. | Installing or removing aircraft engines |
| CN106275505A (en) * | 2015-06-23 | 2017-01-04 | 罗尔公司 | Install or remove aircraft engine |
| 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 (en) * | 2018-05-24 | 2019-12-03 | 劳斯莱斯有限公司 | Installation system and installation method for gas-turbine aeroengine |
| EP3572335A1 (en) * | 2018-05-24 | 2019-11-27 | Rolls-Royce plc | Mounting system and mounting method for gas turbine aero engine |
| US11254447B2 (en) | 2018-05-24 | 2022-02-22 | Rolls-Royce Plc | Mounting system and mounting method for gas turbine aero engine |
| CN110525682B (en) * | 2018-05-24 | 2023-04-18 | 劳斯莱斯有限公司 | Mounting system and mounting method for a gas turbine aircraft engine |
| 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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