CN103303483A - Rotating mechanism for mounting and maintaining aero-engine - Google Patents
Rotating mechanism for mounting and maintaining aero-engine Download PDFInfo
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- CN103303483A CN103303483A CN2013101301389A CN201310130138A CN103303483A CN 103303483 A CN103303483 A CN 103303483A CN 2013101301389 A CN2013101301389 A CN 2013101301389A CN 201310130138 A CN201310130138 A CN 201310130138A CN 103303483 A CN103303483 A CN 103303483A
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- 238000012423 maintenance Methods 0.000 claims abstract description 33
- 238000009434 installation Methods 0.000 claims description 25
- 125000004122 cyclic group Chemical group 0.000 claims description 3
- 238000011084 recovery Methods 0.000 claims description 3
- 201000004384 Alopecia Diseases 0.000 description 3
- 231100000360 alopecia Toxicity 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 239000008358 core component Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000012467 final product Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 239000000047 product Substances 0.000 description 1
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Abstract
The invention discloses a rotating mechanism for mounting and maintaining an aero-engine, which comprises a hydraulic actuator cylinder, a front main bearing beam of an aircraft engine compartment, a front framework, an engine, cross beams, a rear bearing beam of the aircraft engine compartment, a rear framework, pins, an auxiliary mount, an accessory casing and a main mount, wherein the front framework, the rear framework and one cross beam form a fixed framework mechanism, the engine is fixedly arranged in the framework mechanism through the main mount and the auxiliary mount, the engine can be mounted on an aircraft through fixing the framework mechanism on the aircraft engine compartment, and the framework mechanism of the engine rotates by taking the pins as the axis and is used for controlling the rotating angle and height of the engine through the stretching length of the hydraulic actuator cylinder. The rotating mechanism for mounting and maintaining the aero-engine has the advantages that the stability is good, the weight of the engine is favorably lightened, the design difficulty of the engine is reduced, the occupied space is small, the maintaining efficiency is improved, the working reliability of the main mount and the auxiliary mount of the engine is ensured, and the rotating mechanism is suitable for equipment needing repeated hoisting maintenance in other industries.
Description
Technical field
The present invention relates to the aviation series products installation, safeguard and to use mechanism, particularly a kind of aero-engine installation and maintenance rotating mechanism.
Background technology
Aero-engine is the core component of aircraft, and it needs regular handling labor, to guarantee not influence the attendance rate, safety and the maintenance cost of aircraft.In the handling labor of driving engine, the handling labor of engine accessory power rating has been occupied most maintenance workload again, so the convenience that engine accessory power rating is safeguarded has great significance for the maintainability that improves driving engine and aircraft.
For the aircraft that adopts the built-in type driving engine to install, in order to guarantee that aircraft has less wind area, the annex of driving engine usually needs to be arranged in side or side-lower, like this because the spacing of engine accessory power rating and aircraft bulkhead is little, machinery space is higher apart from ground, and the ground crew can't directly safeguard annex and system.Therefore common way is by a High Altitude Platform, sets up the maintenance window that can raise at the aircraft engine nacelle place and carries out maintenance, perhaps by special hanging device or driving engine installation unwheeling etc. driving engine is decomposed from aircraft and carries out the alopecia maintenance.Set up maintenance window and can destroy the structure integrity of aircraft, and for some specific aircraft configuration, maintenance window may be subject to other structures and become infeasible; Existing alopecia handling labor need be by outside main equipment or instrument, base or the maintenance factory perfect for hardware facility can provide these equipment, other numerous airports then are difficult to possess these conditions, and because these equipment volume are bigger, be not easy to transportation and dispose, therefore limited the alerting ability of big-and-middle-sized aircraft maintenance.
Summary of the invention
The objective of the invention is to reduce driving engine dependence to outside complex apparatus when safeguarding, the spy provides a kind of aero-engine installation and maintenance rotating mechanism as far as possible.
The invention provides a kind of aero-engine installation and maintenance rotating mechanism, it is characterized in that: described aero-engine installation and maintenance rotating mechanism, comprise that hydraulic actuator 1 sees Fig. 1 and two states of Fig. 2, main bearing beam 2 before the aircraft engine nacelle, stationary engine front baffle 3, driving engine 4, the first crossbeams 5, bearing beam 6 behind the aircraft engine nacelle, stationary engine is assisted joint 9 is installed with rear frame 7, the first pins 8, accessory drive gearbox 10, main joint 11, the second pins 12, the second crossbeams 13 of installing, the 3rd pin 14, the four pins 15;
Wherein: stationary engine is formed a fixing frame mechanism with front baffle 3, stationary engine with rear frame 7 and second crossbeam 13, driving engine 4 is fixed in the frame mechanism with the auxiliary joint 9 of installing by the main joint 11 of installing, and this frame mechanism is fixed on the aircraft engine nacelle and driving engine 4 can be installed on the aircraft;
When safeguarding, remove the affixed of frame mechanism and machinery space, be connected before the aircraft engine nacelle on the hydraulic actuator 1 on the main bearing beam 2 and engine frame by the 3rd pin the 14 and the 4th pin 15, engine frame mechanism is the axle center rotation with first pin, 8 and second pin 12, control angle and the height of engine rotation by the length of hydraulic actuator 1 stretching, extension, when hydraulic actuator 1 is stretched over maximum length, driving engine 4 will rotate to maximum angle and minimum position along with frame mechanism, at this moment accessory drive gearbox 10 rotates under the aircraft, and the annex height that need safeguard also has been reduced to service personnel need not be by the exercisable position of outside platform; After safeguard finishing, hydraulic actuator 1 contracted length, when being retracted to length hour that frame mechanism and aircraft engine nacelle is affixed, driving engine recovery normal operation.
Described stationary engine is the semiellipse cyclic structure with front baffle 3 and stationary engine with rear frame 7.
Driving engine main installs that joint is fixed on the front baffle, the auxiliary joint of installing is arranged on the rear frame, and front and back framework and crossbeam are just affixed with driving engine before driving engine is installed, thereby the driving engine installation is exactly the process of installation frame mechanism; Rear frame mechanism is installed captives joint with aircraft engine nacelle, and overlap joint gets well forward and backward framework and be connected with the pin that the aircraft engine nacelle load is striden between the beam, and hydraulic actuator is connected with the pin that frame mechanism and aircraft engine nacelle load are striden beam respectively; When the driving engine Flight Line Maintenance, the releasing frame mechanism is captiveed joint with aircraft engine nacelle, stretching, extension by hydraulic actuator, allow driving engine along with frame mechanism rotates, under making that the engine accessory power rating casing rotates to aircraft from side or side-lower, thereby not needing outside Oversize vehicle to set up under the situation about being equipped with, finish the maintenance to systems such as engine accessory power rating casings.
Advantage of the present invention:
Aero-engine installation and maintenance rotating mechanism of the present invention, the anglec of rotation is big, under pressurized strut full extension state, reach the maximum anglec of rotation, the accessory device that is conducive to be positioned at driving engine side or side-lower is safeguarded under rotating to aircraft, simultaneously under the effect of the pulling force of pressurized strut full extension and driving engine gravity, entire mechanism will keep well stability, show as at maintainability fast and safely: accessibility is good when using this mechanism to safeguard, personnel can stand directly on ground and keep in repair; When using this mechanism to keep in repair or reengine, can reduce the dependence to equipment such as ground major repair cars, low to the outfield maintenance requirement; Good stability when using this mechanism to keep in repair is conducive to improve maintenance efficiency; More flexible when using this mechanism to make the engine accessory power rating design, be conducive to alleviate engine weight, reduce the engine design difficulty.
It is little to take up room, it is affixed with driving engine that the frame segment that belongs to aircraft engine nacelle originally is set a roof beam in place, installation process only needs this frame mechanism is connected with the aircraft bearing beam, and swivel pin is the occupying volume external space not, and pressurized strut is placed in the space between frame mechanism and aircraft bearing beam and gets final product.The framework that described aero-engine installation and maintenance rotating mechanism is affixed driving engine rotates with respect to aircraft engine nacelle, the main and auxiliary installation joint of driving engine all is installed on the frame mechanism, avoided conventional engines process of the most complicated main and auxiliary installation joint of aligning during re-engine after alopecia like this, improved maintenance efficiency, guaranteed the reliability of the main and auxiliary installation joint of driving engine work; Be applicable to the equipment that needs to lift repeatedly maintenance in the other industry.
Description of drawings
The present invention is further detailed explanation below in conjunction with drawings and the embodiments:
Fig. 1 is installing condition aero-engine installation and maintenance rotating mechanism scheme drawings;
Fig. 2 is service mode aero-engine installation and maintenance rotating mechanism scheme drawings;
Fig. 3 is aero-engine installation and maintenance rotating mechanism scheme drawing;
Fig. 4 is driving engine installing condition scheme drawing aboard.
The specific embodiment
Present embodiment provides a kind of aero-engine installation and maintenance rotating mechanism, it is characterized in that: described aero-engine installation and maintenance rotating mechanism, comprise that hydraulic actuator 1 sees Fig. 1 and two states of Fig. 2, main bearing beam 2 before the aircraft engine nacelle, stationary engine front baffle 3, driving engine 4, the first crossbeams 5, bearing beam 6 behind the aircraft engine nacelle, stationary engine is assisted joint 9 is installed with rear frame 7, the first pins 8, accessory drive gearbox 10, main joint 11, the second pins 12, the second crossbeams 13 of installing, the 3rd pin 14, the four pins 15;
Wherein: stationary engine is formed a fixing frame mechanism with front baffle 3, stationary engine with rear frame 7 and second crossbeam 13, driving engine 4 is fixed in the frame mechanism with the auxiliary joint 9 of installing by the main joint 11 of installing, and this frame mechanism is fixed on the aircraft engine nacelle and driving engine 4 can be installed on the aircraft;
When safeguarding, remove the affixed of frame mechanism and machinery space, be connected before the aircraft engine nacelle on the hydraulic actuator 1 on the main bearing beam 2 and engine frame by the 3rd pin the 14 and the 4th pin 15, engine frame mechanism is the axle center rotation with first pin, 8 and second pin 12, control angle and the height of engine rotation by the length of hydraulic actuator 1 stretching, extension, when hydraulic actuator 1 is stretched over maximum length, driving engine 4 will rotate to maximum angle and minimum position along with frame mechanism, at this moment accessory drive gearbox 10 rotates under the aircraft, and the annex height that need safeguard also has been reduced to service personnel need not be by the exercisable position of outside platform; After safeguard finishing, hydraulic actuator 1 contracted length, when being retracted to length hour that frame mechanism and aircraft engine nacelle is affixed, driving engine recovery normal operation.
Described stationary engine is the semiellipse cyclic structure with front baffle 3 and stationary engine with rear frame 7.
Driving engine main installs that joint is fixed on the front baffle, the auxiliary joint of installing is arranged on the rear frame, and front and back framework and crossbeam are just affixed with driving engine before driving engine is installed, thereby the driving engine installation is exactly the process of installation frame mechanism; Rear frame mechanism is installed captives joint with aircraft engine nacelle, and overlap joint gets well forward and backward framework and be connected with the pin that the aircraft engine nacelle load is striden between the beam, and hydraulic actuator is connected with the pin that frame mechanism and aircraft engine nacelle load are striden beam respectively; When the driving engine Flight Line Maintenance, the releasing frame mechanism is captiveed joint with aircraft engine nacelle, stretching, extension by hydraulic actuator, allow driving engine along with frame mechanism rotates, under making that the engine accessory power rating casing rotates to aircraft from side or side-lower, thereby not needing outside Oversize vehicle to set up under the situation about being equipped with, finish the maintenance to systems such as engine accessory power rating casings.
Claims (2)
1. aero-engine installation and maintenance rotating mechanism, it is characterized in that: described aero-engine installation and maintenance rotating mechanism, comprise hydraulic actuator (1), main bearing beam (2) before the aircraft engine nacelle, stationary engine front baffle (3), driving engine (4), first crossbeam (5), bearing beam behind the aircraft engine nacelle (6), stationary engine rear frame (7), first pin (8), the auxiliary joint (9) of installing, accessory drive gearbox (10), the main joint (11) of installing, second pin (12), second crossbeam (13), the 3rd pin (14), the 4th pin (15);
Wherein: stationary engine is formed a fixing frame mechanism with front baffle (3), stationary engine with rear frame (7) and second crossbeam (13), driving engine (4) is installed joint (11) and is assisted installation joint (9) to be fixed in the frame mechanism by main, and this frame mechanism is fixed on the aircraft engine nacelle and driving engine (4) can be installed on the aircraft;
Bearing beam (6) behind main bearing beam (2) and the aircraft engine nacelle before first crossbeam (5) the connection aircraft engine nacelle; Stationary engine is connected with second crossbeam (13) by first pin (8) with rear frame (7); Stationary engine is connected with second crossbeam (13) by second pin (12) with front baffle (3); The auxiliary joint (9) of installing is installed in stationary engine with on the rear frame (7);
When safeguarding, remove the affixed of frame mechanism and machinery space, be connected on the hydraulic actuator (1) on the preceding main bearing beam (2) of aircraft engine nacelle and the engine frame by the 3rd pin (14) and the 4th pin (15), engine frame mechanism is the axle center rotation with first pin (8) and second pin (12), control angle and the height of engine rotation by the length of hydraulic actuator (1) stretching, extension, when hydraulic actuator (1) is stretched over maximum length, driving engine (4) will rotate to maximum angle and minimum position along with frame mechanism, accessory drive gearbox (10) rotates under the aircraft, and the annex height that need safeguard also has been reduced to service personnel need not be by the exercisable position of outside platform; After safeguard finishing, hydraulic actuator (1) contracted length, when being retracted to length hour that frame mechanism and aircraft engine nacelle is affixed, driving engine recovery normal operation.
2. according to the described aero-engine installation and maintenance of claim 1 rotating mechanism, it is characterized in that: described stationary engine is the semiellipse cyclic structure with front baffle (3) and stationary engine with rear frame (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310130138.9A CN103303483B (en) | 2013-04-16 | 2013-04-16 | A kind of aero-engine installation and maintenance rotating mechanism |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310130138.9A CN103303483B (en) | 2013-04-16 | 2013-04-16 | A kind of aero-engine installation and maintenance rotating mechanism |
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| Publication Number | Publication Date |
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| CN103303483A true CN103303483A (en) | 2013-09-18 |
| CN103303483B CN103303483B (en) | 2015-12-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310130138.9A Active CN103303483B (en) | 2013-04-16 | 2013-04-16 | A kind of aero-engine installation and maintenance rotating mechanism |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3039824A1 (en) * | 2015-08-07 | 2017-02-10 | Snecma | KIT FOR GUIDING AN AIRCRAFT TURBOMACHINE DURING ITS INSTALLATION / REMOVAL ALONG A CRIB |
| CN108820246A (en) * | 2018-07-25 | 2018-11-16 | 中国科学院工程热物理研究所 | A kind of small-size turbojet engine quickly upper machine mounting structure and method |
| CN109367813A (en) * | 2018-10-26 | 2019-02-22 | 中国南方航空股份有限公司 | A kind of aircraft APU rear bearing cavity maintenance tool |
| CN113277094A (en) * | 2020-02-19 | 2021-08-20 | 通用电气公司 | Aircraft and propulsion engine mounting system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6292999B1 (en) * | 1998-09-25 | 2001-09-25 | Stanley Aviation Corporation | Method of installing and removing jet aircraft engine |
| WO2008125631A1 (en) * | 2007-04-13 | 2008-10-23 | Airbus France | Device for attaching an aircraft engine and aircraft comprising at least one such device |
| WO2008148722A1 (en) * | 2007-06-04 | 2008-12-11 | Airbus France | Aircraft turboprop attachment device comprising hydraulic fastening means |
| CN101797981A (en) * | 2008-12-24 | 2010-08-11 | 通用电气公司 | Method and apparatus for mounting and dismounting an aircraft engine |
| CN203581386U (en) * | 2013-04-16 | 2014-05-07 | 中国航空工业集团公司沈阳发动机设计研究所 | Rotating mechanism for mounting and maintaining aero-engine |
-
2013
- 2013-04-16 CN CN201310130138.9A patent/CN103303483B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6292999B1 (en) * | 1998-09-25 | 2001-09-25 | Stanley Aviation Corporation | Method of installing and removing jet aircraft engine |
| WO2008125631A1 (en) * | 2007-04-13 | 2008-10-23 | Airbus France | Device for attaching an aircraft engine and aircraft comprising at least one such device |
| WO2008148722A1 (en) * | 2007-06-04 | 2008-12-11 | Airbus France | Aircraft turboprop attachment device comprising hydraulic fastening means |
| CN101797981A (en) * | 2008-12-24 | 2010-08-11 | 通用电气公司 | Method and apparatus for mounting and dismounting an aircraft engine |
| CN203581386U (en) * | 2013-04-16 | 2014-05-07 | 中国航空工业集团公司沈阳发动机设计研究所 | Rotating mechanism for mounting and maintaining aero-engine |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3039824A1 (en) * | 2015-08-07 | 2017-02-10 | Snecma | KIT FOR GUIDING AN AIRCRAFT TURBOMACHINE DURING ITS INSTALLATION / REMOVAL ALONG A CRIB |
| CN108820246A (en) * | 2018-07-25 | 2018-11-16 | 中国科学院工程热物理研究所 | A kind of small-size turbojet engine quickly upper machine mounting structure and method |
| CN109367813A (en) * | 2018-10-26 | 2019-02-22 | 中国南方航空股份有限公司 | A kind of aircraft APU rear bearing cavity maintenance tool |
| CN109367813B (en) * | 2018-10-26 | 2023-11-10 | 中国南方航空股份有限公司 | Maintenance tool for rear bearing cavity of aircraft APU |
| CN113277094A (en) * | 2020-02-19 | 2021-08-20 | 通用电气公司 | Aircraft and propulsion engine mounting system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103303483B (en) | 2015-12-30 |
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