CN110745250A - Assembly type mounting structure and mounting method for ignition accessory of aero-engine - Google Patents
Assembly type mounting structure and mounting method for ignition accessory of aero-engine Download PDFInfo
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- CN110745250A CN110745250A CN201911153216.0A CN201911153216A CN110745250A CN 110745250 A CN110745250 A CN 110745250A CN 201911153216 A CN201911153216 A CN 201911153216A CN 110745250 A CN110745250 A CN 110745250A
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- 238000000034 method Methods 0.000 title claims abstract description 18
- 238000009434 installation Methods 0.000 claims abstract description 36
- 230000008569 process Effects 0.000 abstract description 8
- 238000013461 design Methods 0.000 abstract description 2
- 210000000078 claw Anatomy 0.000 description 5
- 239000000306 component Substances 0.000 description 3
- 238000013016 damping Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002457 bidirectional effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Mechanical Engineering (AREA)
- Connection Of Plates (AREA)
- Vibration Prevention Devices (AREA)
Abstract
An aircraft engine ignition accessory assembly type mounting structure and a mounting method belong to the technical field of aircraft engine assembly design. Aeroengine ignition annex assembled mounting structure, including installing support, first support and second support, the installing support is provided with first pin, second pin and finger shape contact, first pin and second pin all are connected with aeroengine installation limit through first support, the finger shape contact is connected with aeroengine installation limit through the second support, and first support is provided with joint bearing for with first pin or second pin joint, the second support also is provided with joint bearing for with finger shape contact connection. The assembly type installation structure and the installation method of the ignition accessory of the aero-engine ensure that the ignition accessory is reliably installed, the working process is stable and free of damage, and the aero-engine is ensured to normally work.
Description
Technical Field
The invention belongs to the technical field of assembly design of aero-engines, and particularly relates to an assembly type mounting structure and a mounting method for ignition accessories of an aero-engine.
Background
The installation of current engine ignition system adopts the mode of plate holder screw fixation, because of ignition annex bulky, weight is heavy, and for the down-set slope installation, receives environmental factor influences such as vibration, high temperature in engine working process, and the support mounting claw of installation fixed ignition annex often breaks down the trouble such as. After the mounting claws are broken, the influence of vibration on ignition accessories is intensified, so that the faults of crack damage of the ignition accessories, breakage of electrical connection parts and the like are generally caused, the ignition of an engine combustion chamber is influenced, the problems of unsuccessful ignition of the engine and the like are caused, the work of the engine is influenced, and the airplane cannot finish the subjects according to the preset requirements.
As shown in fig. 1, the existing ignition accessories of the aero-engine are all installed by using an integral installation base, the installation base is made of a whole metal plate, 4 metal installation claws are welded on the installation base, and an engine case and the installation base are fixed through the installation claws. As shown in figure 2, the ignition accessory is installed on the installation seat through a bolt, the installation seat is fixed on the engine casing through the bolt, the installation and the fixation of the ignition accessory are realized, and the installation of the whole ignition accessory is a rigid structure. The ignition accessory is large in size and 7kg in weight, after the ignition accessory is mounted on a circular shell of an engine, stress generated by screw fixation is increased due to vibration generated in the working process of the engine, due to the fact that the circular shell is mounted, stress concentration is generated on a mounting bracket of the ignition accessory, the bracket is damaged, the ignition accessory is not firmly mounted, an engine ignition system cannot stably work, meanwhile, the rejection rate of the ignition accessory bracket is high, and replacement cost is high.
Disclosure of Invention
In order to solve the technical problems of difficult installation and fixation, high damage rate and the like of ignition accessories caused by the factors of limited installation space, stress and the like in the prior art, the invention provides the assembly type installation structure and the installation method of the ignition accessories of the aero-engine, which ensure the reliable installation and fixation of the ignition accessories, the stable working process and no damage and ensure the normal work of the aero-engine.
In order to achieve the purpose, the technical scheme of the invention is as follows:
an aircraft engine ignition accessory assembly type mounting structure comprises a mounting bracket, a first supporting bracket and a second supporting bracket;
the mounting bracket is provided with a first pin, a second pin and a finger-shaped contact, the first pin and the second pin are connected with the mounting edge of the aero-engine through the first supporting bracket, and the finger-shaped contact is connected with the mounting edge of the aero-engine through the second supporting bracket;
the first support bracket is provided with a joint bearing used for being connected with the first pin or the second pin;
the second support bracket is also provided with a knuckle bearing for connection with the finger contact.
The mounting bracket is of a rectangular frame structure and is used for fixing the ignition accessory, and the first pin and the second pin are respectively located on two long edges of the mounting bracket.
The finger-shaped contact comprises a shell, the shell is provided with a hook-shaped sliding groove, an ejector pin is arranged in the shell, one end of the ejector pin penetrates through the shell to be connected with the mounting support and the second supporting support, the other end of the ejector pin is provided with a tail attachment, the ejector pin is provided with a spring and a sliding block, and the sliding block moves along the hook-shaped sliding groove to limit the ejector pin.
The arrangement directions of the first pin and the second pin are the same, and the arrangement direction of the finger-shaped contact is vertical to the arrangement direction of the second pin.
The first supporting bracket and the second supporting bracket are both provided with mounting holes for being fixedly connected with an engine mounting edge.
The mounting method of the ignition accessory of the aero-engine adopts the assembly type mounting structure of the ignition accessory of the aero-engine, and comprises the following steps:
installing an ignition accessory on an installation support, connecting one first support with one installation edge of the aircraft engine, and respectively connecting the other first support and the second support with the other installation edge of the aircraft engine;
respectively inserting a first pin and a second pin of the mounting bracket into the joint bearings of the first supporting bracket corresponding to the first pin and the second pin;
the mounting bracket is connected to the second support bracket by finger contacts.
The invention has the beneficial effects that:
1) the volume is small, the weight is light, the weight of the mounting bracket of the rectangular frame structure is lighter than that of other ignition accessory mounting seats for engines, and the requirements of lightening the weight of components of the engine are met;
2) the space is small, and the first pin, the second pin and the finger-shaped contact form a triangular three-point fixing mode, so that the fixing position is reduced compared with the four-point fixing mode of the ignition accessory for the existing engine, the space is saved, and the requirement of the limitation of the peripheral size of the aero-engine can be met;
3) the ignition accessory is firmly installed in two directions by adopting an insertion fixing mode, two first pins and two second pins which are transversely arranged and are used as finger-shaped contacts of a longitudinal positioner, operations such as installing a gasket, screwing a screw and the like are not needed, and the ignition accessory is simple and convenient to install;
4) stress is eliminated, the 3 supporting brackets arranged on the mounting edge of the aero-engine are all provided with the knuckle bearings which can rotate in any direction, and when the engine vibrates, the rotation of the knuckle bearings eliminates stress concentration caused by mounting and fixing;
5) the anti vibration nature is better, and the inside spring damping structure that adopts of longitudinal positioning's finger-shaped contact alleviates the influence that the engine horizontal vibration caused, and longitudinal vibration all can rotate in all directions when joint bearing supports between installing support and support frame, and the clearance is great between thimble and the joint bearing in the bayonet structure, compares in other engine fix with screw's rigid connection structure, can be better alleviate the influence that the vibration caused, avoids the zero subassembly damage that the vibration caused.
Additional features and advantages of the invention will be set forth in part in the detailed description which follows.
Drawings
FIG. 1 is a schematic structural view of a prior art integral ignition accessory mount;
FIG. 2 is a schematic view of a prior art ignition accessory mounted to a mounting base;
FIG. 3 is a schematic structural diagram of a mounting bracket provided in accordance with an embodiment of the present invention;
FIG. 4 is a view in the direction A of FIG. 3;
FIG. 5 is a schematic structural diagram of a first support bracket provided in accordance with an embodiment of the present invention;
fig. 6 is a schematic structural view of a second support bracket according to an embodiment of the present invention, wherein (a) is a front view, (b) is a left side view, and (c) is a top view;
FIG. 7 is a schematic front view of an ignition accessory provided in accordance with an embodiment of the present invention mounted on a mounting bracket;
figure 8 is a left side schematic view of an ignition accessory provided in accordance with an embodiment of the present invention mounted on a mounting bracket.
Reference numerals in the drawings of the specification include:
1-mounting seat, 2-mounting claw, 3-bolt, 4-ignition accessory, 5-mounting support, 6-first pin, 7-finger-shaped contact, 8-first supporting support, 9-knuckle bearing, 10-bushing, 11-thimble, 12-spring, 13-tail attachment, 14-shell, 15-mounting edge, 16-second pin and 17-second supporting support.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.
In the description of the present invention, it is to be understood that the terms "longitudinal", "lateral", "vertical", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, unless otherwise specified and limited, it is to be noted that the terms "mounted," "connected," and "connected" are to be interpreted broadly, and may be, for example, a mechanical connection or an electrical connection, a communication between two elements, a direct connection, or an indirect connection via an intermediate medium, and specific meanings of the terms may be understood by those skilled in the art according to specific situations.
In order to solve the problems in the prior art, as shown in fig. 3 to 8, an embodiment of the invention provides an aircraft engine ignition accessory assembly type mounting structure and a mounting method, which ensure that an ignition accessory 4 is reliably mounted and fixed, the working process is stable and is not damaged, and the aircraft engine is ensured to normally work.
As shown in fig. 3 and 4, the mounting structure for the ignition accessory 4 of the aircraft engine comprises a mounting bracket 5, a first supporting bracket 8 and a second supporting bracket 17, wherein the supporting brackets are used for supporting the mounting bracket 5, reducing vibration and eliminating stress; the mounting support 5 is provided with a first pin 6, a second pin 16 and a finger-shaped contact 7, the first pin 6, the second pin 16 and the finger-shaped contact 7 are welded on the mounting support 5, the first pin 6 and the second pin 16 are connected with an aeroengine mounting edge 15 through a first support 8, the finger-shaped contact 7 is connected with the aeroengine mounting edge 15 through a second support 17, the mounting support 5 is of a rectangular frame structure and is used for fixing the ignition accessory 4, the first pin 6 and the second pin 16 are respectively located on two long edges of the mounting support 5, the arrangement directions of the first pin 6 and the second pin 16 are the same, the arrangement direction of the finger-shaped contact 7 is perpendicular to the arrangement direction of the second pin 16, namely the direction of the second pin 16 is orthogonal to the direction of the finger-shaped contact 7.
As shown in fig. 5 and 6, the first support bracket 8 is provided with a knuckle bearing 9 for connecting with the first pin 6 or the second pin 16, the second support bracket 17 is also provided with a knuckle bearing 9 for connecting with the finger-shaped contact 7, and the first support bracket 8 and the second support bracket 17 are both provided with mounting holes for fixedly connecting with the engine mounting edge 15.
In this embodiment, the mounting bracket 5 of the rectangular frame structure is adopted, the length of the peripheral dimension is 220mm × 150mm, the length of the internal hollow structure is 140mm × 70mm, compared with the integral flat plate structure of the existing ignition accessory 4 mounting seat for the engine, the length of the mounting bracket is 284mm × 206mm, the weight is lighter, the requirements of lightening the components of the engine are met better, and the rectangular frame structure and the supporting bracket are matched to ensure that the weight is light and the ignition accessory 4 can be firmly mounted, namely the working stability of the engine is ensured. The ignition accessory 4 is fixed on a mounting bracket 5, the mounting bracket 5 is fixed on an aeroengine mounting edge 15 through 3 support brackets, a first pin 6, a second pin 16 and a finger contact 7 are installed in a knuckle bearing 9 of the corresponding support bracket and then the finger contact 7 is locked, so that the fixed mounting of the ignition accessory 4 is completed, wherein the first pin 6 is connected with one mounting edge 15 of the aeroengine through a first support bracket 8, the second pin 16 is connected with the other mounting edge 15 of the aeroengine through the first support bracket 8, and the finger contact 7 is connected with the other mounting edge 15 of the aeroengine through a second support bracket 17. As shown in fig. 5, the first support bracket 8 is a triangular structure, a joint bearing 9 is disposed on one vertex of the first support bracket 8, mounting holes are disposed on the other two vertices of the first support bracket 8, and are used for being fixedly connected with the engine mounting edge 15, the first support bracket 8 is further provided with mounting holes for being fixedly connected with the engine mounting edge 15, and the mounting holes and the joint bearing 9 are located on the same plane. As shown in fig. 6, the second support bracket 17 is also provided with a mounting hole for fixedly connecting with the engine mounting edge 15, and the plane of the mounting hole on the second support bracket 17 is perpendicular to the plane of the joint bearing 9. When the engine works, no matter the transverse vibration or the longitudinal vibration can be supported and decomposed through the movement of the joint bearing 9, the flexible connection between the ignition accessory 4 and the engine avoids the action of assembly stress, the 3-point bidirectional fixing mode effectively limits the moving range of the ignition accessory 4, the ignition accessory 4 is ensured to be rapidly installed in a limited space, and the ignition accessory 4 cannot generate large displacement and cannot interfere with surrounding components.
As shown in fig. 4 and 7, the finger-shaped contact 7 includes a housing 14, the housing 14 is provided with a hook-shaped sliding slot, a thimble 11 is disposed inside the housing 14, one end of the thimble 11 passes through the housing 14 to connect the mounting bracket 5 and the second supporting bracket 17, the other end of the thimble 11 is provided with a tail attachment 13 for pressing and screwing the thimble 11, the thimble 11 is provided with a spring 12 and a slider, and the slider moves along the hook-shaped sliding slot to limit the thimble 11. The finger contacts 7 are specifically configured as: the shell 14 is a cylindrical structure, one end of the shell 14 is provided with a through hole, the other end of the shell 14 is in threaded connection with a nut, a thimble 11 is arranged in the shell 14, one end of the thimble 11 penetrates through the through hole of the shell 14 to be connected with a bushing 10 of the mounting bracket 5 and a joint bearing 9 of a second supporting bracket 17, the other end of the thimble 11 is provided with a tail 13, the thimble 11 is externally sleeved with a spring 12, one end, close to the tail 13, of the spring 12 is fixedly connected with the thimble 11, the spring 12 is limited when the tail 13 screws the thimble 11 to compress the spring 12, a plurality of hook-shaped sliding grooves are arranged outside the shell 14, the thimble 11 is provided with a sliding block, and during the process that the tail 13 screws the thimble 11, the sliding block moves along the sliding grooves and fixes the position of the thimble 11, of course, the hook-shaped sliding grooves can be provided with a plurality of, through the cooperation of the finger-shaped contact 7 with the damping function and the second support bracket 17 with the knuckle bearing 9, the influence of external factors such as engine vibration and mounting stress on the ignition accessory 4 is effectively avoided, and the stable work of the ignition system is ensured.
As shown in fig. 7 and 8, a method for mounting an aircraft engine ignition accessory 4, which adopts the assembly type mounting structure of the aircraft engine ignition accessory 4, comprises the following steps:
the ignition accessory 4 is fixedly installed on an installation support 5 through a bolt 3 and a nut, one first support 8 is connected with one installation edge 15 of the aircraft engine, the other first support 8 and one second support 17 are respectively connected with the other installation edge 15 of the aircraft engine, and the two first support 8 and the one second support 17 are both fixedly connected with the corresponding aircraft engine installation edge 15;
inserting the first pin 6 and the second pin 16 of the mounting bracket 5 into the corresponding joint bearings 9 of the first support bracket 8 respectively;
the mounting bracket 5 and the second supporting bracket 17 are connected through the finger-shaped contact 7, namely, the mounting bracket 5 is placed at a position corresponding to the second supporting bracket 17, the thimble 11 of the finger-shaped contact 7 is pushed into the knuckle bearing 9 by force, the tail attachment 13 is rotated, the finger-shaped contact 7 is locked, and the fixed mounting of the ignition attachment 4 is completed.
In order to ensure that the ignition accessory 4 is stably installed on the circular shell of the engine and eliminate the damage of engine vibration, assembly stress and the like to the bracket of the ignition accessory 4, the installation of the ignition accessory 4 is realized through the assembly type installation structure of the invention at the installation position of the existing ignition accessory 4. The ignition accessory 4 is installed in a flexible connection mode through the knuckle bearing 9 of the first supporting bracket 8 and the second supporting bracket 17, the requirement of the external space of an engine can be met, the core components of the engine ignition system can work stably and reliably, the operation space reserved during installation of fasteners such as screws is eliminated, the stress influence caused by rigid connection, namely the influence of damage of the ignition accessory 4 and a mounting seat on the work of the aero-engine is avoided, the influence of factors such as vibration and the like is overcome in the working process of the engine, the ignition accessory 4 is reliably installed and fixed, the working process is stable and free of damage, and the normal work of the aero-engine is ensured.
While embodiments of the invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.
Claims (6)
1. An aircraft engine ignition accessory assembly type mounting structure is characterized by comprising a mounting bracket, a first supporting bracket and a second supporting bracket;
the mounting bracket is provided with a first pin, a second pin and a finger-shaped contact, the first pin and the second pin are connected with the mounting edge of the aero-engine through the first supporting bracket, and the finger-shaped contact is connected with the mounting edge of the aero-engine through the second supporting bracket;
the first support bracket is provided with a joint bearing used for being connected with the first pin or the second pin;
the second support bracket is also provided with a knuckle bearing for connection with the finger contact.
2. The aircraft engine ignition accessory mount structure of claim 1, wherein the mounting bracket is a rectangular frame structure for securing an ignition accessory, and the first pin and the second pin are located on two long sides of the mounting bracket, respectively.
3. The aircraft engine ignition accessory mounting structure of claim 1, wherein the finger contact comprises a housing, the housing is provided with a hook-shaped chute, a thimble is disposed inside the housing, one end of the thimble passes through the housing to connect the mounting bracket and the second support bracket, the other end of the thimble is provided with a tail attachment, the thimble is provided with a spring and a slider, and the slider moves along the hook-shaped chute to limit the thimble.
4. The aircraft engine ignition accessory mount assembly structure of claim 1, wherein the first pin and the second pin are disposed in the same direction, and the finger contact is disposed in a direction perpendicular to the direction of the second pin.
5. The aircraft engine ignition accessory mount-type mounting structure of claim 1 wherein the first support bracket and the second support bracket are each provided with a mounting hole for fixed connection with an engine mounting edge.
6. A method for mounting an ignition accessory of an aircraft engine, using the aircraft engine ignition accessory mounting structure of claim 1, comprising the steps of:
installing an ignition accessory on an installation support, connecting one first support with one installation edge of the aircraft engine, and respectively connecting the other first support and the second support with the other installation edge of the aircraft engine;
respectively inserting a first pin and a second pin of the mounting bracket into the joint bearings of the first supporting bracket corresponding to the first pin and the second pin;
the mounting bracket is connected to the second support bracket by finger contacts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911153216.0A CN110745250B (en) | 2019-11-22 | 2019-11-22 | Assembly type mounting structure and mounting method for ignition accessory of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911153216.0A CN110745250B (en) | 2019-11-22 | 2019-11-22 | Assembly type mounting structure and mounting method for ignition accessory of aero-engine |
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| Publication Number | Publication Date |
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| CN110745250A true CN110745250A (en) | 2020-02-04 |
| CN110745250B CN110745250B (en) | 2023-04-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911153216.0A Active CN110745250B (en) | 2019-11-22 | 2019-11-22 | Assembly type mounting structure and mounting method for ignition accessory of aero-engine |
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Citations (7)
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|---|---|---|---|---|
| US5860623A (en) * | 1995-05-03 | 1999-01-19 | The Boeing Company | Three link failsafe engine mount |
| RU2004102950A (en) * | 2004-02-04 | 2005-07-27 | Федеральное государственное унитарное предпри тие "Государственный космический научно-производственный центр им. М.В. Хруничева" (RU) | DEVICE FOR CONNECTING AND DISCONNECTING ELECTRICAL CONNECTIONS BETWEEN SEPARABLE SPACE COMPARTMENT COMPARTMENTS |
| US20110197595A1 (en) * | 2008-02-28 | 2011-08-18 | Airbus Operations(Inc As A Societe Par Act Simpl.) | Engine assembly for an aircraft comprising attachments for engines offset below on the fan frame |
| CN204144114U (en) * | 2014-11-10 | 2015-02-04 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of aero-engine microswitch |
| CN109372638A (en) * | 2018-12-16 | 2019-02-22 | 中国航发沈阳发动机研究所 | A kind of connection structure of aero-engine and accessory drive gearbox |
| US20190092484A1 (en) * | 2015-01-07 | 2019-03-28 | Lord Corporation | Aircraft engine mount |
| CN109625294A (en) * | 2018-12-16 | 2019-04-16 | 中国航发沈阳发动机研究所 | Hanging structure between aero-engine and external accessory casing |
-
2019
- 2019-11-22 CN CN201911153216.0A patent/CN110745250B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5860623A (en) * | 1995-05-03 | 1999-01-19 | The Boeing Company | Three link failsafe engine mount |
| RU2004102950A (en) * | 2004-02-04 | 2005-07-27 | Федеральное государственное унитарное предпри тие "Государственный космический научно-производственный центр им. М.В. Хруничева" (RU) | DEVICE FOR CONNECTING AND DISCONNECTING ELECTRICAL CONNECTIONS BETWEEN SEPARABLE SPACE COMPARTMENT COMPARTMENTS |
| US20110197595A1 (en) * | 2008-02-28 | 2011-08-18 | Airbus Operations(Inc As A Societe Par Act Simpl.) | Engine assembly for an aircraft comprising attachments for engines offset below on the fan frame |
| CN204144114U (en) * | 2014-11-10 | 2015-02-04 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of aero-engine microswitch |
| US20190092484A1 (en) * | 2015-01-07 | 2019-03-28 | Lord Corporation | Aircraft engine mount |
| CN109372638A (en) * | 2018-12-16 | 2019-02-22 | 中国航发沈阳发动机研究所 | A kind of connection structure of aero-engine and accessory drive gearbox |
| CN109625294A (en) * | 2018-12-16 | 2019-04-16 | 中国航发沈阳发动机研究所 | Hanging structure between aero-engine and external accessory casing |
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| CN110745250B (en) | 2023-04-18 |
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