CN210852946U - Small turbine engine mounting structure - Google Patents
Small turbine engine mounting structure Download PDFInfo
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- CN210852946U CN210852946U CN201920939796.5U CN201920939796U CN210852946U CN 210852946 U CN210852946 U CN 210852946U CN 201920939796 U CN201920939796 U CN 201920939796U CN 210852946 U CN210852946 U CN 210852946U
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- turbine engine
- support
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- pull rod
- mounting structure
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Abstract
The utility model relates to a mounting structure of engine, especially a small-size turbine engine mounting structure belongs to aircraft structural design field. The utility model provides a small-size turbine engine mounting structure, includes support and pull rod, the support is three, and two of them supports are fixed on aircraft 27 frames, and are connected with small-size turbine engine, and the third support passes through the pull rod and is connected with aircraft 28 frames. The utility model has the advantages of as follows: 1. can quick assembly disassembly and adjustment, shortened engine dismouting time, it is little to have solved installation space, dismouting difficulty scheduling problem. 2. The installation structure has simple form, light weight and good maintainability.
Description
Technical Field
The utility model relates to a mounting structure of engine, especially a small-size turbine engine mounting structure belongs to aircraft structural design field.
Background
The engine mounting mode mainly comprises four mounting modes, namely an engine frame mounting mode, a support mounting mode, a nacelle mounting mode and a hanging beam mounting mode. Wherein, the engine installed inside the fuselage usually adopts a support type installation form, and is realized through a front support and a rear support, as shown in fig. 1, a left shaft neck 2 and a right shaft neck 3 of a front installation surface of the engine are fixed on the airplane through a left quick-release mounting joint 1 and a right quick-release mounting joint 4, and are used as a main stress structure and compensate the thermal expansion of the engine. The rear mounting surface of the engine is fixed on an airplane bearing structure through a side pull rod fixing support 9, a side pull rod 10 and a side engine fixing point 11 to serve as an auxiliary hanging point, and a tie rod fixing support 7 and a tie rod 6 are connected with an airplane body 8 and an upper engine fixing point 5 in a free state to balance the transverse moment generated when the engine deflects left and right. The structure is complex, and the problems of poor disassembly operability, long disassembly and assembly time and the like due to space limitation exist.
SUMMERY OF THE UTILITY MODEL
The utility model aims at solving the problem that exists among the prior art, provide one kind and have quick assembly disassembly and adjustment, and the simple small-size turbine engine mounting structure of mounting structure form.
In order to achieve the above purpose, the utility model adopts the following technical scheme: the utility model provides a small-size turbine engine mounting structure, includes support and pull rod, the support is three, and two of them supports are fixed on aircraft 27 frames, and are connected with small-size turbine engine, and the third support passes through the pull rod and is connected with aircraft 28 frames.
Preferably, the small turbine engine is arranged on the right side of the aircraft 27-28 in the following direction through a support and pull rod mounting mode
Preferably, the pull rod is an adjusting pull rod and can be adjusted and installed.
Preferably, the support and the pull rod are connected through a quick-release pin, so that the support can be quickly detached.
The utility model fixes a small turbine engine on the right side of the aircraft 27-28 frame along the course reliably through the installation form of the pull rod and the three supports; in the process of disassembling the small-sized turbine engine, the quick-disassembling pin and the bolt are only required to be taken down, and the small-sized turbine engine can move downwards at the moment, so that the engine is quickly disassembled and assembled, and the engine is assembled, otherwise, especially when the distance between the 27 frames and the 28 frames of the airplane has manufacturing tolerance, the length of the pull rod is adjusted to achieve the compensation effect.
Compared with the prior art, the utility model has the advantages of as follows:
1. can quick assembly disassembly and adjustment, shortened engine dismouting time, it is little to have solved installation space, dismouting difficulty scheduling problem.
2. The installation structure has simple form, light weight and good maintainability.
Drawings
FIG. 1 is a schematic diagram of the structure of the prior art;
FIG. 2 is a schematic structural diagram of an embodiment of the present invention;
FIG. 3 is a view A-A of FIG. 2;
in fig. 1, a left quick-release mounting section; 2. A left journal; 3. A right journal; 4. A right quick-release mounting section; 5. An upper engine mount point; 6. A tie rod; 7. A tie rod fixing support; 8. An engine body; 9. A side pull rod fixing support; 10. A side pull rod; 11. a side engine mount point;
in fig. 2-3, 1, an aircraft 28 frame; 2. A support; 3. adjusting the pull rod; 4. a quick release pin; 5. an aircraft 27 frame; 6. A bolt; 7. a small turbine engine; 8. a support; 9. and (4) a support.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings 2-3: as shown in fig. 2-3, a small turbine engine mounting structure mainly comprises an airplane 28 frame 1, a support 2, a pull rod 3, a quick release pin 4, an airplane 27 frame 5, a bolt 6, a small turbine engine 7, a support 8 and a support 9. The support 9 is connected with the frame 5 of the airplane 27 through a connecting piece, the support 9 is fixed with the connecting piece through a bolt 6, the support 8 is connected with the frame 1 of the airplane 28 through an adjusting pull rod 3, and the support 8 is connected and fixed with the adjusting pull rod 3 through a quick-release pin 4.
As shown in fig. 2 and 3, a small turbine engine 7 is reliably fixed on the right side of the aircraft 27-28 in the following direction by adjusting the installation form of the pull rod 3, the support 2, the support 8 and the support 9; during the disassembly process of the small turbine engine, the quick-release pin 4 and the bolt 6 are only required to be removed, and the small turbine engine 7 can move downwards, so that the engine can be quickly disassembled and assembled, and vice versa during the assembly process of the engine, particularly when the distance between the frames 27 and 28 of the airplane has manufacturing tolerance, the length of the pull rod 3 is adjusted to achieve the compensation effect.
Through designing above-mentioned mounting structure form, the small-size turbine engine in-service use that the tandem double seat training machine of domestic assembled shows, above-mentioned small-size turbine engine mounting structure form can solve that the small-size turbine engine installation space that the tandem double seat training machine of domestic assembled is little, the difficult scheduling problem of dismouting, and the small-size turbine engine that has realized that the tandem double seat training machine of certain assembled has quick assembly disassembly and adjustment, and mounting structure form is simple, light in weight, the maintainability is good. The small turbine engine assembled with a certain type of tandem twin-seat trainer in China is ensured to exert the functions and the performance of the small turbine engine in the airplane, and the requirement of starting the engine in the full-envelope range is met.
Claims (4)
1. A small-sized turbine engine mounting structure characterized in that: including support and pull rod, the support is three, and wherein on two support fixed aircraft frames I, and be connected with small-size turbine engine, the third support passes through the pull rod and is connected with aircraft frame II.
2. The small turbine engine mounting structure according to claim 1, wherein: the small turbine engine is arranged on the right side of the aircraft frame I-aircraft frame II along the course direction through a support and pull rod mounting mode.
3. The small turbine engine mounting structure according to claim 1, wherein: the pull rod is an adjusting pull rod and can be adjusted and installed.
4. The small turbine engine mounting structure according to claim 1, wherein: the support is connected with the pull rod through a quick-release pin, so that the support can be quickly detached.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920939796.5U CN210852946U (en) | 2019-06-21 | 2019-06-21 | Small turbine engine mounting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920939796.5U CN210852946U (en) | 2019-06-21 | 2019-06-21 | Small turbine engine mounting structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210852946U true CN210852946U (en) | 2020-06-26 |
Family
ID=71299819
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920939796.5U Active CN210852946U (en) | 2019-06-21 | 2019-06-21 | Small turbine engine mounting structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210852946U (en) |
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2019
- 2019-06-21 CN CN201920939796.5U patent/CN210852946U/en active Active
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Legal Events
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP02 | Change in the address of a patent holder | ||
| CP02 | Change in the address of a patent holder |
Address after: Nanchang high tech Industrial Development Zone, Jiangxi Province Patentee after: JIANGXI HONGDU AVIATION INDUSTRY GROUP Co.,Ltd. Address before: 330000 Jiangxi city in Nanchang Province, the new bridge box 460 box 5001 Patentee before: JIANGXI HONGDU AVIATION INDUSTRY GROUP Co.,Ltd. |