CN204043914U - For the flywheel gear of Aero-Engine Start test run - Google Patents
For the flywheel gear of Aero-Engine Start test run Download PDFInfo
- Publication number
- CN204043914U CN204043914U CN201420361636.4U CN201420361636U CN204043914U CN 204043914 U CN204043914 U CN 204043914U CN 201420361636 U CN201420361636 U CN 201420361636U CN 204043914 U CN204043914 U CN 204043914U
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- wheel hub
- flywheel gear
- aero
- test run
- engine start
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Abstract
The utility model discloses a kind of flywheel gear for Aero-Engine Start test run, flywheel gear is for substituting the screw propeller be loaded in aeromotor, flywheel gear comprises: for the wheel hub be connected with the output terminal of aeromotor, the outside of wheel hub is provided with circular wheel rim, the spoke that wheel hub extends through multiple radial direction along wheel hub connects wheel rim, and wheel hub is positioned at the center of wheel rim.It is compact that flywheel gear comprises wheel hub, wheel rim and spoke structure, each all shorter to development length in the plane of wheel rim, therefore can be arranged in the small space in environment storehouse, identical with the weight of screw propeller for the weight of the flywheel gear of Aero-Engine Start test run, and moment of inertia is identical with the moment of inertia of screw propeller, therefore screw propeller can be replaced to be installed on engine, in environment storehouse, to complete the test of engine band oar.The above-mentioned flywheel gear for Aero-Engine Start test run is simple and compact for structure, and propeller simulation engine band oar can be replaced preferably to test.
Description
Technical field
The utility model relates to Engine Block Test field, especially, relates to a kind of flywheel gear for Aero-Engine Start test run.
Background technology
Aeromotor does not allow No Load Start and test run, therefore aeromotor test run in not installation situation, is all to be generally with screw propeller or to connect dynamometer machine to carry out test run.Overall engine, when carrying out high/low temperature running-up test, need be placed in a high and low temperature environment storehouse by aeromotor, and for ensureing that environment temperature can realize fast lifting, the size design in environment storehouse often less, can not hold engine band screw propeller and test.Therefore the test carried out in environment storehouse of aeromotor, at a kind of device replacing screw propeller of engine power output shaft end design, need test with simulated engine band oar.
Utility model content
The utility model object is to provide a kind of flywheel gear for Aero-Engine Start test run, to solve the technical matters that engine band propeller test cannot carry out in environment storehouse.
For achieving the above object, the technical solution adopted in the utility model is as follows:
A kind of flywheel gear for Aero-Engine Start test run, flywheel gear is for substituting the screw propeller be loaded in aeromotor, flywheel gear comprises: for the wheel hub be connected with the output terminal of aeromotor, the outside of wheel hub is provided with circular wheel rim, the spoke that wheel hub extends through multiple radial direction along wheel hub connects wheel rim, and wheel hub is positioned at the center of wheel rim.
Preferably, the circumference of multiple spoke along flywheel gear between wheel rim and wheel hub is uniformly distributed.
Preferably, the quantity of spoke is 4.
Preferably, the width at spoke both ends increases gradually.
Preferably, wheel hub is circular ring structure, and the inner circle of wheel hub is bullport, and wheel hub is provided with pilot hole and mounting hole, and pilot hole is blind hole, and around bullport distribution, mounting hole is through hole, and wherein a part of mounting hole is arranged in pilot hole.
Preferably, mounting hole is uniformly distributed around bullport, is arranged at mounting hole in pilot hole and corresponding pilot hole is arranged with one heart.
Preferably, on same axis of symmetry, the length ratio of the length of wheel hub, the length of spoke and wheel rim is (0.9 ~ 1.1): (6.6 ~ 6.8): (0.5 ~ 0.7).
Preferably, the thickness of spoke is less than the thickness of wheel hub and wheel rim.
The utility model has following beneficial effect: it is compact that the flywheel gear for Aero-Engine Start test run comprises wheel hub, wheel rim and spoke structure, each all shorter to development length in the plane of wheel rim, therefore can be arranged in the small space in environment storehouse, identical with the weight of screw propeller for the weight of the flywheel gear of Aero-Engine Start test run, and moment of inertia is identical with the moment of inertia of screw propeller, therefore screw propeller can be replaced to be installed on engine, in environment storehouse, to complete the test of engine band oar.The above-mentioned flywheel gear for Aero-Engine Start test run is simple and compact for structure, and propeller simulation engine band oar can be replaced preferably to test.
Except object described above, feature and advantage, the utility model also has other object, feature and advantage.Below with reference to figure, the utility model is described in further detail.
Accompanying drawing explanation
The accompanying drawing forming a application's part is used to provide further understanding of the present utility model, and schematic description and description of the present utility model, for explaining the utility model, is not formed improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 is the structural representation of the flywheel gear for Aero-Engine Start test run of the utility model preferred embodiment;
Fig. 2 is the cross-sectional view of the flywheel gear for Aero-Engine Start test run of the utility model preferred embodiment.
Description of reference numerals: 100, wheel hub; 110, bullport; 120, pilot hole; 130, mounting hole; 200, spoke; 300, wheel rim.
Embodiment
Below in conjunction with accompanying drawing, embodiment of the present utility model is described in detail, but the multitude of different ways that the utility model can be defined by the claims and cover is implemented.
See figures.1.and.2, preferred embodiment of the present utility model provides a kind of flywheel gear for Aero-Engine Start test run, flywheel gear is for substituting the screw propeller be loaded in aeromotor, flywheel gear comprises: for the wheel hub 100 be connected with the output terminal of aeromotor, the outside of wheel hub 100 is provided with circular wheel rim 300, the spoke 200 that wheel hub 100 extends through multiple radial direction along wheel hub 100 connects wheel rim 300, and wheel hub 100 is positioned at the center of wheel rim 300.
Identical with the weight of screw propeller for the weight of the flywheel gear of Aero-Engine Start test run, and moment of inertia is identical with the moment of inertia of screw propeller.Wheel hub 100 is for being connected with the output terminal of engine, and it is positioned at the center of wheel rim 300, makes each shorter to size of the whole flywheel gear for Aero-Engine Start test run.Wheel rim 300 is circular ring structure, wheel hub 100 can be made stressed comparatively even, avoid local pressure excessive, cause serious wear, affect the serviceable life of wheel hub 100.Spoke 200 connects wheel hub 100 and wheel rim 300, can strengthen the serviceable life of wheel rim 300.The above-mentioned flywheel gear for Aero-Engine Start test run is simple and compact for structure, and propeller simulation engine band oar can be replaced preferably to test.
Preferably, with reference to Fig. 1, the circumference of multiple spokes 200 along flywheel gear between wheel rim 300 and wheel hub 100 is uniformly distributed.Spoke 200 is centrosymmetric, and this design can make wheel hub 100 uniform force, can strengthen the serviceable life of wheel rim 300.And the center of gravity of the whole flywheel gear for Aero-Engine Start test run is positioned at the center of wheel hub 100, the flywheel gear for Aero-Engine Start test run is less likely to occur deflection and tilts in rotation process.
Preferably, with reference to Fig. 1, the quantity of spoke 200 is 4.The quantity of spoke 200 is 4, and the angle between two adjacent two spokes 200 is 90 °.When general assembly (TW) is certain, arranges multiple spoke 200, can reduce the weight of wheel rim 300, the diameter of wheel rim 300 can correspondingly be reduced, the flywheel gear for Aero-Engine Start test run is more compact, can use in more narrow and small environment storehouse.The quantity of spoke 200 is also too much unsuitable, otherwise structure relative complex, manufacturing cost is higher, and therefore the quantity of spoke 200 can preferably be set to 4.
Preferably, with reference to Fig. 1, the width at spoke 200 both ends increases gradually.The two ends of spoke 200 are stressed comparatively large, therefore can increase the width at spoke 200 two ends, make spoke 200 be connected more tight with wheel hub 100 and wheel rim 300.Further, the flywheel gear for Aero-Engine Start test run is that overall processing is arranged, and as completed by cutting processing, the junction of spoke 200 and wheel hub 100 and the junction of spoke 200 and wheel rim 300 are arc transition.
Preferably, with reference to Fig. 1, wheel hub 100 is circular ring structure, the inner circle of wheel hub 100 is bullport 110, wheel hub 100 is provided with pilot hole 120 and mounting hole 130, and pilot hole 120 is blind hole, and distributes around bullport 110, mounting hole 130 is through hole, and wherein a part of mounting hole 130 is arranged in pilot hole 120.The bullport 110 of wheel hub 100 is for the output terminal of nested engine, and pilot hole 120 is for positioning action, and mounting hole 130 as bolt, makes the output terminal compact siro spinning technology of flywheel gear for Aero-Engine Start test run and engine by web member.Part mounting hole 130 is arranged in pilot hole 120, has saved space, has avoided arranging porous on wheel hub 100, caused the intensity of wheel hub 100 to decline.
Preferably, see figures.1.and.2, mounting hole 130 is uniformly distributed around bullport 110, is arranged at mounting hole 130 in pilot hole 120 and corresponding pilot hole 120 is arranged with one heart.This kind of setting can make mounting hole 130 be positioned at the center of pilot hole 120, is convenient to web member and stretches in mounting hole 130, easy for installation.
Preferably, on same axis of symmetry, the length ratio of the length of wheel hub 100, the length of spoke 200 and wheel rim 300 is (0.9 ~ 1.1): (6.6 ~ 6.8): (0.5 ~ 0.7).Under this design, can make the width of wheel hub 100 loop configuration, the length of spoke 200, the width of the loop configuration of wheel rim 300 keeps suitable ratio, makes wheel hub 100 and wheel rim 300 obtain higher intensity.
Preferably, with reference to Fig. 1, the thickness of spoke 200 is less than the thickness of wheel hub 100 and wheel rim 300.The thickness of suitable reduction spoke 200, can make the corresponding increase of the thickness of wheel hub 100 and wheel rim 300, enhance the intensity of wheel hub 100 and wheel rim 300.
The foregoing is only preferred embodiment of the present utility model, be not limited to the utility model, for a person skilled in the art, the utility model can have various modifications and variations.All within spirit of the present utility model and principle, any amendment done, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (8)
1. the flywheel gear for Aero-Engine Start test run, described flywheel gear is for substituting the screw propeller be loaded in described aeromotor, it is characterized in that, described flywheel gear comprises: for the wheel hub (100) be connected with the output terminal of described aeromotor, the outside of described wheel hub (100) is provided with circular wheel rim (300), the spoke (200) that described wheel hub (100) extends through multiple radial direction along described wheel hub (100) connects described wheel rim (300), described wheel hub (100) is positioned at the center of described wheel rim (300).
2. the flywheel gear for Aero-Engine Start test run according to claim 1, it is characterized in that, the circumference of multiple described spokes (200) along described flywheel gear between described wheel rim (300) and described wheel hub (100) is uniformly distributed.
3. the flywheel gear for Aero-Engine Start test run according to claim 2, is characterized in that, the quantity of described spoke (200) is 4.
4. the flywheel gear for Aero-Engine Start test run according to claim 3, is characterized in that, the width at described spoke (200) both ends increases gradually.
5. the flywheel gear for Aero-Engine Start test run according to claim 4, it is characterized in that, described wheel hub (100) is circular ring structure, the inner circle of described wheel hub (100) is bullport (110), described wheel hub (100) is provided with pilot hole (120) and mounting hole (130), described pilot hole (120) is blind hole, and distribute around described bullport (110), described mounting hole (130) is through hole, and wherein a part of described mounting hole (130) is arranged in described pilot hole (120).
6. the flywheel gear for Aero-Engine Start test run according to claim 5, it is characterized in that, described mounting hole (130) is uniformly distributed around described bullport (110), is arranged at described mounting hole (130) in described pilot hole (120) and corresponding described pilot hole (120) is arranged with one heart.
7. the flywheel gear for Aero-Engine Start test run according to claim 6, it is characterized in that, on same axis of symmetry, the length of the length of described wheel hub (100), described spoke (200) and the length ratio of described wheel rim (300) are (0.9 ~ 1.1): (6.6 ~ 6.8): (0.5 ~ 0.7).
8. the flywheel gear for Aero-Engine Start test run according to any one of claim 1 ~ 7, it is characterized in that, the thickness of described spoke (200) is less than the thickness of described wheel hub (100) and described wheel rim (300).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420361636.4U CN204043914U (en) | 2014-07-01 | 2014-07-01 | For the flywheel gear of Aero-Engine Start test run |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420361636.4U CN204043914U (en) | 2014-07-01 | 2014-07-01 | For the flywheel gear of Aero-Engine Start test run |
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| Publication Number | Publication Date |
|---|---|
| CN204043914U true CN204043914U (en) | 2014-12-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420361636.4U Active CN204043914U (en) | 2014-07-01 | 2014-07-01 | For the flywheel gear of Aero-Engine Start test run |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117288499A (en) * | 2023-11-24 | 2023-12-26 | 中国飞机强度研究所 | Lightweight flywheel for ultra-high acceleration test of aviation tire and manufacturing method thereof |
-
2014
- 2014-07-01 CN CN201420361636.4U patent/CN204043914U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117288499A (en) * | 2023-11-24 | 2023-12-26 | 中国飞机强度研究所 | Lightweight flywheel for ultra-high acceleration test of aviation tire and manufacturing method thereof |
| CN117288499B (en) * | 2023-11-24 | 2024-02-13 | 中国飞机强度研究所 | Lightweight flywheel for ultra-high acceleration test of aviation tire and manufacturing method thereof |
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| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |