CN114542640A - Damping vibration attenuation device and aircraft engine - Google Patents
Damping vibration attenuation device and aircraft engine Download PDFInfo
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- CN114542640A CN114542640A CN202011328800.8A CN202011328800A CN114542640A CN 114542640 A CN114542640 A CN 114542640A CN 202011328800 A CN202011328800 A CN 202011328800A CN 114542640 A CN114542640 A CN 114542640A
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- damping
- tube
- pipe
- attenuation device
- vibration attenuation
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- 238000013016 damping Methods 0.000 title claims abstract description 148
- 230000002787 reinforcement Effects 0.000 claims description 7
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 230000009467 reduction Effects 0.000 abstract description 5
- 230000004044 response Effects 0.000 abstract description 4
- 238000003780 insertion Methods 0.000 description 6
- 230000037431 insertion Effects 0.000 description 6
- 238000001816 cooling Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 239000003638 chemical reducing agent Substances 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- 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
- F16F7/00—Vibration-dampers; Shock-absorbers
- F16F7/08—Vibration-dampers; Shock-absorbers with friction surfaces rectilinearly movable along each other
- F16F7/082—Vibration-dampers; Shock-absorbers with friction surfaces rectilinearly movable along each other and characterised by damping force adjustment means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Vibration Dampers (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention discloses a damping vibration attenuation device and an aero-engine, relates to the field of aero-engines, and is used for optimizing the performance of the damping vibration attenuation device. The damping vibration attenuation device comprises a vortex reduction pipe and a damping pipe. The vortex reducing pipe is provided with a concave cavity. The damping tube is arranged in the concave cavity; the first end of the damping tube is detachably connected with the top of the concave cavity, the connection length of the damping tube is adjustable, the second end of the damping tube abuts against the bottom of the concave cavity, and the middle of the damping tube is in contact with the inner wall of the concave cavity in a deformable mode and in a deformed state. According to the damping vibration attenuation device provided by the technical scheme, different damping characteristics can be realized by adjusting the depth of the damping pipe inserted into the vortex reducing pipe, so that the vibration response of the vortex reducing pipe is inhibited.
Description
Technical Field
The invention relates to the field of aircraft engines, in particular to a damping vibration attenuation device and an aircraft engine.
Background
In order to enhance the cooling of high-temperature components, the pressure loss of cooling airflow is often reduced by adding a vortex reducer in the structure of a modern aero-engine, so that the cooling effect of the high-temperature components is improved, and unnecessary performance loss of the gas compressor is avoided.
The inventor finds that at least the following problems exist in the prior art: the vortex reducer structure is a cantilever-supported multi-pipe structure and is easy to be excited by cooling airflow in a disc cavity to generate forced response.
Disclosure of Invention
The invention provides a damping vibration attenuation device and an aircraft engine, which are used for optimizing the damping vibration attenuation device.
The embodiment of the invention provides a damping vibration attenuation device, which comprises:
a vortex reducing pipe having a cavity; and
a damping tube mounted in the cavity; the first end of the damping tube is detachably connected with the top of the concave cavity, the second end of the damping tube abuts against the bottom of the concave cavity, and the middle of the damping tube is in contact with the inner wall of the concave cavity in a deformable mode.
In some embodiments, the outer wall surface and/or the inner wall surface of the damping tube is provided with a groove; and/or the damping pipe is provided with a through hole penetrating through the wall body of the damping pipe.
In some embodiments, the grooves are distributed along the circumference of the damping tube in a plurality; and/or a plurality of through holes are distributed along the circumferential direction of the damping pipe.
In some embodiments, the depth of the groove varies along the axial direction of the damper tube.
In some embodiments, at least one of the ends of the groove is provided with a reinforcement portion along an axial direction of the damper tube to increase a thickness of the damper tube at the reinforcement portion.
In some embodiments, the cavity bottom of the vortex reducing pipe is provided with an annular surface protruding inwards, and the second end of the damping pipe abuts against the annular surface.
In some embodiments, the first end of the damper tube is provided with an external thread, the top of the cavity is provided with an internal thread, and the external thread and the internal thread form a threaded fit.
In some embodiments, the engagement length of the internal thread and the external thread is adjustable.
In some embodiments, when the damper tube is in an undeformed state, a gap is provided between an outer wall of the damper tube at the middle portion and an inner wall of the vortex reduction tube.
The embodiment of the invention also provides an aircraft engine which comprises the damping vibration attenuation device provided by any technical scheme of the invention.
According to the damping vibration attenuation device provided by the technical scheme, the first end of the damping pipe is detachably connected with the top of the cavity, the connection length is adjustable, different damping characteristics can be realized by adjusting the depth of the damping pipe inserted into the vortex reducing pipe, and therefore the vibration response of the vortex reducing pipe is restrained. When the damping pipe is inserted into the vortex reducing pipe, the damping pipe does not deform in the original state; when the insertion depth of the damping tube is enough, the damping tube begins to deform; then, the longer the depth of insertion of the damper tube, the larger the amount of deformation of the damper tube, and the larger the contact area between the damper tube and the vortex reducing tube. The damping characteristics of the entire damping vibration attenuation device are changed by the insertion depth of the damping tube. When vibration takes place, because subtract vortex pipe and damping tube laminating and have relative displacement between the two to produce frictional force, consume the vibration energy, thereby reach the damping effect, restrain harmful vibration.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention. In the drawings:
FIG. 1 is a schematic structural diagram of a damping vibration-damping device provided in an embodiment of the present invention;
FIG. 2 is a schematic view of a vortex reducing pipe structure of the damping vibration damping device according to the embodiment of the present invention;
FIG. 3 is a schematic view of a damper tube structure of the damping vibration attenuation apparatus according to the embodiment of the present invention;
fig. 4 is a schematic view of a damper tube structure of a damping vibration attenuation device according to another embodiment of the present invention.
Detailed Description
The technical solution provided by the present invention is explained in more detail with reference to fig. 1 to 4.
Referring to fig. 1, an embodiment of the present invention provides a damping vibration attenuation device, which includes a vortex reducing pipe 1 and a damping pipe 2. The vortex reducing tube 1 has a cavity 11. The damping tube 2 is mounted in the cavity 11; the first end 21 of the damping tube 2 is detachably connected with the top of the concave cavity 11 and the connection length is adjustable, the second end 22 of the damping tube 2 abuts against the bottom of the concave cavity 11, the middle part of the damping tube 2 is configured to be deformable, and the middle part of the damping tube 2 in a deformation state is in contact with the inner wall of the concave cavity 11. The larger the deformation of the middle portion of the damping tube 2, the larger the contact area of the middle portion of the damping tube 2 with the inner wall of the cavity 11.
The vortex reducing pipe 1 is a tubular structure applied to a compressor of a turbofan engine and used for reducing the loss of bleed air. The cavity 11 of the vortex reducing pipe 1 has various structural forms, and is suitable for installing the damping pipe 2. Referring to fig. 2, in some embodiments, the vortex reducing tube 1 is provided with a hole running axially through the hole, the middle part of the hole being provided with an annular surface 110 protruding towards the inner wall of the hole, the annular surface 110 being intended to be in abutting contact with the second end 22 of the damping tube 2. Of course, the hole may be provided at a middle portion thereof with projections projecting toward the inner wall of the hole, which are not annular, but two or three projections are arranged in a circumferential direction of the inner wall of the hole, unlike the annular surface. This construction can also be realized against the second end 22 of the damping tube 2.
According to the damping vibration attenuation device provided by the technical scheme, different damping characteristics can be realized by adjusting the depth of the damping pipe 2 inserted into the vortex reducing pipe 1, so that the vibration response of the vortex reducing pipe 1 is inhibited. When the damping pipe 2 is inserted into the vortex reducing pipe 1, the damping pipe 2 is not deformed in the original state; when the insertion depth of the damping tube 2 is enough, the damping tube 2 starts to deform; then, the longer the depth of insertion of the damper tube 2, the larger the amount of deformation of the damper tube 2, and the larger the contact area between the damper tube 2 and the vortex reduction tube 1. The damping characteristic of the damping structure is closely related to the actual size of the damping structure, such as the length and the thickness of the damping structure, and the contact pressure between the damping structure and the vortex reducing pipe 1. Contact pressure refers to the contact force generated after two or more structures are contacted. The damping vibration attenuation device provided by the technical scheme can adjust the insertion depth of the damping tube 2 according to needs, further adjust the deformation quantity of the damping tube 2 and further adjust the damping characteristic of the damping tube.
In order to facilitate the deformation of the damping tube 2, in some embodiments, the outer and/or inner wall surface of the damping tube 2 is provided with a groove 23. The groove 23 does not extend through the wall of the damping tube 2, but only thins a part of the wall of the damping tube 2. The groove 23 may be provided in plural, and the plural grooves 23 are distributed along the circumferential direction of the damper tube 2. The depth of the groove 23 may be uniform or variable for the same groove 23 along the axial direction of the damping tube 2.
In some embodiments, the damping tube 2 is provided with a through hole passing through its wall. The through holes and the grooves 23 may be arranged simultaneously, alternatively, discretely, next to each other. The arrangement is dependent on the damping parameters required.
Above-mentioned technical scheme is through setting up structural feature such as recess 23, through-hole in the axial direction of damping pipe 2, length direction promptly for damping pipe 2 length direction can be by compression deformation. Through designing different weak positions, the deformation of the damping structure under the action of external force can be adjusted, and then the contact area and the contact pressure of the rest of the vortex reducing pipes 1 are changed.
In some embodiments, the grooves 23 are arranged in a plurality dispersed along the circumference of the damper tube 2; and/or a plurality of through holes are distributed along the circumference of the damping tube 2. Fig. 3 and 4 illustrate two different arrangements of the grooves 23.
Referring to fig. 3 and 4, in some embodiments, at least one of the ends of the groove 23 is provided with a reinforcement portion 24 along the axial direction of the damper tube 2 to increase the thickness of the damper tube 2 at the reinforcement portion 24. The reinforcing parts 24 may be provided at both ends of the groove 23 in the length direction. The provision of the reinforcement 24 makes the thickness of a partial region of the damper tube 2 large, which makes the structure of the damper tube 2 more stable in other regions than the deformed region.
The connection between the first end 21 of the damping tube 2 and the tip of the vortex reducing tube 1 will be described. Referring to fig. 1-4, in some embodiments, the first end 21 of the damper tube 2 is provided with an external thread, and the top of the cavity 11 is provided with an internal thread, the external thread and the internal thread forming a threaded fit. When the vortex reducing pipe 1 is matched with the damping structure, the contact stress between the vortex reducing pipe 1 and the damping structure can obviously change the damping effect of the damping vibration attenuation device. Will subtract vortex pipe 1 and damping structural design for threaded connection, simultaneously, at the structural a plurality of weak positions of designing of damping, the packing force that provides through threaded connection for the damping structure takes place deformation, and then changes all the other area of contact and the pressure that subtract vortex pipe 1, and then adjusts this damping structure's damping characteristic. And the damping vibration attenuation device only needs to be installed once, the damping characteristic of the damping structure is adjusted in a thread rotating mode, the efficiency of damping design and research can be improved, a large number of damping structures do not need to be produced to match out the proper damping characteristic, and the cost is reduced.
In some embodiments, the twist length of the internal and external threads is adjustable. The damping characteristic of the damping vibration attenuation device is changed by adjusting the screwing length of the internal thread and the external thread.
In some embodiments, when the damper tube 2 is in an undeformed state, there is a gap between the outer wall of the middle portion of the damper tube 2 and the inner wall of the vortex reduction tube 1. The gap is, for example, 0.1mm to 0.5 mm. The top of the damping pipe 2 is contacted with the annular surface of the vortex reducing pipe 1, and an initial gap exists between the vortex reducing pipe 1 and the damping pipe 2. This initial clearance allows the damping tube 2 to be easily fitted inside the vortex reduction tube 1. Follow-up regulation subtracts the length of vortex pipe 1 and 2 screw thread closure sections of damping tube, because the second end of damping tube 2 supports the top on the toroidal surface, can no longer remove, if continue to increase the length of adding vortex pipe 1 and 2 screw thread closure sections of damping tube this moment, can make damping tube 2 take place deformation, then with the inner wall contact that subtracts vortex pipe 1 on. If the vortex reducing pipe 1 and the damping pipe 2 are subjected to vibration and then relatively displaced, the vibration energy is consumed due to the friction force formed by the contact of the vortex reducing pipe 1 and the damping pipe.
When the damping pipe 2 is in a deformation state, the outer wall of the middle part of the damping pipe 2 is attached to the inner wall of the vortex reducing pipe 1. The larger the deformation of the damping pipe 2 is, the tighter the outer wall of the middle part of the damping pipe 2 is attached to the inner wall of the vortex reducing pipe 1 is, and the larger the contact area is.
The material of the vortex reducing pipe 1 and the damping pipe 2 can be the same, and both are made of metal.
The embodiment of the invention also provides an aircraft engine which comprises the damping vibration attenuation device provided by any technical scheme of the invention.
In the description of the present invention, it is to be understood that the terms "central", "longitudinal", "lateral", "front", "rear", "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 referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be considered as limiting the scope of the present invention.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: it is to be understood that modifications may be made to the technical solutions described in the foregoing embodiments, or equivalents may be substituted for some of the technical features thereof, but such modifications or substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. A damped vibration damping device, comprising:
a vortex reducing pipe (1) having a cavity (11); and
a damping tube (2) mounted in said cavity (11); the first end (21) of the damping tube (2) is detachably connected with the top of the concave cavity (11) and the connection length is adjustable, the second end (22) of the damping tube (2) abuts against the bottom of the concave cavity (11), and the middle of the damping tube (2) is in contact with the inner wall of the concave cavity (11) in a deformable manner and in a deformation state.
2. Damping vibration attenuation device according to claim 1, characterized in that the outer wall surface and/or the inner wall surface of the damping tube (2) is provided with a groove (23); and/or the damping pipe (2) is provided with a through hole penetrating through the wall body of the damping pipe.
3. A damped vibration damping device according to claim 2, characterized in that the grooves (23) are arranged in a plurality distributed along the circumference of the damping tube (2); and/or a plurality of through holes are distributed along the circumferential direction of the damping pipe (2).
4. Damping vibration device according to claim 2, characterized in that the depth of the groove (23) varies along the axial direction of the damping tube (2).
5. Damping vibration attenuation device according to claim 2, characterized in that at least one of the ends of the groove (23) is provided with a reinforcement (24) along the axial direction of the damping tube (2) to increase the thickness of the damping tube (2) at the reinforcement (24).
6. Damping vibration attenuation device according to claim 1, characterized in that the bottom of the cavity (11) of the vortex reducing pipe (1) is provided with an annular surface (110) protruding inwards, and the second end (22) of the damping pipe (2) abuts against the annular surface (110).
7. Damping vibration attenuation device according to claim 1, characterized in that the first end (21) of the damping tube (2) is provided with an external thread and the top of the cavity (11) is provided with an internal thread, the external thread and the internal thread forming a threaded fit.
8. The damped vibration damping device according to claim 7, wherein a screwing length of said internal thread and said external thread is adjustable.
9. Damping vibration attenuation device according to claim 1, characterized in that when the damping tube (2) is in an undeformed state, there is a gap between the outer wall of the middle part of the damping tube (2) and the inner wall of the vortex reducing tube (1).
10. An aircraft engine, characterized in that it comprises a damping and vibration-damping device as claimed in any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011328800.8A CN114542640B (en) | 2020-11-24 | 2020-11-24 | Damping vibration attenuation device and aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011328800.8A CN114542640B (en) | 2020-11-24 | 2020-11-24 | Damping vibration attenuation device and aeroengine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114542640A true CN114542640A (en) | 2022-05-27 |
| CN114542640B CN114542640B (en) | 2024-04-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011328800.8A Active CN114542640B (en) | 2020-11-24 | 2020-11-24 | Damping vibration attenuation device and aeroengine |
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Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE648325C (en) * | 1936-01-08 | 1937-07-28 | E H Hans Holzwarth Dr Ing | Control element for deflagration chambers, in particular of internal combustion turbines, which can be adjusted by a tensioned pressure medium |
| FR2594487A1 (en) * | 1986-02-14 | 1987-08-21 | Kloeckner Humboldt Deutz Ag | GAS TURBINE WITH COOLING OF THE BEARING BY THE FUEL, USED ONCE ONLY, ESPECIALLY IN TELEGUIDE MISSILE |
| EP0886078A2 (en) * | 1997-06-19 | 1998-12-23 | Basf Aktiengesellschaft | Friction damper having a elastomer spring element |
| CA2387462A1 (en) * | 2001-05-31 | 2002-11-30 | Snecma Moteurs | Centripetal flow air bleed device |
| CN101238265A (en) * | 2005-05-24 | 2008-08-06 | 杰弗里·约翰·汤普森 | Energy-absorbing and force-limiting friction coupling |
| GB2468528A (en) * | 2009-03-13 | 2010-09-15 | Rolls Royce Plc | Vibration damper for use with hollow turbine blades |
| CN102019939A (en) * | 2009-09-15 | 2011-04-20 | 福伊特专利公司 | Energy consumption device, in particular in the form of impact protection for a rail-led vehicle |
| CN203097955U (en) * | 2012-12-24 | 2013-07-31 | 中航商用航空发动机有限责任公司 | Air guiding assembly of gas turbine engine |
| CN103453063A (en) * | 2012-12-03 | 2013-12-18 | 上海理工大学 | Nested collision damper |
| CN104246143A (en) * | 2012-04-06 | 2014-12-24 | 斯奈克玛 | Power transmission system for a turbomachine |
| CN104534014A (en) * | 2014-11-11 | 2015-04-22 | 上海宇航***工程研究所 | Shear type damping tube having vibration damping performance and vibration damping adapter |
| CN204553354U (en) * | 2015-03-11 | 2015-08-12 | 中航商用航空发动机有限责任公司 | Subtract the gas compressor of scroll and aeroengine |
| CN105134629A (en) * | 2015-09-23 | 2015-12-09 | 广东美的制冷设备有限公司 | Fan and air purifier |
| CN106321524A (en) * | 2016-11-18 | 2017-01-11 | 湖南核三力技术工程有限公司 | Damping, muffling and air compensation device for orifice plate |
| CN107023394A (en) * | 2017-04-07 | 2017-08-08 | 中国航发沈阳发动机研究所 | Tubular type compressor rotor air entraining device with damping |
| CN107676115A (en) * | 2017-11-15 | 2018-02-09 | 辽宁工程技术大学 | A kind of screw thread shearing type energy-absorbing erosion control hydraulic vertical prop |
| CN207246308U (en) * | 2017-09-06 | 2018-04-17 | 石家庄市东昌机械制造有限公司 | A kind of shifting axle axial resistance detent mechanism |
| CN208900415U (en) * | 2018-10-17 | 2019-05-24 | 哈尔滨电气股份有限公司 | A kind of compressor disk with air extraction structure |
| CN111664207A (en) * | 2020-05-12 | 2020-09-15 | 北京强度环境研究所 | Variable damping friction pair of base type metal shock absorber |
-
2020
- 2020-11-24 CN CN202011328800.8A patent/CN114542640B/en active Active
Patent Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE648325C (en) * | 1936-01-08 | 1937-07-28 | E H Hans Holzwarth Dr Ing | Control element for deflagration chambers, in particular of internal combustion turbines, which can be adjusted by a tensioned pressure medium |
| FR2594487A1 (en) * | 1986-02-14 | 1987-08-21 | Kloeckner Humboldt Deutz Ag | GAS TURBINE WITH COOLING OF THE BEARING BY THE FUEL, USED ONCE ONLY, ESPECIALLY IN TELEGUIDE MISSILE |
| EP0886078A2 (en) * | 1997-06-19 | 1998-12-23 | Basf Aktiengesellschaft | Friction damper having a elastomer spring element |
| CA2387462A1 (en) * | 2001-05-31 | 2002-11-30 | Snecma Moteurs | Centripetal flow air bleed device |
| CN101238265A (en) * | 2005-05-24 | 2008-08-06 | 杰弗里·约翰·汤普森 | Energy-absorbing and force-limiting friction coupling |
| GB2468528A (en) * | 2009-03-13 | 2010-09-15 | Rolls Royce Plc | Vibration damper for use with hollow turbine blades |
| CN102019939A (en) * | 2009-09-15 | 2011-04-20 | 福伊特专利公司 | Energy consumption device, in particular in the form of impact protection for a rail-led vehicle |
| CN104246143A (en) * | 2012-04-06 | 2014-12-24 | 斯奈克玛 | Power transmission system for a turbomachine |
| CN103453063A (en) * | 2012-12-03 | 2013-12-18 | 上海理工大学 | Nested collision damper |
| CN203097955U (en) * | 2012-12-24 | 2013-07-31 | 中航商用航空发动机有限责任公司 | Air guiding assembly of gas turbine engine |
| CN104534014A (en) * | 2014-11-11 | 2015-04-22 | 上海宇航***工程研究所 | Shear type damping tube having vibration damping performance and vibration damping adapter |
| CN204553354U (en) * | 2015-03-11 | 2015-08-12 | 中航商用航空发动机有限责任公司 | Subtract the gas compressor of scroll and aeroengine |
| CN105134629A (en) * | 2015-09-23 | 2015-12-09 | 广东美的制冷设备有限公司 | Fan and air purifier |
| CN106321524A (en) * | 2016-11-18 | 2017-01-11 | 湖南核三力技术工程有限公司 | Damping, muffling and air compensation device for orifice plate |
| CN107023394A (en) * | 2017-04-07 | 2017-08-08 | 中国航发沈阳发动机研究所 | Tubular type compressor rotor air entraining device with damping |
| CN207246308U (en) * | 2017-09-06 | 2018-04-17 | 石家庄市东昌机械制造有限公司 | A kind of shifting axle axial resistance detent mechanism |
| CN107676115A (en) * | 2017-11-15 | 2018-02-09 | 辽宁工程技术大学 | A kind of screw thread shearing type energy-absorbing erosion control hydraulic vertical prop |
| CN208900415U (en) * | 2018-10-17 | 2019-05-24 | 哈尔滨电气股份有限公司 | A kind of compressor disk with air extraction structure |
| CN111664207A (en) * | 2020-05-12 | 2020-09-15 | 北京强度环境研究所 | Variable damping friction pair of base type metal shock absorber |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114542640B (en) | 2024-04-05 |
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