CN208296979U - A kind of Aero Engine Testing noise testing sensor fixing structure - Google Patents
A kind of Aero Engine Testing noise testing sensor fixing structure Download PDFInfo
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- CN208296979U CN208296979U CN201820862833.2U CN201820862833U CN208296979U CN 208296979 U CN208296979 U CN 208296979U CN 201820862833 U CN201820862833 U CN 201820862833U CN 208296979 U CN208296979 U CN 208296979U
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- 238000012360 testing method Methods 0.000 title claims abstract description 57
- 238000007789 sealing Methods 0.000 claims description 10
- 230000003449 preventive effect Effects 0.000 claims description 5
- 239000011810 insulating material Substances 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 238000002474 experimental method Methods 0.000 abstract description 4
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- Testing Of Engines (AREA)
Abstract
The utility model relates to aero-engines to start acoustics experimental field, in particular to a kind of Aero Engine Testing noise testing sensor fixing structure.The mounting structure includes: mounting hole, for through the stepped hole of engine complete machine or component casing；Anti-dropout component axially inside offers first through hole, and bottom end is provided with noise control sound test sensor dropping structure, and with mounting hole by being threadedly engaged, top offers external screw thread for bottom；And anti-pop-up component, the second through-hole identical with first through hole internal diameter is axially inside offered, top is provided with noise control sound test sensor ejecting structure, is connected through a screw thread at the top of bottom and anti-dropout component；In the cavity that noise testing sensor is placed in first through hole and the second through-hole is formed.A kind of reliable noise transducer mounting structure is provided for the experiment of current aerospace engine noise.
Description
Technical Field
The utility model relates to an aeroengine starts acoustics experiment field, in particular to aeroengine is experimental with noise test sensor mounting structure.
Background
The noise level of the aircraft engine is used as an important index in the design, the examination and the shaping of the engine, the research on the noise test of the aircraft engine in China just starts, and the noise test mainly stays in the stage of 'only performing mechanism and principle test research but not accurately testing engineering problems' in a laboratory, and engineering experience for reference is lacked. If the noise test of the whole machine and the parts of the engineering aircraft engine needs to be carried out, the problem of installation of the noise sensor needs to be solved firstly, and only if the noise sensor is firmly installed at the correct position, accurate test and data acquisition can be carried out, so that the noise level of the whole machine and the parts of the engine can be evaluated.
At present, a noise test sensor mounting structure for an aircraft engine test, which can simultaneously ensure that a noise sensor is mounted at a correct position and the noise sensor is firmly mounted, is absent, so that the noise test sensor can measure effective noise test data and avoid falling into a flow channel to cause the running risk of the engine or be popped up due to the vibration of a casing to cause the damage of the engine.
Disclosure of Invention
The utility model aims at providing an aeroengine is noise test sensor mounting structure for experiment to alleviate or solve above-mentioned at least one problem.
The technical scheme of the utility model is that: an aeroengine is experimental with noise test sensor mounting structure, includes:
the mounting hole is a stepped hole penetrating through the whole engine or a part casing, and is internally provided with threads;
the anti-falling part is internally provided with a first through hole along the axial direction of the mounting hole, the bottom end of the anti-falling part is provided with an anti-noise test sensor falling structure, the bottom of the anti-falling part is in threaded fit with the mounting hole, and the top of the anti-falling part is provided with an external thread; and the number of the first and second groups,
the anti-ejection part is internally provided with a second through hole with the same inner diameter as the first through hole along the axial direction of the mounting hole, the top end of the anti-ejection part is provided with a noise-proof test sensor ejection structure, and the bottom of the anti-ejection part is connected with the top of the anti-drop part through threads;
wherein,
the noise test sensor is arranged in a cavity formed by the first through hole and the second through hole.
Preferably, the bottom end of the anti-drop part is flush with the inner surface of the whole engine or the part casing, and the anti-noise test sensor drop structure comprises a boss arranged at the bottom end of the anti-drop part.
Preferably, the noise-proof test sensor ejection structure comprises a boss disposed at the top end of the anti-ejection member.
Preferably, the mounting structure further comprises a gasket arranged between the central protrusion of the anti-drop part and the whole engine or the part casing.
Preferably, the mounting structure further comprises a sealing rubber ring which is arranged in a sealing groove formed in the top end of the anti-falling part.
Preferably, a first lock screw hole is formed in the middle of the anti-falling part, a second lock screw hole is formed in the outer portion of the anti-falling part, and the first lock screw hole is fastened with the second lock screw hole and the first lock screw hole of the noise test sensor mounting structure for the adjacent aircraft engine test through lock screws.
Preferably, the components of the mounting structure are made of an insulating material, and the insulating material has a temperature resistance level greater than that of the noise test environment.
The utility model has the advantages that: the noise test sensor mounting structure for the aircraft engine test can ensure that the noise sensor is mounted at a correct position and the noise sensor is firmly mounted, and can ensure that the noise test sensor can measure effective noise test data and avoid falling into a flow channel to cause the running risk of an engine or be popped up due to the vibration of a casing to cause the damage of the engine.
Drawings
Fig. 1 is the utility model discloses aeroengine is noise test sensor mounting structure for experiment along axial sectional view.
Fig. 2 is a schematic diagram of the noise test sensor of fig. 1.
Fig. 3 is a schematic structural view of the anti-ballistic component of fig. 1.
Fig. 4 is a schematic structural view of the falling off preventive member in fig. 1.
Fig. 5 is a schematic view of the mounting hole in fig. 1.
Detailed Description
In order to make the purpose, technical solution and advantages of the present invention clearer, the following will combine the drawings in the embodiments of the present invention to perform more detailed description on the technical solution in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present invention, and should not be construed as limiting the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the invention.
The following describes the mounting structure of the noise test sensor for aircraft engine test in further detail with reference to fig. 1 to 5.
The utility model provides an aeroengine is experimental with noise test sensor mounting structure, a serial communication port, include:
the mounting hole is a step hole penetrating through the whole engine or the part casing 6, and is internally provided with threads;
the anti-falling part 4 is internally provided with a first through hole along the axial direction of the mounting hole, the bottom end of the anti-falling part is provided with an anti-noise test sensor falling structure, the bottom of the anti-falling part is in threaded fit with the mounting hole, and the top of the anti-falling part is provided with an external thread;
the inside of the anti-ejection part 2 is provided with a second through hole with the same inner diameter as the first through hole along the axial direction of the mounting hole, the top end of the anti-ejection part is provided with a noise-proof test sensor ejection structure, and the bottom of the anti-ejection part is connected with the top of the anti-drop part 4 through threads;
the sealing gasket 5 is arranged between the middle part of the anti-falling part 4 and the whole engine or part casing 6 so as to ensure that no gas leaks from the part in the test process;
the sealing rubber ring 3 is arranged in a sealing groove formed in the top end of the anti-falling part 4 so as to ensure that no gas leaks from the sealing groove in the test process;
wherein,
the noise test sensor 1 is arranged in a cavity formed by the first through hole and the second through hole;
the bottom end of the anti-falling part 4 is arranged to be flush with the inner surface of the whole engine or the part casing 6 so as to reduce the influence on the internal airflow;
the anti-noise test sensor falling structure can be a boss arranged at the bottom end of the falling-off preventing part 4, the structure is simple and convenient to manufacture and fix, and the surface is smooth and easy to arrange to be flush with the inner surface of the whole engine or the part engine shell 6;
the anti-noise test sensor pop-up structure can be a boss arranged at the top end of the anti-ejection part 2, and the structure is simple and convenient to manufacture and fix;
the middle of the anti-falling part 4 is provided with a first lock screw hole, the exterior of the anti-falling part 2 is provided with a second lock screw hole, and the first lock screw hole is fastened with the second lock screw hole and the first lock screw hole of the noise test sensor mounting structure for the test of the adjacent aircraft engine through lock screws, so that the fastening of the mounting structure is guaranteed, and the occupied space of the mounting structure is small, and the operation space of the wrench is guaranteed.
The above description is only for the specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention should be covered by the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (7)
1. The utility model provides an aeroengine is experimental with noise test sensor mounting structure which characterized in that includes:
the mounting hole is a stepped hole penetrating through the whole engine or a part casing, and is internally provided with threads;
the anti-falling part (4) is internally provided with a first through hole along the axial direction of the mounting hole, the bottom end of the anti-falling part is provided with an anti-noise test sensor falling structure, the bottom of the anti-falling part is in threaded fit with the mounting hole, and the top of the anti-falling part is provided with an external thread; and the number of the first and second groups,
the anti-pop-up component (2) is internally provided with a second through hole with the same inner diameter as the first through hole along the axial direction of the mounting hole, the top end of the anti-pop-up component is provided with an anti-noise test sensor pop-up structure, and the bottom of the anti-pop-up component is connected with the top of the anti-drop component (4) through threads;
wherein,
the noise test sensor (1) is arranged in a cavity formed by the first through hole and the second through hole.
2. The mounting structure according to claim 1, wherein a bottom end of the drop-off preventive member (4) is flush with an inner surface of the engine complete machine or the component casing, and the noise test sensor drop-off preventive structure includes a boss provided at the bottom end of the drop-off preventive member (4).
3. The mounting structure according to claim 2, wherein the noise-proof test sensor ejection structure includes a boss provided at a tip end of the ejection-proof member (2).
4. The mounting structure according to claim 3, further comprising a gasket (5), wherein the drop-off preventive member (4) protrudes at a middle portion thereof, and the gasket (5) is provided between the protrusion and the engine complete body or the component case.
5. The mounting structure according to claim 4, further comprising a sealing rubber ring (3), wherein a sealing groove is formed at the top end of the anti-falling part (4), and the sealing rubber ring (3) is arranged in the sealing groove.
6. The mounting structure according to claim 5, wherein a first lock screw hole is formed in the middle of the anti-drop part (4), a second lock screw hole is formed in the outer part of the anti-drop part (2), and the first lock screw hole is fastened with the second lock screw hole and a first lock screw hole of the adjacent noise test sensor mounting structure for the aircraft engine test through lock screws.
7. The mounting structure according to claim 6, wherein the components of the mounting structure are made of an insulating material having a temperature resistance level greater than a temperature level of a noise test environment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820862833.2U CN208296979U (en) | 2018-06-05 | 2018-06-05 | A kind of Aero Engine Testing noise testing sensor fixing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820862833.2U CN208296979U (en) | 2018-06-05 | 2018-06-05 | A kind of Aero Engine Testing noise testing sensor fixing structure |
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| Publication Number | Publication Date |
|---|---|
| CN208296979U true CN208296979U (en) | 2018-12-28 |
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| CN201820862833.2U Active CN208296979U (en) | 2018-06-05 | 2018-06-05 | A kind of Aero Engine Testing noise testing sensor fixing structure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110695573A (en) * | 2019-10-12 | 2020-01-17 | 东风（武汉）汽车零部件有限公司 | Error proofing device for part welding |
| CN112857815A (en) * | 2019-11-28 | 2021-05-28 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for testing internal noise of aircraft engine compressor |
-
2018
- 2018-06-05 CN CN201820862833.2U patent/CN208296979U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110695573A (en) * | 2019-10-12 | 2020-01-17 | 东风（武汉）汽车零部件有限公司 | Error proofing device for part welding |
| CN112857815A (en) * | 2019-11-28 | 2021-05-28 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for testing internal noise of aircraft engine compressor |
| CN112857815B (en) * | 2019-11-28 | 2022-09-02 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for testing internal noise of aircraft engine compressor |
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