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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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 aero-engines to start acoustics experimental field, in particular to a kind of Aero Engine Testing is used
Noise testing sensor fixing structure.
Background technique
The noise level of aero-engine is as an important indicator in engine design, examination and sizing, China pair
The research of aero-engine noise experimental test is at the early-stage, and mainly also resting on laboratory " can only carry out mechanism and principle
Experimental study not can solve and precisely be tested engineering problem " stage, lacking can engineering experience for reference.If wanted
Carry out the aero-engine complete machine of engineering and the noise testing test of component, the installation for first having to solve noise transducer is asked
Topic, only noise transducer is fixedly secured to correct position, just can be carried out accurately test and data acquisition, and then assess
The noise level of engine complete machine and component.
Lacking one kind at present can guarantee that noise transducer is mounted on correct position and noise transducer installation jail simultaneously
Solid Aero Engine Testing noise testing sensor fixing structure, it is ensured that noise testing sensor is measuring effective noise
It avoids falling off while test data and causes the operation risk of engine inside air stream enter runner or pop up cause because of the vibration of casing
It is damaged to.
Summary of the invention
The purpose of the utility model is to provide a kind of Aero Engine Testing noise testing sensor fixing structure, with
Mitigate or solve the problems, such as it is above-mentioned at least one.
The technical solution of the utility model is: a kind of Aero Engine Testing noise testing sensor fixing structure, packet
It includes:
Mounting hole, for through the stepped hole of engine complete machine or component casing, inside offers screw thread；
Anti-dropout component, the internal axial direction along the mounting hole offer first through hole, and bottom end is provided with noise control sound test
Sensor dropping structure, with the mounting hole by being threadedly engaged, top offers external screw thread for bottom；And
Anti- pop-up component, inside axially offer the second through-hole identical with the first through hole internal diameter along mounting hole, push up
End is provided with noise control sound test sensor ejecting structure, is connected through a screw thread at the top of bottom and the anti-dropout component；
Wherein,
In the cavity that noise testing sensor is placed in the first through hole and second through-hole is formed.
Preferably, the bottom end of anti-dropout component is concordant with engine complete machine or component casing inner surface, and noise control sound test passes
Sensor dropping structure includes the boss that the anti-dropout component bottom ends are arranged in.
Preferably, noise control sound test sensor ejecting structure includes the boss that anti-pop-up component top is arranged in.
Preferably, which further includes gasket, setting anti-dropout central part it is prominent with engine complete machine or
Between component casing.
Preferably, which further includes sealing rubber ring, is arranged in the seal groove that anti-dropout component top opens up.
Preferably, anti-dropout central part offers the first lock wire hole, and anti-pop-up component outer offers the second lock wire hole,
First lock wire hole is installed by lock silk and the second lock wire hole and adjacent Aero Engine Testing noise testing sensor
First lock wire hole fastening of structure.
Preferably, the component of the mounting structure is manufactured using insulating materials, and the temperature resistant grade of the insulating materials is greater than
The temperature grade of noise testing environment.
Utility model has the advantages that providing a kind of Aero Engine Testing noise testing sensor installation knot
Structure can guarantee that noise transducer is mounted on correct position and noise transducer firmly installs, it is ensured that noise testing sensor
It avoids falling off while measuring effective noise test data and causes the operation risk of engine inside air stream enter runner or because of machine
The vibration of casket and pop up cause and be damaged to.
Detailed description of the invention
Fig. 1 is the utility model Aero Engine Testing noise testing sensor fixing structure along axial sectional view.
Fig. 2 is the schematic diagram of the noise testing sensor in Fig. 1.
Fig. 3 is the structural schematic diagram of the anti-pop-up component in Fig. 1.
Fig. 4 is the structural schematic diagram of the anti-dropout component in Fig. 1.
Fig. 5 is the schematic diagram of the mounting hole in Fig. 1.
Specific embodiment
To keep the purposes, technical schemes and advantages of the utility model implementation clearer, below in conjunction with the utility model
Attached drawing in embodiment, is further described in more detail the technical scheme in the embodiment of the utility model.In the accompanying drawings, from beginning
Same or similar element or element with the same or similar functions are indicated to same or similar label eventually.Described reality
Applying example is the utility model a part of the embodiment, instead of all the embodiments.Below with reference to the embodiment of attached drawing description
It is exemplary, it is intended to for explaining the utility model, and should not be understood as limiting the present invention.It is practical new based on this
Embodiment in type, every other implementation obtained by those of ordinary skill in the art without making creative efforts
Example, fall within the protection scope of the utility model.The embodiments of the present invention are described in detail with reference to the accompanying drawing.
In the description of the present invention, it should be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of describing the present invention and simplifying the description, rather than indication or suggestion is signified
Device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as to this is practical
The limitation of novel protected range.
1- Fig. 5 makes the utility model Aero Engine Testing of noise testing sensor fixing structure with reference to the accompanying drawing
It is further described.
The utility model provides a kind of Aero Engine Testing noise testing sensor fixing structure, and feature exists
In, comprising:
Mounting hole, for through the stepped hole of engine complete machine or component casing 6, inside offers screw thread；
Anti-dropout component 4, the internal axial direction along the mounting hole offer first through hole, and bottom end is provided with noise control sound test
Sensor dropping structure, with the mounting hole by being threadedly engaged, top offers external screw thread for bottom；
Anti- pop-up component 2, inside axially offer the second through-hole identical with the first through hole internal diameter along mounting hole, push up
End is provided with noise control sound test sensor ejecting structure, and bottom and the top of the anti-dropout component 4 are connected through a screw thread；
Gasket 5 is arranged in the middle part of the anti-dropout component 4 between prominent and engine complete machine or component casing 6, to protect
There is no gas to leak from this during confirmatory test；
Sealing rubber ring 3 is arranged in the seal groove that 4 top of anti-dropout component opens up, not have gas during guarantee test
Body is leaked from this；
Wherein,
In the cavity that noise testing sensor 1 is placed in the first through hole and second through-hole is formed；
The bottom end that anti-dropout component 4 is arranged is concordant with engine complete machine or 6 inner surface of component casing, to reduce to internal gas
The influence of stream；
Noise control sound test sensor dropping structure can be the boss that 4 bottom end of anti-dropout component is arranged in, this structure is simple
Convenient for manufacturing and fixing, and the smooth easy setting in surface is concordant with engine complete machine or component machine 6 inner surfaces of first；
Noise control sound test sensor ejecting structure can be the boss that anti-pop-up 2 top of component is arranged in, this structure
It is simple convenient for manufacture and fixed；
The first lock wire hole is offered in the middle part of anti-dropout component 4, offers the second lock wire hole outside anti-pop-up component 2, it should
First lock wire hole is installed with noise testing sensor and is tied by lock silk and the second lock wire hole and adjacent Aero Engine Testing
First lock wire hole fastening of structure, guarantees the fastening of mounting structure with this and occupied space guarantees the operating space of spanner less.
Above description is only a specific implementation of the present invention, but the protection scope of the utility model is not limited to
In this, anyone skilled in the art within the technical scope disclosed by the utility model, the change that can be readily occurred in
Change or replace, should be covered within the scope of the utility model.Therefore, the protection scope of the utility model should be with described
Subject to scope of protection of the claims.
Claims (7)
1. a kind of Aero Engine Testing noise testing sensor fixing structure characterized by comprising
Mounting hole, for through the stepped hole of engine complete machine or component casing, inside offers screw thread；
Anti-dropout component (4), the internal axial direction along the mounting hole offer first through hole, and bottom end is provided with noise control sound test biography
Sensor dropping structure, with the mounting hole by being threadedly engaged, top offers external screw thread for bottom；And
Anti- pop-up component (2), inside axially offer the second through-hole identical with the first through hole internal diameter along the mounting hole,
Top is provided with noise control sound test sensor ejecting structure, is connected through a screw thread at the top of bottom and the anti-dropout component (4)；
Wherein,
In the cavity that noise testing sensor (1) is placed in the first through hole and second through-hole is formed.
2. mounting structure according to claim 1, which is characterized in that the bottom end of the anti-dropout component (4) and the hair
Motivation complete machine or component casing inner surface are concordant, and the noise control sound test sensor dropping structure includes being arranged in the anti-dropout
The boss of component (4) bottom end.
3. mounting structure according to claim 2, which is characterized in that the noise control sound test sensor ejecting structure includes
Boss on described anti-pop-up component (2) top is set.
4. mounting structure according to claim 3, which is characterized in that further include gasket (5), the anti-dropout component
(4) middle part is prominent, and the gasket (5) is arranged between the protrusion and engine complete machine or component casing.
5. mounting structure according to claim 4, which is characterized in that further include sealing rubber ring (3), the anti-dropout component
(4) top offers seal groove, and the sealing rubber ring (3) is arranged in the seal groove.
6. mounting structure according to claim 5, which is characterized in that offer first in the middle part of the anti-dropout component (4)
Wire hole is locked, the second lock wire hole is offered outside the anti-pop-up component (2), the first lock wire hole passes through lock silk and described second
Lock the first lock wire hole fastening of wire hole and adjacent Aero Engine Testing noise testing sensor fixing structure.
7. mounting structure according to claim 6, which is characterized in that the component of the mounting structure uses insulating materials system
It makes, and the temperature resistant grade of the insulating materials is greater than the temperature grade of noise testing 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 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208296979U true CN208296979U (en) | 2018-12-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820862833.2U Active CN208296979U (en) | 2018-06-05 | 2018-06-05 | A kind of Aero Engine Testing noise testing sensor fixing structure |
Country Status (1)
| Country | Link |
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| CN (1) | CN208296979U (en) |
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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