CN216524808U - Combined type aero-engine test probe mounting structure - Google Patents
Combined type aero-engine test probe mounting structure Download PDFInfo
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- CN216524808U CN216524808U CN202122832016.7U CN202122832016U CN216524808U CN 216524808 U CN216524808 U CN 216524808U CN 202122832016 U CN202122832016 U CN 202122832016U CN 216524808 U CN216524808 U CN 216524808U
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- probe mounting
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Abstract
The utility model provides a combined type aircraft engine test probe mounting structure which comprises a stepping motor, a probe supporting rod, a fixed seat and a mounting seat, wherein the probe supporting rod is in butt joint with a push rod of the stepping motor, the stepping motor is arranged on the fixed seat, the fixed seat is connected with the mounting seat through a long bolt, the mounting seat is fixed on an engine casing through a short bolt, and a locking mechanism is arranged in the mounting seat and used for locking the probe supporting rod. By adopting the utility model, the corresponding probe supporting rod is selected for different measurement parameters in the test, so that the parameters of the engine at different radial positions can be conveniently measured; in addition, the test probe can select different probe supporting rods and sensing parts according to different tests, the measuring points at different positions can be controlled and measured, the components can be replaced mutually, a large amount of resource waste caused by the waste of the test probe is effectively avoided, the test is conveniently carried out, and the test cost is greatly saved.
Description
Technical Field
The utility model relates to the technical field of aeroengine pneumatic parameter probes; in particular to a combined type aero-engine test probe mounting structure.
Background
In the test of the whole aircraft engine and parts, the total temperature, the total pressure, the direction and other pneumatic parameters of the air flow of the internal flow passage of the engine are often required to be measured, and the method is used for researching the performance and the service life of the whole aircraft engine and parts. In order to measure aerodynamic parameters such as the temperature and the pressure of the air flow of the aircraft engine, a total temperature and a total pressure probe of the aircraft engine are generally adopted for measurement. The conventional total temperature and total pressure probe is made into an integrated structure by designing a structure and adopting modes such as welding and the like, and is used for measuring pneumatic parameters of a fixed position of an engine.
The traditional aircraft engine test probe adopts a mode that a supporting rod is welded with a mounting seat to form an integral probe, different test probes are required to be designed according to different aircraft engine models, different sections, different measuring point positions and different types of measurement parameters, and each test probe can only be used in the same position of an engine of the same model to carry out corresponding test parameter measurement. Because the probes are integrally immobilized and cannot be replaced, the whole probe is scrapped after the test is finished, and a large amount of test probes are wasted to cause a large amount of resources.
SUMMERY OF THE UTILITY MODEL
In order to solve the technical problem, the utility model provides a combined type aircraft engine test probe mounting structure.
The utility model is realized by the following technical scheme.
The utility model provides a combined type aircraft engine test probe mounting structure which comprises a stepping motor, a probe supporting rod, a fixed seat and a mounting seat, wherein the probe supporting rod is in butt joint with a push rod of the stepping motor, the stepping motor is arranged on the fixed seat, the fixed seat is connected with the mounting seat through a long bolt, the mounting seat is fixed on an engine casing through a short bolt, and a locking mechanism is arranged in the mounting seat and used for locking the probe supporting rod.
The locking mechanism comprises a cylindrical joint, a compression nut and a self-tightening chuck, one end of the cylindrical joint is fixed on the mounting seat, the compression nut is screwed at the other end of the cylindrical joint, the self-tightening chuck is arranged in the cylindrical joint, the head of the self-tightening chuck extends out of the cylindrical joint, and the compression nut is provided with a tapered hole corresponding to the head.
A step surface is arranged in the cylindrical joint, and the inner diameter of the step surface is smaller than the outer diameter of the self-tightening chuck.
And a gasket is arranged between the step surface and the self-tightening chuck.
The head of the self-tightening chuck is matched with the conical hole in shape.
The head of the self-tightening chuck is of a four-petal structure.
The cylindrical joint is also internally provided with a sleeve, an inner hole of the sleeve is matched with the probe supporting rod, the sleeve penetrates through the engine case, one end of the sleeve, which is positioned in the cylindrical joint, is screwed with a locking ring, and the other end of the sleeve is provided with an outward flanging.
And a sealing base plate is also arranged on the inner side of the outward flanging.
The switching mechanism comprises a push rod connecting block and a lead shell, the push rod connecting block is detachably connected with the lead shell, the push rod connecting block is fixedly connected with a push rod of the stepping motor, and the middle of the end face of the lead shell is fixedly connected with the probe supporting rod.
The push rod connecting block is connected with the lead shell through threads.
The utility model has the beneficial effects that:
by adopting the utility model, the corresponding probe supporting rod is selected for different measurement parameters in the test, so that the parameters of different radial positions of the engine can be conveniently measured; in addition, the test probe can select different probe supporting rods and sensing parts aiming at different tests, can control and measure measuring points at different positions, can be replaced mutually, effectively avoids a large amount of resource waste caused by the waste of the test probe, is convenient for test development, and greatly saves test cost.
Drawings
Fig. 1 is a schematic structural view of the present invention.
Fig. 2 is a schematic structural view of the locking mechanism.
Fig. 3 is a schematic view of the structure of the self-tightening chuck.
Fig. 4 is a schematic structural diagram of the changeover mechanism.
In the figure: 1-an engine case; 2-a step motor; 3-a probe support bar; 4-a switching mechanism; 5-fixing the base; 6-mounting a base; 7-long bolt; 8-short bolts; 9-a locking mechanism; 10-a barrel joint; 11-a compression nut; 12-self-tightening chuck; 13-a tapered hole; 14-step surface; 15-a gasket; 16-a cannula; 17-a locking ring; 18-flanging; 19-sealing the backing plate; 20-a push rod connecting block; 21-lead shell.
Detailed Description
The technical solution of the present invention is further described below, but the scope of the claimed invention is not limited to the described.
As shown in FIGS. 1 to 4, the structure of the present invention is schematically illustrated:
the utility model provides a combined type aircraft engine test probe mounting structure which comprises a stepping motor 2, a probe supporting rod 3, a fixed seat 5 and a mounting seat 6, wherein the probe supporting rod 3 is in butt joint with a push rod of the stepping motor 2, the stepping motor 2 is arranged on the fixed seat 5, the fixed seat 5 is connected with the mounting seat 6 through a long bolt 7, the mounting seat 6 is fixed on an engine case 1 through a short bolt 8, a locking mechanism 9 is arranged in the mounting seat 6, and the locking mechanism 9 is used for locking the probe supporting rod 3.
The principle is as follows: the stepping motor 2 is fixed through the fixing seat 5, the stepping motor 2 is started, the length of the probe supporting rod 3 extending into the casing can be adjusted through a push rod of the stepping motor 2, then the probe supporting rod 3 is locked through the locking mechanism 9, and the measurement of the pneumatic parameters of the engine can be started. The probe supporting rod 3 is provided with a probe, the specific form of the probe can be selected according to the requirement, and the probe belongs to the common knowledge.
By adopting the utility model, the corresponding probe supporting rod 3 is selected for different measurement parameters in the test, so that the parameters of different radial positions of the engine can be conveniently measured; in addition, the test probe can select different probe supporting rods 3 and sensing parts aiming at different tests, can control and measure measuring points at different positions, can be replaced mutually, effectively avoids a large amount of resource waste caused by the waste of the test probe, is convenient for test development, and greatly saves test cost.
Referring to fig. 2 and 3:
the locking mechanism 9 comprises a cylindrical joint 10, a compression nut 11 and a self-tightening chuck 12, one end of the cylindrical joint 10 is fixed on the mounting base 6, the compression nut 11 is screwed on the other end of the cylindrical joint 10, the self-tightening chuck 12 is arranged in the cylindrical joint 10, the head of the self-tightening chuck 12 extends out of the cylindrical joint 10, and the compression nut 11 is provided with a taper hole 13 corresponding to the head. The cylindrical joint 10 is screwed in through the compression nut 11, the tapered hole 13 is tightly pressed with the head of the self-tightening chuck 12, and the self-tightening chuck 12 is gradually enabled to clamp the probe supporting rod 3, so that locking is realized; simple structure, convenient operation, and stability is good.
A step surface 14 is arranged in the cylindrical joint 10, and the inner diameter of the step surface 14 is smaller than the outer diameter of the self-tightening chuck 12. The self-tightening chuck 12 is convenient to limit, and the stability is improved.
A gasket 15 is arranged between the step surface 14 and the self-tightening chuck 12.
The head of the self-tightening chuck 12 is shaped to fit into the tapered bore 13.
The head of the self-tightening chuck 12 is of a four-petal structure.
The gap between the compression nut 11 and the self-tightening chuck 12 is small when the self-tightening chuck is locked, and the internal structure is prevented from being polluted.
The cylindrical joint 10 is also internally provided with a sleeve 16, the inner hole of the sleeve 16 is matched with the probe supporting rod 3, the sleeve 16 penetrates through the engine case 1, one end of the sleeve 16, which is positioned in the cylindrical joint 10, is screwed with a locking ring 17, and the other end of the sleeve 16 is provided with an outward flange 18. The sleeve 16 can be positioned through the locking ring 17 and the flanging 18, and the flanging 18 realizes plane sealing, so that the sealing property between the outer side of the sleeve 16 and the engine case 1 is improved; and the sleeve 16 has good guiding function to the probe supporting rod 3, so that the probe supporting rod 3 can be made into any section shape according to the requirement.
And a sealing cushion plate 19 is arranged on the inner side of the outward flange 18. The contact area is convenient to increase, and the sealing performance is improved.
Referring to fig. 4:
the switching mechanism 4 comprises a push rod connecting block 20 and a lead shell 21, the push rod connecting block 20 is detachably connected with the lead shell 21, the push rod connecting block 20 is fixedly connected with a push rod of the stepping motor 2, and the middle part of the end face of the lead shell 21 is fixedly connected with the probe supporting rod 3. With this arrangement, the lead case 21 of the probe is arranged along the probe shaft 3, and is laterally led out through the lead case 21, so that no mechanical interference occurs with the structure of the stepping motor 2 or the like.
The push rod connecting block 20 is connected with the lead shell 21 through threads.
Claims (10)
1. The utility model provides a modular aeroengine test probe mounting structure which characterized in that: including step motor (2), probe branch (3), fixing base (5), mount pad (6), probe branch (3) and the push rod butt joint of step motor (2), on fixing base (5) were located in step motor (2), fixing base (5) are connected through stay bolt (7) with mount pad (6), mount pad (6) are fixed on engine machine casket (1) through short bolt (8), are equipped with locking mechanism (9) in mount pad (6), and locking mechanism (9) are used for locking probe branch (3).
2. The modular aircraft engine test probe mounting structure of claim 1, wherein: locking mechanism (9) are including cylindric joint (10), gland nut (11), from tight chuck (12), and on cylindric joint (10) one end was fixed in mount pad (6), gland nut (11) spiro union was connected in cylindric joint (10) other end, and in cylindric joint (10) was located in from tight chuck (12), the head of self tight chuck (12) stretched out cylindric joint (10), and gland nut (11) are equipped with bell mouth (13) corresponding this head.
3. The modular aircraft engine test probe mounting structure of claim 2, wherein: a step surface (14) is arranged in the cylindrical joint (10), and the inner diameter of the step surface (14) is smaller than the outer diameter of the self-tightening chuck (12).
4. The modular aircraft engine test probe mounting structure of claim 3, wherein: and a gasket (15) is arranged between the step surface (14) and the self-tightening chuck (12).
5. The modular aircraft engine test probe mounting structure of claim 2, wherein: the head shape of the self-tightening chuck (12) is adapted to the tapered hole (13).
6. The modular aircraft engine test probe mounting structure of claim 5, wherein: the head of the self-tightening chuck (12) is of a four-petal structure.
7. The modular aircraft engine test probe mounting structure of claim 2, wherein: still be equipped with sleeve pipe (16) in barrel joint (10), sleeve pipe (16) hole and probe branch (3) cooperation, sleeve pipe (16) run through engine machine casket (1), and sleeve pipe (16) are located one end spiro union in barrel joint (10) and have locking ring (17), and the sleeve pipe (16) other end is equipped with flanging (18).
8. The modular aircraft engine test probe mounting structure of claim 7, wherein: and a sealing cushion plate (19) is also arranged on the inner side of the outward flanging (18).
9. The modular aircraft engine test probe mounting structure of claim 1, wherein: still include changeover mechanism (4), changeover mechanism (4) include push rod connecting block (20), lead wire shell (21), and push rod connecting block (20) and lead wire shell (21) are detachable connection, and push rod connecting block (20) pass through fixed connection with step motor (2)'s push rod, the terminal surface middle part and probe branch (3) fixed connection of lead wire shell (21).
10. The modular aircraft engine test probe mounting structure of claim 9, wherein: the push rod connecting block (20) is connected with the lead shell (21) through threads.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122832016.7U CN216524808U (en) | 2021-11-18 | 2021-11-18 | Combined type aero-engine test probe mounting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122832016.7U CN216524808U (en) | 2021-11-18 | 2021-11-18 | Combined type aero-engine test probe mounting structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216524808U true CN216524808U (en) | 2022-05-13 |
Family
ID=81530733
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122832016.7U Active CN216524808U (en) | 2021-11-18 | 2021-11-18 | Combined type aero-engine test probe mounting structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216524808U (en) |
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2021
- 2021-11-18 CN CN202122832016.7U patent/CN216524808U/en active Active
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