CN115789112A - Connecting structure for mounting remote measuring device of aircraft engine - Google Patents
Connecting structure for mounting remote measuring device of aircraft engine Download PDFInfo
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- CN115789112A CN115789112A CN202310084938.5A CN202310084938A CN115789112A CN 115789112 A CN115789112 A CN 115789112A CN 202310084938 A CN202310084938 A CN 202310084938A CN 115789112 A CN115789112 A CN 115789112A
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- aircraft engine
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- telemetry device
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- 238000009434 installation Methods 0.000 claims abstract description 13
- 238000007789 sealing Methods 0.000 claims abstract description 10
- 238000012360 testing method Methods 0.000 claims abstract description 6
- 230000006835 compression Effects 0.000 claims description 15
- 238000007906 compression Methods 0.000 claims description 15
- 210000004907 gland Anatomy 0.000 claims description 2
- 230000013011 mating Effects 0.000 claims 1
- 238000012546 transfer Methods 0.000 abstract description 13
- 238000001816 cooling Methods 0.000 abstract description 4
- 238000009413 insulation Methods 0.000 abstract description 3
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000011161 development Methods 0.000 abstract description 2
- 210000003739 neck Anatomy 0.000 description 7
- 238000000034 method Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000004323 axial length Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000013024 troubleshooting Methods 0.000 description 1
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Abstract
The invention provides a connecting structure for mounting a telemetering device of an aircraft engine, which comprises: one end of the switching section is connected with a signal transmitter of the telemetering device; the periphery of the transfer shaft is integrally provided with a sealing structure, the other end of the transfer section is abutted against the sealing structure, the other end of the transfer section is connected with one end of the transfer shaft, and the other end of the transfer shaft is fixedly connected with a shaft neck of a rotating part of an engine. The invention has the following beneficial effects: the connection mode has good stability, the assembly and disassembly are simple and convenient, and the heat insulation and cooling requirements are met; the installation of various telemetering signal transmitters in different engine environments can be realized, and the universality is very strong; the existing engine is fully utilized, the refitting workload is reduced, the test refitting period is shortened, and the development cost of the engine is saved.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to a connecting structure for mounting a telemetering device of an aero-engine.
Background
The rotary part of the aircraft engine is in a severe working environment, and is required to bear high pressure, high temperature and high rotating speed, so that faults such as blade fracture and the like are easy to occur. Therefore, the method is particularly important for measuring parameters of a rotating part of an aircraft engine in the process of developing and troubleshooting a new machine. The method measures the key parameters of the rotating part in the real environment of the engine, and has important engineering value and practical significance for correcting a calculation model and improving the precision of a design result. At present, the important method for measuring the parameters of the rotating part of the aircraft engine is the measurement of a remote measuring technology, and the parameters of the dynamic stress, the temperature, the pressure and the like of the engine are measured by respectively connecting a remote measuring device with the rotating part and a stator part. According to the measuring principle of the telemetering device, a signal transmitter of the telemetering device needs to be connected with a rotating part, generally, the rotating part does not have a mounting interface of the signal transmitter, and a special connecting structure needs to be designed to meet the mounting requirement of the signal transmitter.
Disclosure of Invention
In view of this, the present invention provides a connection structure for mounting a telemetry device of an aircraft engine, so as to meet the mounting requirement of a signal transmitter of the telemetry device on the aircraft engine.
The embodiment of the specification provides the following technical scheme: a connection structure for an aircraft engine telemetry device installation, comprising: one end of the switching section is connected with a signal transmitter of the telemetering device; the periphery of the transfer shaft is integrally provided with a sealing structure, the other end of the transfer section is abutted to the sealing structure, the other end of the transfer section is connected with one end of the transfer shaft, and the other end of the transfer shaft is fixedly connected with the shaft neck of the rotary part of the engine.
Furthermore, the switching section comprises a first large-diameter section, a middle connecting section and a second large-diameter section which are connected in sequence, and the maximum diameter of the first large-diameter section and the maximum diameter of the second large-diameter section are both larger than the maximum diameter of the middle connecting section.
Further, the intermediate connecting section is provided with a plurality of radial through holes arranged at intervals along the circumferential direction.
Furthermore, the first large-diameter section is connected with a signal transmitter of the telemetering device, and a plurality of circumferential through holes arranged at intervals are arranged on the end face of the first large-diameter section.
Furthermore, a step surface is formed at the joint of the second large-diameter section and the middle connecting section, a gap is formed between the step surface and one end of the transfer shaft, and the end surface of the second large-diameter section is abutted to the sealing structure.
Furthermore, the other end of the switching section is fixedly connected with one end of the switching shaft through a compression nut.
Further, the connecting structure for mounting the remote measuring device of the aircraft engine further comprises a locking ring which is arranged at the compression nut and can lock the compression nut and the adapter shaft.
Further, the compression nut is provided with an axial through hole for penetrating the test lead.
Furthermore, the adapter shaft is connected with the shaft neck of the rotating part of the engine through a pin, and the adapter shaft is in interference fit with the matching cylindrical surface of the shaft neck of the rotating part of the engine.
Compared with the prior art, the beneficial effects that can be achieved by the at least one technical scheme adopted by the embodiment of the specification at least comprise: the connection mode has good stability, the disassembly and the assembly are simple and convenient, and the requirements of heat insulation and cooling are met; the installation of various telemetering signal transmitters in different engine environments can be realized, and the universality is very strong; the existing engine is fully utilized, the refitting workload is reduced, the test refitting period is shortened, and the development cost of the engine is saved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic structural diagram of an embodiment of the present invention;
FIG. 2 is a schematic structural view of a locking ring in an embodiment of the present invention;
fig. 3 is a schematic structural diagram of an adapter segment according to an embodiment of the present invention.
Reference numbers in the figures: 1. a telemetry device signal transmitter; 2. a switching section; 3. a compression nut; 4. a locking ring; 5. a sealing structure; 6. a transfer shaft; 7. a journal of an engine rotating member; 8. a pin.
Detailed Description
The embodiments of the present application will be described in detail below with reference to the accompanying drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1 to 3, the connection structure for mounting the telemetering device of the aircraft engine comprises an adapter section 2 and one end of the adapter section 2 of an adapter shaft 6, wherein the adapter section 2 is connected with a telemetering device signal transmitter 1; the periphery integration of switching axle 6 is provided with seal structure 5, and the other end and the seal structure 5 butt of switching section 2, and the other end of switching section 2 is connected with the one end of switching axle 6, and the other end and the engine rotary part axle journal 7 fixed connection of switching axle 6.
The embodiment of the invention can meet the requirement of installing the signal transmitter 1 of the telemetering device on the rotating part of the engine, has compact connecting structure, less parts and small newly added mass, can neglect the dynamic influence on the whole rotor and has better stability; the telemetering device signal transmitter 1 and the connecting structure for installing the telemetering device of the aircraft engine are both simple and convenient to disassemble and assemble.
Specifically, the switching section 2 includes a first large-diameter section, an intermediate connection section and a second large-diameter section which are connected in sequence, and the maximum diameter of the first large-diameter section and the maximum diameter of the second large-diameter section are both larger than the maximum diameter of the intermediate connection section. The middle connecting section is provided with a plurality of radial through holes arranged at intervals along the circumferential direction. The radial through holes in the switching section 2 effectively play a role in heat insulation and cooling, and the normal work of the signal transmitter 1 of the telemetering device is guaranteed.
The first large-diameter section is connected with the signal transmitter 1 of the telemetering device, and a plurality of circumferential through holes arranged at intervals are arranged on the end face of the first large-diameter section. The installation interface of the first large-diameter section and the telemetering device signal transmitter 1 is fixed by the traditional flange connection and the screws, so that the replacement of different telemetering device signal transmitters 1 can be realized under the condition of keeping the interfaces consistent, and the universality is very strong. Meanwhile, the flange edge (the end face of the first large-diameter section) is provided with a circumferential through hole for cooling and mounting, and the number of the holes is comprehensively determined according to requirements of an air system, a temperature field, strength and the like.
The junction of the second large-diameter section and the middle connecting section forms a step surface, a certain gap is formed between the step surface and one end of the adapter shaft 6, and the end surface of the second large-diameter section is abutted against the sealing structure 5. The other end of the adapter section 2 is fixedly connected with one end of the adapter shaft 6 through the compression nut 3.
Further, the connecting structure for mounting the remote measuring device of the aircraft engine further comprises a locking ring 4 which is arranged at the compression nut 3 and can lock the compression nut 3 with the adapter shaft 6.
The adapter section 2 and the sealing structure 5 are fixed on the adapter shaft 6 through the compression nut 3, and the compression nut 3 is locked with the adapter shaft 6 through the locking ring 4. Wherein the locking ring 4 is provided with lugs for circumferential locking of the compression nut 3.
Preferably, the gland nut 3 is provided with an axial through hole for the passage of the test lead. The test lead passes through the step hole of the adapter shaft 6 and the axial through hole of the compression nut 3 and is installed on the signal transmitter 1 of the telemetering device. And a step hole of the adapter shaft 6 is plugged after being led.
The adapter shaft 6 is connected with a shaft neck 7 of a rotating part of the engine by a pin 8, and the adapter shaft 6 is in interference fit with a matching cylindrical surface of the shaft neck 7 of the rotating part of the engine. The adapter shaft 6 is axially positioned by an axial spigot of a shaft neck 7 of a rotating part of the engine and the pin 8, the adapter shaft 6 is circumferentially positioned by the pin 8, and the pin 8 and the interference fit torque transmission are adopted.
The transfer shaft 6 adopts a connection mode of pin, spigot and cylindrical surface interference fit, is easy to realize the installation and connection with various shaft necks, and is convenient to disassemble and assemble; the installation of the signal transmitter 1 of the telemetering device in different engine environments can be realized by adjusting the axial lengths of the switching shaft 6 and the switching section 2, adjusting the vent holes on the switching section 2 and replacing different types of sealing structures; meanwhile, the design of the embodiment of the invention has recoverability, and the modified structure can recover the engine structure by plugging by adding the plugging cover.
The above description is only exemplary of the invention and should not be taken as limiting the scope of the invention, so that the invention is intended to cover all modifications and equivalents of the embodiments described herein. In addition, the technical features, the technical schemes and the technical schemes can be freely combined and used.
Claims (9)
1. A connection structure for installation of an aircraft engine telemetry device, comprising:
one end of the switching section (2) is connected with the signal transmitter (1) of the telemetering device;
the integrated seal structure (5) that is provided with of switching axle (6), periphery, the other end and the seal structure (5) butt of switching section (2), and the other end and the one end of switching axle (6) of switching section (2) are connected, the other end and the engine rotary part axle journal (7) fixed connection of switching axle (6).
2. The connection structure for the installation of telemetric devices for aircraft engines according to claim 1, characterized in that the adapter section (2) comprises a first large-diameter section, an intermediate connection section and a second large-diameter section connected in series, the maximum diameter of the first large-diameter section and the maximum diameter of the second large-diameter section being greater than the maximum diameter of the intermediate connection section.
3. A connection arrangement for the installation of an aircraft engine telemetry device according to claim 2, characterised in that the intermediate connection section is provided with a plurality of spaced radial through holes in the circumferential direction.
4. The connection structure for aircraft engine telemetry device mounting according to claim 2, characterized in that the first large diameter section is connected with a telemetry device signal transmitter (1), and an end face of the first large diameter section is provided with a plurality of circumferential through holes arranged at intervals.
5. The connection structure for aircraft engine telemetry device mounting as claimed in claim 2, wherein the junction of the second large diameter section and the intermediate connection section forms a step surface, the step surface has a gap with one end of the adapter shaft (6), and the end surface of the second large diameter section abuts against the sealing structure (5).
6. The connection structure for the installation of an aircraft engine telemetry device according to claim 1, characterized in that the other end of the adapter section (2) is fixedly connected with one end of the adapter shaft (6) by means of a compression nut (3).
7. The connection structure for the installation of an aircraft engine telemetry device according to claim 6, characterized in that it further comprises a locking ring (4) provided at the compression nut (3) and able to lock the compression nut (3) with the adapter shaft (6).
8. Connection structure for the installation of telemetric means of an aircraft engine according to claim 6, characterized in that the gland nut (3) is provided with an axial through hole for the passage of a test lead.
9. The connection structure for the installation of an aircraft engine telemetry device according to claim 1, characterized in that the adapter shaft (6) is connected with the journal (7) of the rotating part of the engine by means of a pin (8), and the adapter shaft (6) is in interference fit with the mating cylindrical surface of the journal (7) of the rotating part of the engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310084938.5A CN115789112A (en) | 2023-02-09 | 2023-02-09 | Connecting structure for mounting remote measuring device of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310084938.5A CN115789112A (en) | 2023-02-09 | 2023-02-09 | Connecting structure for mounting remote measuring device of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115789112A true CN115789112A (en) | 2023-03-14 |
Family
ID=85430592
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310084938.5A Pending CN115789112A (en) | 2023-02-09 | 2023-02-09 | Connecting structure for mounting remote measuring device of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115789112A (en) |
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|---|---|---|---|---|
| DE10025095A1 (en) * | 2000-05-20 | 2001-11-22 | Volkswagen Ag | Test bed for internal combustion engine of vehicle, has gear for connecting universal shaft of load machine and crank shaft, whose output side is aligned parallel to vehicle front axle |
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| JP2011257286A (en) * | 2010-06-10 | 2011-12-22 | Meidensha Corp | Shaft coupling auxiliary apparatus and shaft coupling method |
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| CN207715579U (en) * | 2017-12-14 | 2018-08-10 | 中国航发沈阳发动机研究所 | A kind of multi-function coupling |
| CN209638263U (en) * | 2019-03-05 | 2019-11-15 | 宁波思密德机电科技有限公司 | A kind of push-rod electric machine thin-wall flange |
| CN114033744A (en) * | 2022-01-11 | 2022-02-11 | 成都中科翼能科技有限公司 | Novel gas turbine low-pressure compressor rotor structure and assembling method |
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| CN216695583U (en) * | 2022-02-16 | 2022-06-07 | 中国航发商用航空发动机有限责任公司 | Multipurpose rotor signal measuring system of civil aircraft engine |
| CN114674564A (en) * | 2022-04-18 | 2022-06-28 | 南京航空航天大学 | Spliced movable plugboard total pressure distortion generator and test method |
| CN115163201A (en) * | 2021-04-06 | 2022-10-11 | 中国航发商用航空发动机有限责任公司 | Device and system for testing high-pressure turbine rotor of aircraft engine |
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2023
- 2023-02-09 CN CN202310084938.5A patent/CN115789112A/en active Pending
Patent Citations (14)
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|---|---|---|---|---|
| DE10025095A1 (en) * | 2000-05-20 | 2001-11-22 | Volkswagen Ag | Test bed for internal combustion engine of vehicle, has gear for connecting universal shaft of load machine and crank shaft, whose output side is aligned parallel to vehicle front axle |
| CN101657627A (en) * | 2007-04-17 | 2010-02-24 | 通用汽车环球科技运作公司 | Method and apparatus for determining intake air mass |
| JP2011257286A (en) * | 2010-06-10 | 2011-12-22 | Meidensha Corp | Shaft coupling auxiliary apparatus and shaft coupling method |
| US20140105727A1 (en) * | 2012-10-12 | 2014-04-17 | Snecma | Measurement installation for blade failure testing in a turbomachine |
| CN203051521U (en) * | 2012-12-27 | 2013-07-10 | 中国燃气涡轮研究院 | Reliable connecting structure of rotating disk shaft |
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| CN205278133U (en) * | 2015-12-14 | 2016-06-01 | 中国燃气涡轮研究院 | Rotary disk is experimental with preceding journal coupling structure |
| CN207715579U (en) * | 2017-12-14 | 2018-08-10 | 中国航发沈阳发动机研究所 | A kind of multi-function coupling |
| CN209638263U (en) * | 2019-03-05 | 2019-11-15 | 宁波思密德机电科技有限公司 | A kind of push-rod electric machine thin-wall flange |
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| CN114033744A (en) * | 2022-01-11 | 2022-02-11 | 成都中科翼能科技有限公司 | Novel gas turbine low-pressure compressor rotor structure and assembling method |
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Application publication date: 20230314 |
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