CN112345105B - Lead structure for testing temperature of rotor disc body of air compressor - Google Patents
Lead structure for testing temperature of rotor disc body of air compressor Download PDFInfo
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- CN112345105B CN112345105B CN202011106972.0A CN202011106972A CN112345105B CN 112345105 B CN112345105 B CN 112345105B CN 202011106972 A CN202011106972 A CN 202011106972A CN 112345105 B CN112345105 B CN 112345105B
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- Prior art keywords
- lead
- shaft
- outer shaft
- lead pin
- disc body
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K7/00—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements
- G01K7/02—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using thermoelectric elements, e.g. thermocouples
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
- G01K1/14—Supports; Fastening devices; Arrangements for mounting thermometers in particular locations
- G01K1/143—Supports; Fastening devices; Arrangements for mounting thermometers in particular locations for measuring surface temperatures
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Abstract
The invention provides a novel lead structure for testing the temperature of a rotor disc body of a gas compressor, which comprises an inner shaft (1), a supporting ring (2), an outer shaft (3), a lead pin (4), a disc body (5), a testing lead (6), a lead device (7) and a temperature sensor (8). The structure measures the transient temperature of the disc body in the test process under the condition of not changing the real working environment of the disc body and damaging the disc body.
Description
Technical Field
The invention belongs to the field of gas turbine engine compressor component rotor testing, and particularly relates to a lead structure for testing the temperature of a compressor rotor disc body.
Background
The compressor rotor disk body of the gas turbine engine, in particular the final stage rotor disk body, works in a high-temperature and high-stress environment. The accurate measurement of the disc body temperature has important significance for evaluating the disc body strength and the service life and checking the numerical calculation method of the temperature field.
For the final-stage rotor of the multistage compressor, if the traditional thermocouple measurement is adopted, the wiring operation difficulty of the lead wire entering the front-stage current collector of the compressor through the drum is very high. Therefore, the temperature of the crystal and the temperature indicating paint is commonly measured at home. However, the crystal and the temperature indicating paint can only record the highest temperature in the whole test process, and cannot measure the temperature of various working conditions. And for the temperature measurement of the crystal, small holes are required to be processed on the disc body, so that the fatigue life of the disc body can be influenced. For temperature measurement of the temperature indicating paint, the test result needs to be compared with the map manually, and the error is larger.
Disclosure of Invention
The purpose of the invention is that: aiming at the defects of the temperature measurement method, the invention provides a novel lead structure for testing the temperature of the rotor disk body of the gas compressor, which can measure the transient temperature of the disk body in the test process under the condition of not changing the real working environment of the disk body and damaging the disk body.
The technical scheme of the invention is as follows: the lead structure for testing the temperature of the rotor disc body of the compressor comprises an inner shaft 1, a supporting ring 2, an outer shaft 3, a lead pin 4, a disc body 5, a test lead 6, a lead electrical device 7 and a temperature sensor 8;
the inner shaft 1 is positioned in the outer shaft 3, one end of the inner shaft 1 is fixedly connected with the electric guide 7, and the other end is fixedly connected with the support ring 2; the supporting ring 2 is fixedly connected with the outer shaft 3; the outer wall of the supporting ring 2 is matched with the inner wall of the outer shaft 3 to limit the lead pin 4, and the lead pin 4 passes through an opening on the inner wall of the outer shaft 3;
the surface of the tray body 5 is provided with a temperature sensor 8, and the temperature sensor 8 is connected with one end of a test lead 6; the test leads 6 pass through the through holes in the lead pins 4 in sequence, are arranged along the surface of the support ring and the inner surface of the inner shaft, and are connected with the lead 7.
Further, the lead pin 4 is a nonmetallic material.
Further, the thermal conductivity of the lead pin 4 is 0.15 to 0.3W/(mK).
Further, the hardness of the lead pin 4 is 30 to 45 (rockwell hardness, E).
Further, the upper part of the lead pin 4 is of a cylindrical structure, and the lower part of the lead pin is of a square boss; the square boss is located between the outer wall of the support ring 2 and the inner wall of the outer shaft 3.
Further, in the lead structure test, the cylindrical end face of the lead pin 4 is in contact with the tray 5; gaps are respectively reserved between the bottom end face and the upper end face of the square boss of the lead pin 4 and the outer wall of the supporting ring 2 and the inner wall of the outer shaft 3.
Further, the inner shaft 1 is of a cylinder structure; a soft filler is arranged in the inner shaft 1 for fixing the test lead 6.
Further, the outer surface diameter of the outer shaft 3 corresponds to the outer surface diameter of the air duct in the engine.
The invention has the beneficial effects that:
the invention has the advantages of no change of the actual working environment of the disc body, no damage to the disc body, capability of arranging and measuring a plurality of working condition points at one time and simple wiring operation.
Drawings
FIG. 1 is a schematic view of a lead structure of the present invention;
FIG. 2 is a schematic view of a pin structure;
FIG. 3 is a schematic view of an outer shaft construction;
FIG. 4 is a schematic view of a support ring structure;
FIG. 5 is a schematic view of a pin assembly gap;
reference numerals illustrate: 1-inner shaft 2-supporting ring 3-outer shaft 4-lead pin 5-disk 6-test lead 7-lead 8-temperature sensor.
Detailed Description
The invention is further described in detail by the following embodiments:
as shown in fig. 1, the present embodiment provides a lead structure for testing the temperature of a rotor disk of a compressor, which includes an inner shaft 1, a support ring 2, an outer shaft 3, a lead pin 4, a disk 5, a test lead 6, a lead 7 and a temperature sensor 8.
The inner shaft 1 is positioned in the outer shaft 3, one end of the inner shaft 1 is fixedly connected with the electric guide 7, and the other end is fixedly connected with the support ring 2; the supporting ring 2 is fixedly connected with the outer shaft 3; the outer wall of the supporting ring 2 is matched with the inner wall of the outer shaft 3 to limit the lead pin 4, and the lead pin 4 passes through an opening on the inner wall of the outer shaft 3.
The surface of the tray body 5 is provided with a temperature sensor 8, and the temperature sensor 8 is connected with one end of a test lead 6; the test leads 6 sequentially pass through the through holes on the lead pins 4, are arranged along the surface of the support ring 2 and the inner surface of the inner shaft 1, are connected with the lead 7, and transmit test signals to the rack receiving device.
In this embodiment, the outer shaft 3 and the inner shaft 1 may be mounted at the front end of the compressor through bolt holes. The outer shaft 3 can be connected to the support ring 2 by means of radial pins, limiting the circumferential displacement of the support ring 2.
The round shaft end of the lead pin 4 (structure shown in figure 2) passes through the round hole of the outer shaft 3 (structure shown in figure 3) and contacts with the bottom surface of the disc body, and the round hole on the outer shaft 3 limits the axial movement of the lead pin 4; the supporting ring 2 (structure is shown in fig. 4) is provided with a corresponding square groove, and the square groove is matched with a square boss of the lead pin 4 to limit the rotation of the lead pin 4. Fig. 5 shows a schematic view of the assembly gap of the lead pin, as shown in fig. 5, the disc 5 limits the outward movement of the lead pin 4 under the action of centrifugal force, and gaps S1 and S2 are left between the lead pin 4 and the outer shaft 3 and the support ring 2, so as to compensate for the radial deformation mismatch of the outer shaft 3 and the disc 5.
The function of the pin 4 is to protect the test wire 6, since the outer shaft 3 and the disc 5 are at a distance in the radial direction, the test wire 6 may break under the effect of centrifugal force and air flow if the wire is directly led from the disc 5 to the outer shaft 3.
In the embodiment, the lead pin 4 can be made of polyimide material, and has the hardness of 30-45 (Rockwell hardness, E) and cannot damage the disc body; and the heat conductivity coefficient is 0.15-0.3W/(m.K), and the influence on the temperature of the disc body is very small.
The outer diameter of the outer shaft 3 can be consistent with an air conduit in the engine, so that the flow field near the disc body 5 is consistent with the real environment, and the temperature field of the disc body 5 is consistent with that in the engine. The air conduit is a pipeline for passing cooling air in the engine, and the air conduit and the compressor rotor form a channel for cooling air in the disc cavity.
In order to facilitate the lead, the diameter of the hole on the inner shaft 1 can be designed to be 2-3 times larger than that of the test lead 6, and the test lead 6 can be fixed through soft filler after passing through the inner shaft 1, so that the test lead 6 is prevented from shaking in the inner shaft 1 when the rotor rotates;
the assembly sequence of this structure is: the lead pin 4 passes through the round hole of the outer shaft 3, the support ring 2 is assembled, radial pins for connecting the outer shaft 3 and the support ring 2 are assembled, after the tray body 5 is assembled, the test lead 6 passes through the lead pin 4 and the lead hole of the support ring 2, the test lead 6 is fixed on the tray body 5 and connected with the thermocouple 8, and finally the test lead 6 passes through the inner shaft 1 to reach the lead 7 at the front end of the compressor. The structure is implemented in a compressor component test simulating the operating state of the engine.
Claims (8)
1. The lead structure for the temperature test of the rotor disc body of the compressor is characterized by comprising an inner shaft (1), a supporting ring (2), an outer shaft (3), a lead pin (4), a disc body (5), a test lead (6), a lead device (7) and a temperature sensor (8);
the inner shaft (1) is positioned in the outer shaft (3), one end of the inner shaft (1) is fixedly connected with the current guiding device (7), and the other end of the inner shaft is fixedly connected with the supporting ring (2); the supporting ring (2) is fixedly connected with the outer shaft (3); the outer wall of the supporting ring (2) is matched with the inner wall of the outer shaft (3) to limit the lead pin (4), and the lead pin (4) passes through an opening on the inner wall of the outer shaft (3);
the surface of the tray body (5) is provided with a temperature sensor (8), and the temperature sensor (8) is connected with one end of the test lead (6); the test lead (6) sequentially passes through the through holes on the lead pins (4), is arranged along the surface of the support ring and the inner surface of the inner shaft, and is connected with the lead electrical appliance (7);
the round shaft end of the lead pin penetrates through the round hole of the outer shaft and is contacted with the bottom surface of the disc body; the supporting ring is provided with a corresponding square groove which is matched with the square boss of the lead pin; the cylindrical end face of the lead pin (4) is contacted with the tray body (5); gaps S1 and S2 are reserved between the lead pins and the outer shaft and between the lead pins and the support ring; the outer diameter of the outer shaft (3) corresponds to the air duct in the engine.
2. A lead structure according to claim 1, characterized in that the lead pin (4) is of a non-metallic material.
3. The lead structure according to claim 1, wherein the thermal conductivity of the lead pin (4) is 0.15 to 0.3W/(m·k).
4. The lead structure according to claim 1, wherein the rockwell hardness E of the lead pin (4) is 30 to 45.
5. The lead structure according to claim 1, wherein the upper part of the lead pin (4) is a cylindrical structure and the lower part is a square boss; the square boss is located between the outer wall of the support ring (2) and the inner wall of the outer shaft (3).
6. The lead structure according to claim 5, wherein gaps are respectively formed between the bottom end face and the upper end face of the square boss of the lead pin (4) and the outer wall of the supporting ring (2) and the inner wall of the outer shaft (3).
7. A lead structure according to claim 1, characterized in that the inner shaft (1) is a cylindrical structure; the inner shaft (1) is internally provided with soft filler for fixing the test lead (6).
8. A lead structure according to claim 1, wherein the outer surface diameter of the outer shaft (3) corresponds to the outer surface diameter of the air duct in the engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011106972.0A CN112345105B (en) | 2020-10-16 | 2020-10-16 | Lead structure for testing temperature of rotor disc body of air compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011106972.0A CN112345105B (en) | 2020-10-16 | 2020-10-16 | Lead structure for testing temperature of rotor disc body of air compressor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112345105A CN112345105A (en) | 2021-02-09 |
| CN112345105B true CN112345105B (en) | 2023-06-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011106972.0A Active CN112345105B (en) | 2020-10-16 | 2020-10-16 | Lead structure for testing temperature of rotor disc body of air compressor |
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| CN (1) | CN112345105B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113984259A (en) * | 2021-09-18 | 2022-01-28 | 中国航发南方工业有限公司 | Lead device for measuring dynamic stress of compressor blade |
| CN114396969A (en) * | 2022-01-26 | 2022-04-26 | 中国航发沈阳发动机研究所 | Guide pipe structure for testing high-pressure rotor of engine |
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|---|---|---|---|---|
| JP2000125516A (en) * | 1999-11-11 | 2000-04-28 | Sony Corp | Inner rotor type brushless motor, and method of detecting temperature of the motor |
| CN205015110U (en) * | 2015-04-30 | 2016-02-03 | 中国航空动力机械研究所 | Installation device is measured to aeroengine's compressor blade dynamic stress |
| CN105588652A (en) * | 2015-12-15 | 2016-05-18 | 中国燃气涡轮研究院 | Air spraying-based turbine blade temperature measurement method |
| CN207894533U (en) * | 2018-03-02 | 2018-09-21 | 成都凯天电子股份有限公司 | The platinum resistance temperature sensor of triplex redundance measuring temperature is provided for engine mouth |
| CN208399038U (en) * | 2018-07-10 | 2019-01-18 | 中国航发沈阳发动机研究所 | A kind of aircraft engine rotor part temperature test structure |
| CN110926819A (en) * | 2019-12-05 | 2020-03-27 | 中国航发四川燃气涡轮研究院 | Rotor inner cavity flow characteristic test structure |
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2020
- 2020-10-16 CN CN202011106972.0A patent/CN112345105B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000125516A (en) * | 1999-11-11 | 2000-04-28 | Sony Corp | Inner rotor type brushless motor, and method of detecting temperature of the motor |
| CN205015110U (en) * | 2015-04-30 | 2016-02-03 | 中国航空动力机械研究所 | Installation device is measured to aeroengine's compressor blade dynamic stress |
| CN105588652A (en) * | 2015-12-15 | 2016-05-18 | 中国燃气涡轮研究院 | Air spraying-based turbine blade temperature measurement method |
| CN207894533U (en) * | 2018-03-02 | 2018-09-21 | 成都凯天电子股份有限公司 | The platinum resistance temperature sensor of triplex redundance measuring temperature is provided for engine mouth |
| CN208399038U (en) * | 2018-07-10 | 2019-01-18 | 中国航发沈阳发动机研究所 | A kind of aircraft engine rotor part temperature test structure |
| CN110926819A (en) * | 2019-12-05 | 2020-03-27 | 中国航发四川燃气涡轮研究院 | Rotor inner cavity flow characteristic test structure |
Non-Patent Citations (1)
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| 航空发动机研发过程中的固有测试性设计;王强等;《机械工程师》;20180610(第06期);第126-129页 * |
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| CN112345105A (en) | 2021-02-09 |
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