CN112345105A - Lead structure for temperature test of compressor rotor disc body - Google Patents

Lead structure for temperature test of compressor rotor disc body Download PDF

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Publication number
CN112345105A
CN112345105A CN202011106972.0A CN202011106972A CN112345105A CN 112345105 A CN112345105 A CN 112345105A CN 202011106972 A CN202011106972 A CN 202011106972A CN 112345105 A CN112345105 A CN 112345105A
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China
Prior art keywords
lead
support ring
shaft
test
outer shaft
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CN202011106972.0A
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Chinese (zh)
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CN112345105B (en
Inventor
凡星
钟明桥
王晓
费君
廖清志
文近安
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AECC Sichuan Gas Turbine Research Institute
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AECC Sichuan Gas Turbine Research Institute
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Publication of CN112345105A publication Critical patent/CN112345105A/en
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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
    • 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
    • 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 temperature test of a rotor disc body of an air compressor, which comprises an inner shaft (1), a support ring (2), an outer shaft (3), a lead pin (4), a disc body (5), a test lead (6), a power lead device (7) and a temperature sensor (8). The structure can measure the transient temperature of the tray body in the test process under the conditions of not changing the real working environment of the tray body and damaging the tray body.

Description

Lead structure for temperature test of compressor rotor disc body
Technical Field
The invention belongs to the field of testing of gas compressor part rotors of gas turbine engines, and particularly relates to a lead structure for testing the temperature of a rotor disc body of a gas compressor.
Background
A gas compressor rotor disc body of a gas turbine engine, in particular to a final-stage rotor disc body, works in a high-temperature and high-stress environment. The accurate measurement of the temperature of the disc body has important significance for evaluating the strength and the service life of the disc body and checking a numerical calculation method of a temperature field.
For a final-stage rotor of the multistage compressor, if the traditional thermocouple measurement is adopted, the wiring operation difficulty that a lead wire enters an electricity starter at the front section of the compressor through a drum barrel is very high. Therefore, the temperature measurement of crystal and temperature indicating paint is commonly adopted in China. However, the crystal and the temperature indicating paint can only record the highest temperature in the whole test process, and the temperature of various working conditions cannot be measured. And for crystal temperature measurement, small holes are required to be processed in the disc body during installation, and the fatigue life of the disc body is influenced. For temperature measurement of the temperature indicating paint, the test result needs manual comparison of the atlas, and the error is large.
Disclosure of Invention
The purpose of the invention is as follows: aiming at the defects of the temperature measuring method, the invention provides a novel lead structure for temperature test of a rotor disc body of the gas compressor, which is used for measuring the transient temperature of the disc body in the test process under the conditions that the real working environment of the disc body is not changed and the disc body is damaged.
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 support ring 2, an outer shaft 3, a lead pin 4, a disc body 5, a test lead 6, an electrical starter 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 initiator 7, and the other end of the inner shaft is fixedly connected with the support ring 2; the support ring 2 is fixedly connected with the outer shaft 3; the outer wall of the support ring 2 is matched with the inner wall of the outer shaft 3 to limit the lead pin 4, and the lead pin 4 penetrates through an opening on the inner wall of the outer shaft 3;
a temperature sensor 8 is arranged on the surface of the disc body 5, and the temperature sensor 8 is connected with one end of the test lead 6; the test lead 6 passes through the through hole on the lead pin 4 in sequence, is arranged along the surface of the support ring and the inner surface of the inner shaft, and is connected with the current leading device 7.
Further, the lead pin 4 is a non-metallic material.
Further, the lead pin 4 has a thermal conductivity of 0.15 to 0.3W/(mK).
Further, the lead pin 4 has a hardness of 30 to 45 (Rockwell hardness, E).
Furthermore, 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 positioned between the outer wall of the support ring 2 and the inner wall of the outer shaft 3.
Further, during the lead structure test, the cylindrical end surface of the lead pin 4 is in contact with the disc body 5; gaps exist between the bottom end surface and the upper end surface of the square boss of the lead pin 4 and the outer wall of the support ring 2 and the inner wall of the outer shaft 3 correspondingly.
Further, the inner shaft 1 is of a cylinder structure; the inner shaft 1 is provided with a soft filler for fixing the test lead 6.
Further, the outer shaft 3 has an outer surface diameter corresponding to the outer surface diameter of the air guide tube in the engine.
The invention has the beneficial effects that:
the invention has the advantages of not changing the actual working environment of the disc body, avoiding damage to the disc body, being capable of arranging and measuring a plurality of working condition points at one time and being simple in wiring operation.
Drawings
FIG. 1 is a schematic view of a lead structure according to the present invention;
FIG. 2 is a schematic view of a lead pin configuration;
FIG. 3 is a schematic view of an outer shaft;
FIG. 4 is a schematic view of a support ring structure;
FIG. 5 is a schematic view of a lead pin assembly gap;
description of reference numerals: 1-inner shaft 2-support ring 3-outer shaft 4-lead pin 5-disk 6-test lead 7-power-on device 8-temperature sensor.
Detailed Description
The present invention will be described in further detail below by way of specific embodiments:
as shown in fig. 1, in the present embodiment, a lead structure for temperature testing of a compressor rotor disc body is provided, and the lead structure includes an inner shaft 1, a support ring 2, an outer shaft 3, a lead pin 4, a disc body 5, a test lead 6, an electrical 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 initiator 7, and the other end of the inner shaft is fixedly connected with the support ring 2; the support ring 2 is fixedly connected with the outer shaft 3; the outer wall of the support ring 2 is matched with the inner wall of the outer shaft 3 to limit the lead pin 4, and the lead pin 4 penetrates through the opening on the inner wall of the outer shaft 3.
A temperature sensor 8 is arranged on the surface of the disc body 5, and the temperature sensor 8 is connected with one end of the test lead 6; the test lead 6 passes through the through hole on the lead pin 4 in sequence, is arranged along the surface of the support ring 2 and the inner surface of the inner shaft 1, is connected with the electric lead 7, and transmits a test signal to the rack receiving device.
In this embodiment, the outer shaft 3 and the inner shaft 1 can be mounted on 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 (shown in the structure of figure 2) passes through the round hole of the outer shaft 3 (shown in the structure of 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 support ring 2 (structure shown in fig. 4) is provided with a corresponding square groove, and the square groove is matched with the square boss of the lead pin 4 to limit the rotation of the lead pin 4. Fig. 5 is a schematic view of the lead pin assembly gap, and as shown in fig. 5, the disc 5 will limit 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 the mismatch of radial deformation of the outer shaft 3 and the disc 5.
The function of the lead pins 4 is to protect the test leads 6, and since there is a certain distance in the radial direction between the outer shaft 3 and the disc 5, the test leads 6 may break under the action of centrifugal force and air flow if they are led directly from the disc 5 to the outer shaft 3.
In this embodiment, the lead pin 4 may be made of polyimide, and has a hardness of 30 to 45 (rockwell hardness, E), so that the disc body is not damaged; and the heat conduction 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 that of an air conduit in an engine, so that a flow field near the disc body 5 is ensured to be consistent with a real environment, and further, the temperature field of the disc body 5 is consistent with that in the engine. The air conduit is a pipeline for cooling air to pass through in the engine, and the air conduit and the compressor rotor form a channel for cooling air in the disk cavity.
In order to facilitate the lead, the diameter of a hole on the inner shaft 1 can be designed to be 2-3 times larger than that of the test lead 6, the test lead 6 can be fixed through soft fillers after penetrating through the inner shaft 1, and the test lead 6 is prevented from shaking in the inner shaft 1 when the rotor rotates;
the assembly sequence of this structure does: firstly, a lead pin 4 penetrates through a circular hole of an outer shaft 3, then the support ring 2 is installed, then a radial pin for connecting the outer shaft 3 and the support ring 2 is installed, after a disc body 5 is assembled, a test lead 6 firstly penetrates through lead holes of the lead pin 4 and the support ring 2, then the test lead 6 is fixed on the disc body 5 and connected with a thermocouple 8, and finally the test lead 6 penetrates through an inner shaft 1 to reach a lead device 7 at the front end of the gas compressor. The structure is implemented in a compressor part test for simulating the working state of an engine.

Claims (8)

1. A lead structure for temperature test of a compressor rotor disc body is characterized by comprising an inner shaft (1), a support ring (2), an outer shaft (3), a lead pin (4), a disc body (5), a test lead (6), an electrical initiator (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 electricity leading device (7), and the other end of the inner shaft is fixedly connected with the support ring (2); the support ring (2) is fixedly connected with the outer shaft (3); the outer wall of the support ring (2) is matched with the inner wall of the outer shaft (3) to limit the lead pin (4), and the lead pin (4) penetrates through an opening on the inner wall of the outer shaft (3);
a temperature sensor (8) is arranged on the surface of the tray body (5), 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 electric lead device (7).
2. 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 lead pin (4) has a thermal conductivity of 0.15 to 0.3W/(m-K).
4. The lead structure according to claim 1, wherein the lead pin (4) has a Rockwell hardness E of 30 to 45.
5. The lead structure of claim 1, characterized in that the upper part of the lead pin (4) is a cylindrical structure, and the lower part is a square boss; the square boss is positioned between the outer wall of the support ring (2) and the inner wall of the outer shaft (3).
6. A lead structure according to claim 5, characterized in that the cylindrical end surface of the lead pin (4) is in contact with the disc (5) during the lead structure test; gaps are reserved between the bottom end surface and the upper end surface of the square boss of the lead pin (4) and the outer wall of the support ring (2) and the inner wall of the outer shaft (3) respectively.
7. A lead construction according to claim 1, characterised in that the inner shaft (1) is of cylindrical construction; the inner shaft (1) is internally provided with a soft filler for fixing a test lead (6).
8. A lead construction according to claim 1, characterised in that the outer surface diameter of the outer shaft (3) corresponds to the diameter of the outer surface of the air duct in the engine.
CN202011106972.0A 2020-10-16 2020-10-16 Lead structure for testing temperature of rotor disc body of air compressor Active CN112345105B (en)

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CN202011106972.0A CN112345105B (en) 2020-10-16 2020-10-16 Lead structure for testing temperature of rotor disc body of air compressor

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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

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CN112345105B CN112345105B (en) 2023-06-23

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Cited By (2)

* Cited by examiner, † Cited by third party
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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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

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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

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Cited By (2)

* Cited by examiner, † Cited by third party
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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