CN112857815B - Method for testing internal noise of aircraft engine compressor - Google Patents
Method for testing internal noise of aircraft engine compressor Download PDFInfo
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- CN112857815B CN112857815B CN201911190596.5A CN201911190596A CN112857815B CN 112857815 B CN112857815 B CN 112857815B CN 201911190596 A CN201911190596 A CN 201911190596A CN 112857815 B CN112857815 B CN 112857815B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H17/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves, not provided for in the preceding groups
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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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
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Combustion & Propulsion (AREA)
- Control Of Positive-Displacement Pumps (AREA)
- Testing Of Engines (AREA)
Abstract
The invention belongs to the field of performance testing of aero-engines, and particularly relates to a method for testing internal noise of an aero-engine compressor. The technical scheme of the invention is as follows: a method for testing internal noise of an aircraft engine compressor comprises the steps of determining the position of a measuring point as a hole probe hole on a high-pressure casing of the aircraft engine, leading out an internal noise signal of the engine through a switching device, and connecting the switching device with a noise measurement system to accurately measure the internal noise of the engine compressor. The method can accurately measure the internal noise of the aero-engine compressor.
Description
Technical Field
The invention belongs to the field of performance testing of aero-engines, and particularly relates to a method for testing internal noise of an aero-engine compressor.
Background
At present, in the aspect of noise testing of the domestic aeroengine, the noise testing system mainly focuses on external noise testing of the aeroengine, and can better meet the testing requirements of noise (jet noise, BPF noise and the like) outside the engine through a noise measuring system. The interior of an aircraft engine compressor belongs to a complex environment with high temperature, high pressure and high flow velocity, and the internal noise test of the compressor is very difficult to develop under the condition of not influencing the performance of the engine. For the internal noise of the air compressor of the aircraft engine, preliminary research shows that part of sound waves with specific frequencies have cut-off characteristics and cannot be transmitted to the outside of the engine, so that research on a test method for the internal noise of the air compressor of the aircraft engine is urgently needed.
Disclosure of Invention
The invention provides a method for testing internal noise of an aircraft engine compressor, which can accurately measure the internal noise of the aircraft engine compressor.
The technical scheme of the invention is as follows:
a method for testing internal noise of an aircraft engine compressor comprises the steps of determining the positions of test points as hole detector holes in a high-pressure casing of the aircraft engine, leading out internal noise signals of the engine through a switching device, and connecting the switching device with a noise measurement system to accurately measure the internal noise of the engine compressor.
Further, the internal noise testing method of the aircraft engine gas compressor comprises the steps that the switching device comprises a connecting pipe, a testing system connector, a casing connector, a sealing washer and a fixing nut, the testing system connector and the casing connector are respectively and fixedly arranged at two ends of the connecting pipe, the sealing washer is arranged between the connecting pipe and the fixing nut, and the fixing nut is connected with an engine culvert casing hole detector mounting seat.
Further, according to the method for testing the internal noise of the aircraft engine compressor, the casing connector is connected with the high-pressure casing hole detector mounting seat, the front end of the casing connector is flush with the inner surface of the high-pressure casing and cannot protrude out of the inner surface of the high-pressure casing; the testing system connector is connected with the noise measuring system through threads; the inner surface of a pipeline formed by the casing connector, the connecting pipe and the testing system connector is smooth and clean, a sealing test is required to be carried out, kerosene or antirust liquid is required to be used for a sealing test, the pressure is kept at 0.5-1 MPa for 5-10 min, and leakage is not allowed; the sealing washer is made of a high-temperature-resistant elastic non-metallic material, has good temperature resistance in the temperature range of 200-300 ℃, and cannot generate an overheating deformation phenomenon.
Further, the method for testing the internal noise of the aircraft engine compressor comprises the steps of testing and arranging 1-2 test points for local noise signals of the aircraft engine compressor; and testing 4-6 test points which are distributed in the whole compressor along the axial direction of the compressor in the internal noise environment of the compressor.
Further, the method for testing the internal noise of the air compressor of the aircraft engine comprises the following steps:
1) the method comprises the following steps of testing internal noise data of the compressor under the full-speed condition, wherein the whole test run process needs to comprise warming-up and pushing-up (N2 speed: MC to 100%) and pulldown (N2: 100% -MC), wherein the heating is carried out for 5-8min, and noise signals can not be collected in the process; in the pushing-up and pulling-down stages, the number of engine state points is set to be 6-8, and the stay time of each state point is 1-3 min;
2) for testing the internal noise data of the compressor in a specific rotating speed range, the test run process needs to comprise warm-up and push-up (N2 rotating speed: n2 min ～N2 max 100%) and pull-down (N2: 100% -N2 max ～N2 min ) Three stages, wherein the warming is carried out for 5-8min, and noise signals can not be collected in the process; in the push-up and pull-down stages, setting an engine state point at the rotating speed of N2 every 100-200 revolutions, and staying for 1-2min at each state point;
3) in order to ensure that the test data is stable and accurate, the whole test needs to be repeatedly tested for 1-2 times, and the interval of repeated engine test running needs to be 30-60 min.
The invention has the beneficial effects that: the testing method can accurately measure the internal noise of the air compressor of the aircraft engine.
Drawings
FIG. 1 is a schematic diagram of a noise test state;
FIG. 2 is a view of the structure of the adapter;
FIG. 3 is a schematic diagram of a hole detector hole location on a high-pressure casing of an aircraft engine;
fig. 4 is a picture of a noise measurement system.
Detailed Description
A method for testing internal noise of an aircraft engine compressor comprises the steps of determining the positions of test points as hole detector holes 8 on a high-pressure casing 3 of the aircraft engine, leading out internal noise signals of the engine through a switching device 1, and connecting the switching device 1 with a noise measurement system 2 to accurately measure the internal noise of the engine compressor. As shown in fig. 4, the noise measurement system 2 is a noise measurement system which is independently developed by the university of shenyang aerospace and is established based on a rigid wall waveguide technology, the system meets the related requirements of GJB150.17A-2009, the measurement error is less than or equal to 1dB, and the system has good static and dynamic characteristics.
As shown in fig. 2, the high-pressure casing 3 of the engine is provided with a plurality of hole probes 8, which can meet the requirement of accurately measuring the internal noise environment of the compressor of the engine.
As shown in fig. 1 and 3, switching device 1 includes connecting pipe 11, test system connector 13, casing connector 12, seal ring 14 and fixation nut 15, and test system connector 13 and casing connector 12 are fixed the setting respectively and are in the both ends of connecting pipe 11, seal ring 14 sets up connecting pipe 11 with between fixation nut 15, fixation nut 15 is connected with engine culvert casing hole finder mount pad 6. The casing connector 12 is connected with the high-voltage casing hole detector mounting seat 5, and the front end of the casing connector 12 is flush with the inner surface of the high-voltage casing 3 and cannot protrude out of the inner surface of the high-voltage casing 3; the testing system connector 13 is connected with the noise measuring system 2 through threads; the inner surface of a pipeline formed by the casing connector 12, the connecting pipe 11 and the testing system connector 13 is smooth and clean, a sealing test is required to be carried out, kerosene or antirust liquid is required to be used for a sealing test, the pressure is kept for 5-10 min at 0.5-1 MPa, and leakage is not allowed; the sealing washer 14 is made of a high-temperature-resistant elastic non-metallic material, has good temperature resistance in the range of 200-300 ℃, and cannot generate an overheating deformation phenomenon. Testing 1-2 test points for testing local noise signals of an engine compressor; and 4-6 measuring points are axially distributed along the air compressor for testing the internal noise environment of the whole air compressor.
The test process comprises the following steps:
1) the internal noise data of the compressor under the condition of full rotation speed is tested, and the whole test run process needs to comprise warm-up and push-up (N2 rotation speed: MC to 100%) and pulldown (N2: 100% -MC), wherein the heating is carried out for 5-8min, and noise signals can not be collected in the process; in the pushing-up and pulling-down stages, the number of engine state points is set to be 6-8, and the stay time of each state point is 1-3 min;
2) for testing the internal noise data of the compressor in a specific rotating speed range, the test run process needs to comprise warm-up and push-up (N2 rotating speed: n2 min ～N2 max 100%) and pull-down (N2: 100% -N2 max ～N2 min ) Three stepsA stage, wherein the heating is carried out for 5-8min, and noise signals can not be collected in the process; in the push-up and pull-down stages, setting an engine state point at the rotating speed of N2 every 100-200 revolutions, and staying for 1-2min at each state point;
3) in order to ensure that the test data is stable and accurate, the whole test needs to be repeatedly tested for 1-2 times, and the interval of repeated engine test running needs to be 30-60 min.
Claims (2)
1. The method for testing the internal noise of the air compressor of the aero-engine is characterized in that the positions of the test points are determined as hole detector holes in a high-pressure casing of the aero-engine, an internal noise signal of the aero-engine is led out through a switching device, and the switching device is connected with a noise measurement system to realize accurate measurement of the internal noise of the air compressor of the aero-engine; the switching device comprises a connecting pipe, a test system connector, a casing connector, a sealing washer and a fixing nut, wherein the test system connector and the casing connector are respectively and fixedly arranged at two ends of the connecting pipe; the casing connector is connected with the high-voltage casing hole detector mounting seat, and the front end of the casing connector is flush with the inner surface of the high-voltage casing and cannot protrude out of the inner surface of the high-voltage casing; the testing system connector is connected with the noise measuring system through threads; the inner surface of a pipeline formed by the casing connector, the connecting pipe and the testing system connector is smooth and clean, a sealing test is required to be carried out, kerosene or antirust liquid is required to be used for a sealing test, the pressure is kept at 0.5-1 MPa for 5-10 min, and leakage is not allowed; the sealing washer is made of a high-temperature-resistant elastic non-metallic material, has good temperature resistance in the range of 200-300 ℃, and cannot generate an overheating deformation phenomenon; the test process comprises the following steps:
1) internal noise data of the compressor under the condition of full rotation speed is tested, and the whole test run process needs to comprise the steps of warming up, pushing up N2 rotation speed: MC-100% and speed of pull-down N2: 100% -MC, wherein warming is carried out for 5-8min, and noise signals are not collected in the process; in the push-up and pull-down stages, the number of engine state points is set to be 6-8, and the stay time of each state point is 1-3 min;
2) testing internal noise data of the compressor in a specific rotating speed range, wherein a test run process needs to comprise warming up and pushing up N2 rotating speed: n2 min ～N2 max 100% and pull-down N2 rotational speed: 100% -N2 max ～N2 min Three stages, wherein the heating is performed for 5-8min, and no noise signal is collected in the process; in the pushing-up and pulling-down stages, setting an engine state point every 100-200 revolutions at the rotating speed of N2, and staying for 1-2min at each state point;
3) in order to ensure that the test data is stable and accurate, the whole test needs to be repeatedly tested for 1-2 times, and the repeated test run of the engine needs to be separated by 30-60 min.
2. The method for testing the internal noise of the aircraft engine compressor according to claim 1, wherein 1-2 test points are arranged for testing the local noise signal of the aircraft engine compressor; and testing 4-6 test points which are distributed in the whole compressor along the axial direction of the compressor in the internal noise environment of the compressor.
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| CN201911190596.5A CN112857815B (en) | 2019-11-28 | 2019-11-28 | Method for testing internal noise of aircraft engine compressor |
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| CN201911190596.5A CN112857815B (en) | 2019-11-28 | 2019-11-28 | Method for testing internal noise of aircraft engine compressor |
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Citations (4)
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|---|---|---|---|---|
| FR2934369A1 (en) * | 2008-07-22 | 2010-01-29 | Renault Sas | Onboard combustion noise determination system for cylinder in diesel engine of motor vehicle, has determination module receiving signal and filtered pressure values at its input, and continuously determining combustion noise in cylinder |
| CN106845111A (en) * | 2017-01-19 | 2017-06-13 | 沈阳航空航天大学 | A kind of aero-engine noise Forecasting Methodology based on multiple regression |
| CN108760329A (en) * | 2018-05-21 | 2018-11-06 | 中国航发沈阳发动机研究所 | A kind of low-pressure turbine noise fest method and its improved method |
| CN208296979U (en) * | 2018-06-05 | 2018-12-28 | 中国航发沈阳发动机研究所 | A kind of Aero Engine Testing noise testing sensor fixing structure |
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2019
- 2019-11-28 CN CN201911190596.5A patent/CN112857815B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2934369A1 (en) * | 2008-07-22 | 2010-01-29 | Renault Sas | Onboard combustion noise determination system for cylinder in diesel engine of motor vehicle, has determination module receiving signal and filtered pressure values at its input, and continuously determining combustion noise in cylinder |
| CN106845111A (en) * | 2017-01-19 | 2017-06-13 | 沈阳航空航天大学 | A kind of aero-engine noise Forecasting Methodology based on multiple regression |
| CN108760329A (en) * | 2018-05-21 | 2018-11-06 | 中国航发沈阳发动机研究所 | A kind of low-pressure turbine noise fest method and its improved method |
| CN208296979U (en) * | 2018-06-05 | 2018-12-28 | 中国航发沈阳发动机研究所 | A kind of Aero Engine Testing noise testing sensor fixing structure |
Non-Patent Citations (2)
| Title |
|---|
| 压气机内部噪声特征与转子叶片声固耦合机理分析;赵奉同 等;《航空学报》;20190525;第40卷(第5期);第119-128页 * |
| 多级轴流压气机内部噪声测试及频谱演化特征分析;栾孝驰等;《沈阳航空航天大学学报》;20120825(第04期);第10-15页 * |
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