CN112483454B - Evaluation method for surge margin of gas compressor - Google Patents
Evaluation method for surge margin of gas compressor Download PDFInfo
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- CN112483454B CN112483454B CN202011258157.6A CN202011258157A CN112483454B CN 112483454 B CN112483454 B CN 112483454B CN 202011258157 A CN202011258157 A CN 202011258157A CN 112483454 B CN112483454 B CN 112483454B
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- compressor
- surge margin
- parameters
- working point
- surge
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Classifications
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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
- F04D27/02—Surge control
-
- 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
Abstract
The invention belongs to the field of aircraft engines, and particularly relates to an evaluation method for surge margin of a gas compressor. The technical scheme of the invention is as follows: a method for evaluating surge margin of a compressor comprises the steps of taking parameters on a surge boundary of the compressor as a constant when an aircraft engine is in batch production, wherein the surge margin of the compressor is in negative correlation with parameters on a working point of the compressor, the parameters on the working point of the compressor are the ratio of the pressurization ratio on the working point to the air flow, and the larger the parameters on the working point of the compressor, the smaller the surge margin of the compressor. According to the evaluation method for the surge margin of the air compressor, the evaluation of the surge margin of the air compressor is completed through the measurement and calculation of the parameters of the inlet section of the air compressor during the test of the engine.
Description
Technical Field
The invention belongs to the field of aircraft engines, and particularly relates to an evaluation method for surge margin of a gas compressor.
Background
The surge margin of the compressor is usually evaluated through a complex test at the engine design stage, and after the engine is batched, the evaluation of the surge margin of the compressor through a bench delivery test is difficult to realize.
According to the calculation formula (1) of the surge margin of the compressor,
the surge margin of the compressor needs to know the pressure ratio and the air flow of the working point of the compressor, the pressure ratio of the surge boundary and the air flow. Therefore, when calculating the surge margin, besides the parameters of the working point, the surge boundary needs to be measured, and the surge boundary needs to be carried out on a professional test bed and cannot be realized on a common batch engine test bed.
Disclosure of Invention
The invention provides an evaluation method of compressor surge margin, which is used for evaluating the compressor surge margin by measuring and calculating the parameters of the inlet section of a compressor during the test of an engine.
The technical scheme of the invention is as follows:
a method for evaluating surge margin of a compressor comprises the steps of taking parameters on a surge boundary of the compressor as a constant when an aircraft engine is in batch production, wherein the surge margin of the compressor is in negative correlation with parameters on a working point of the compressor, the parameters on the working point of the compressor are the ratio of the pressurization ratio on the working point to the air flow, and the larger the parameters on the working point of the compressor, the smaller the surge margin of the compressor.
Further, the method for evaluating the surge margin of the compressor comprises the following specific steps:
1) installing air flow measuring equipment at an air inlet of the aircraft engine to measure the air flow;
2) installing total pressure measuring sensors in front of and behind the air compressor, and measuring the front and rear total pressure values of the air compressor;
3) calculating the pressure ratio of the compressor, namely the ratio of the total outlet pressure to the total inlet pressure;
4) calculating parameters on the working point of the gas compressor;
5) and comparing parameter values on the working points of the compressors in batches, and indirectly evaluating the surge margin of the compressors.
When the aircraft engine is in batch production, the parameters on the surge boundary of the compressor are regarded as constants, and then the calculation formula (1) of the surge margin of the compressor is simplified into the following formula (2):
as can be seen from the formula (2), the surge margin of the compressor is in negative correlation with the parameters of the working point of the compressor, and the larger the parameter of the working point of the compressor is, the smaller the surge margin of the compressor is.
The invention has the beneficial effects that: the invention can complete the evaluation of the surge margin of the air compressor on a common batch engine test bed through the measurement and calculation of the parameters of the inlet section of the air compressor.
Detailed Description
A method for evaluating surge margin of a gas compressor comprises the following specific steps:
1) installing air flow measuring equipment at an air inlet of the aircraft engine to measure the air flow;
2) installing total pressure measuring sensors in front of and behind the air compressor, and measuring the front and rear total pressure values of the air compressor;
3) calculating the pressure ratio of the compressor, namely the ratio of the total outlet pressure to the total inlet pressure;
4) calculating parameters on the working point of the gas compressor;
5) and comparing parameter values on the working points of the compressors in batches, and indirectly evaluating the surge margin of the compressors.
Under the same working state of the air compressors of the first and second aeroengines, the air flow is 100 and 100.5 respectively, the calculation results of the pressure ratio are 3 and 2.95 respectively, and the ratio of the pressure ratio/air flow on the working points of the air compressors of the two engines is 0.03 and 0.02935 respectively; since the ratio 0.03 of the pressure increase ratio/air flow of the first is larger than the ratio 0.02935 of the pressure increase ratio/air flow of the second, the compressor surge margin of the first is smaller than that of the second.
Claims (2)
1. A method for evaluating surge margin of a compressor is characterized in that when an aircraft engine is in batch production, parameters on a surge boundary of the compressor are regarded as constants, the surge margin of the compressor is in negative correlation with parameters on a working point of the compressor, the parameters on the working point of the compressor are the ratio of the pressure increase ratio on the working point to the air flow, and the larger the parameters on the working point of the compressor, the smaller the surge margin of the compressor.
2. The method for evaluating the surge margin of the compressor according to claim 1 is characterized by comprising the following specific steps of:
1) installing air flow measuring equipment at an air inlet of the aircraft engine to measure the air flow;
2) installing total pressure measuring sensors in front of and behind the air compressor, and measuring the front and rear total pressure values of the air compressor;
3) calculating the pressure ratio of the compressor, namely the ratio of the total outlet pressure to the total inlet pressure;
4) calculating parameters on the working point of the gas compressor;
5) and comparing parameter values on the working points of the compressors in batches, and indirectly evaluating the surge margin of the compressors.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011258157.6A CN112483454B (en) | 2020-11-12 | 2020-11-12 | Evaluation method for surge margin of gas compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011258157.6A CN112483454B (en) | 2020-11-12 | 2020-11-12 | Evaluation method for surge margin of gas compressor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112483454A CN112483454A (en) | 2021-03-12 |
| CN112483454B true CN112483454B (en) | 2022-03-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011258157.6A Active CN112483454B (en) | 2020-11-12 | 2020-11-12 | Evaluation method for surge margin of gas compressor |
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| CN103306822A (en) * | 2013-05-23 | 2013-09-18 | 南京航空航天大学 | Aerial turbofan engine control method based on surge margin estimation model |
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| CN111444636A (en) * | 2020-05-18 | 2020-07-24 | 南京航空航天大学 | Axial flow compressor surge margin calculation method based on primitive level degradation characteristic diagram |
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| US6574584B2 (en) * | 2000-12-11 | 2003-06-03 | General Electric Company | Method for evaluating compressor stall/surge margin requirements |
| IT1401663B1 (en) * | 2010-08-31 | 2013-08-02 | Nuovo Pignone Spa | DEVICE AND METHOD TO DETECT A OVERCURRENT IN A COMPRESSOR AND MOVE A CURRENT MARGIN. |
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2020
- 2020-11-12 CN CN202011258157.6A patent/CN112483454B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101329221A (en) * | 2008-05-30 | 2008-12-24 | 沪东重机有限公司 | Method for determining pressure booster distribution machine parameter under marine diesel ISO condition |
| CN102589889A (en) * | 2012-02-23 | 2012-07-18 | 中国航空动力机械研究所 | Overall-unit forced surge method for engine |
| CN103306822A (en) * | 2013-05-23 | 2013-09-18 | 南京航空航天大学 | Aerial turbofan engine control method based on surge margin estimation model |
| CN109611370A (en) * | 2018-12-29 | 2019-04-12 | 中国船舶重工集团公司第七0三研究所 | The regulation device of helium compressor surge margin and regulation method based on the regulation device |
| CN111444636A (en) * | 2020-05-18 | 2020-07-24 | 南京航空航天大学 | Axial flow compressor surge margin calculation method based on primitive level degradation characteristic diagram |
Non-Patent Citations (3)
| Title |
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| 基于试车试验的涡轴发动机整机喘振裕度研究;余双 等;《海军航空工程学院学报》;20181231;第33卷(第4期);第371-375、400页 * |
| 进气畸变下航空发动机失速/喘振适航审定方法;李志平等;《航空学报》;20150930(第09期);第2947-2957页 * |
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| CN112483454A (en) | 2021-03-12 |
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