CN113931866B - Pneumatic instability identification method for aero-engine compressor - Google Patents
Pneumatic instability identification method for aero-engine compressor Download PDFInfo
- Publication number
- CN113931866B CN113931866B CN202111255872.9A CN202111255872A CN113931866B CN 113931866 B CN113931866 B CN 113931866B CN 202111255872 A CN202111255872 A CN 202111255872A CN 113931866 B CN113931866 B CN 113931866B
- Authority
- CN
- China
- Prior art keywords
- pressure
- low
- pressure compressor
- compressor
- engine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Positive-Displacement Air Blowers (AREA)
Abstract
The application particularly relates to an aeroengine compressor pneumatic instability identification method, which comprises the following steps: from the middle of the low-pressure compressor in the current periodExtracting stall characteristic frequency signal P of current period from stage pulsation pressure data 1ps Low frequency signal P 1bs The method comprises the steps of carrying out a first treatment on the surface of the If |P 1ps /P 1bs |≥C 1max Identifying that the low-pressure compressor stalls; if |P after recognizing stall of low-pressure compressor 1ps /P 1bs |<C 1min Identifying stall elimination of the low pressure compressor; extracting stall characteristic frequency signal P of the current period from intermediate stage pulsating pressure data of the high-pressure compressor of the current period 2ps Low frequency signal P 2bs The method comprises the steps of carrying out a first treatment on the surface of the If |P 2ps /P 2bs |≥C 2max Identifying that the high-pressure compressor stalls; after recognizing that stall occurs in the high-pressure compressor, |P 1ps /P 1bs |<C 2min Identifying stall elimination of the high pressure compressor; wherein, the engine low-pressure conversion rotating speed n 1 C when the temperature is between 0.3 and 1.05 1max 0.15; engine low pressure conversion speed n 1 C when the temperature is between 0.3 and 1.05 1min 0.10; high-pressure conversion speed n of engine 2 C when the temperature is between 0.7 and 1.05 2max 0.15; high-pressure conversion speed n of engine 2 C when the temperature is between 0.7 and 1.05 2min 0.10.
Description
Technical Field
The application belongs to the technical field of pneumatic instability identification of aero-engine compressors, and particularly relates to a pneumatic instability identification method of an aero-engine compressor.
Background
The pneumatic instability of the aero-engine comprises stall and instability, the type of the aero-engine generating the pneumatic instability and the first position of the aero-engine are accurately and rapidly identified, and the method has important significance for the development of the aero-engine and the safe flight of the aero-engine.
Currently, a differential pressure identification method is adopted for identifying the pneumatic instability of the aero-engine, and the identification method has the following defects:
1) The single-threshold identification method is adopted, and threshold parameters are not related to the engine state or have low association degree, so that the anti-interference capability and the fault tolerance are poor;
2) The type of pneumatic instability and its first place cannot be identified.
The present application has been made in view of the existence of the above-mentioned technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present invention, which is not necessarily prior art to the present application, and should not be used for evaluating the novelty and the creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide a method for identifying aerodynamic instability of an aero-engine compressor, which overcomes or alleviates the technical drawbacks of at least one aspect known to exist.
The technical scheme of the application is as follows:
a pneumatic instability identification method for an aeroengine compressor comprises the following steps:
intermediate stage pulsating pressure data from low pressure compressor at current time periodExtracting stall characteristic frequency signal P of current period 1ps Low frequency signal P 1bs ；
If |P 1ps /P 1bs |≥C 1max Identifying that the low-pressure compressor stalls;
if |P after recognizing stall of low-pressure compressor 1ps /P 1bs |<C 1min Identifying stall elimination of the low pressure compressor;
extracting stall characteristic frequency signal P of the current period from intermediate stage pulsating pressure data of the high-pressure compressor of the current period 2ps Low frequency signal P 2bs ；
If |P 2ps /P 2bs |≥C 2max Identifying that the high-pressure compressor stalls;
after recognizing that stall occurs in the high-pressure compressor, |P 1ps /P 1bs |<C 2min Identifying stall elimination of the high pressure compressor;
wherein, the liquid crystal display device comprises a liquid crystal display device,
engine low pressure conversion speed n 1 C when the temperature is between 0.3 and 1.05 1max 0.15;
engine low pressure conversion speed n 1 C when the temperature is between 0.3 and 1.05 1min 0.10;
high-pressure conversion speed n of engine 2 C when the temperature is between 0.7 and 1.05 2max 0.15;
high-pressure conversion speed n of engine 2 C when the temperature is between 0.7 and 1.05 2min 0.10.
According to at least one embodiment of the present application, in the method for identifying aerodynamic instability of an aero-engine compressor, the method further includes:
extracting a surge characteristic frequency signal P of the current period from the intermediate-stage pulsation pressure data of the low-pressure compressor of the current period 1bcj ；
Extracting a surge characteristic frequency signal P of the previous period from the intermediate stage pulsation pressure data of the low-pressure compressor of the previous period 1bcn ；
If it is
Identifying that the low pressure compressor is surging;
if the low-pressure compressor is identified to be surging
Identifying a low pressure compressor surge cancellation;
extracting a surge characteristic frequency signal P of the current period from the intermediate-stage pulsation pressure data of the high-pressure compressor of the current period 2bcj ；
Extracting a surge characteristic frequency signal P of the previous period from the intermediate-stage pulsation pressure data of the high-pressure compressor of the previous period 2bcn ；
If it is
Identifying that the high pressure compressor is surging;
if the high-pressure compressor is identified to be surging
Identifying a high pressure compressor surge cancellation;
wherein, the liquid crystal display device comprises a liquid crystal display device,
engine low pressure conversion speed n 1 When the U is positioned between 0.3 and 1.05 1max 0.40;
engine low pressure conversion speed n 1 When the U is positioned between 0.3 and 1.05 1min 0.20;
high-pressure conversion speed n of engine 2 When the U is positioned between 0.7 and 1.05 2max 0.40;
high-pressure conversion speed n of engine 2 When the U is positioned between 0.7 and 1.05 2min 0.20.
According to at least one embodiment of the application, in the aero-engine compressor pneumatic instability identification method, low-pressure compressor intermediate-stage pulsation pressure data are acquired at a frequency not lower than 5 k/s;
the intermediate stage pulsation pressure data of the high-pressure compressor are acquired at a frequency of not less than 5 k/s.
Drawings
Fig. 1 is a schematic diagram of an aero-engine compressor pneumatic instability identification method provided in an embodiment of the present application.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.
The present application is described in further detail below in conjunction with fig. 1.
A pneumatic instability identification method for an aeroengine compressor comprises the following steps:
extracting stall characteristic frequency signal P of the current period from the intermediate stage pulsating pressure data of the low-pressure compressor of the current period 1ps Low frequency signal P 1bs ；
If |P 1ps /P 1bs |≥C 1max Identifying that the low-pressure compressor stalls;
if |P after recognizing stall of low-pressure compressor 1ps /P 1bs |<C 1min Identifying stall elimination of the low pressure compressor;
extracting stall characteristic frequency signal P of the current period from intermediate stage pulsating pressure data of the high-pressure compressor of the current period 2ps Low frequency signal P 2bs ；
If |P 2ps /P 2bs |≥C 2max Identifying that the high-pressure compressor stalls;
after recognizing that stall occurs in the high-pressure compressor, |P 1ps /P 1bs |<C 2min Identifying stall elimination of the high pressure compressor;
wherein, the liquid crystal display device comprises a liquid crystal display device,
engine low pressure conversion speed n 1 C when the temperature is between 0.3 and 1.05 1max 0.15;
engine low pressure conversion speed n 1 C when the temperature is between 0.3 and 1.05 1min 0.10;
high-pressure conversion speed n of engine 2 C when the temperature is between 0.7 and 1.05 2max 0.15;
high-pressure conversion speed n of engine 2 C when the temperature is between 0.7 and 1.05 2min 0.10.
For the aero-engine compressor aerodynamic instability identification method disclosed in the above embodiment, those skilled in the art will understand that it adopts C for stall of low-pressure compressor in aero-engine 1max 、C 1min Double threshold value is used for identification, and C is adopted for stall of high-pressure compressor in aeroengine 2max 、C 2min The double threshold value is identified, the threshold value parameter is related to the conversion rotating speed of the engine, the anti-interference capability and the fault tolerance of the identification of the stall of the compressor are good, in addition, the stall of the low-pressure compressor and the stall of the high-pressure compressor are identified, and the first-time position of the stall of the compressor can be determined when the compressor occurs.
In the method for identifying aerodynamic instability of an aero-engine compressor disclosed in the above embodiment, C 1max 、C 1min 、C 2max 、C 2min The values of the pulse pressure signals are obtained by adopting a plurality of groups of engine stall and stall recovery pulse pressure signals for simulation verification, the pulse pressure signals have strong universality, and when the technical scheme disclosed by the application is applied, related technicians can also determine the specific values according to specific actual conditions.
In some optional embodiments, the method for identifying aerodynamic instability of an aero-engine compressor further includes:
extracting a surge characteristic frequency signal P of the current period from the intermediate-stage pulsation pressure data of the low-pressure compressor of the current period 1bcj ；
Extracting a surge characteristic frequency signal P of the previous period from the intermediate stage pulsation pressure data of the low-pressure compressor of the previous period 1bcn ；
If it is
Identifying that the low pressure compressor is surging;
if the low-pressure compressor is identified to be surging
Identifying a low pressure compressor surge cancellation;
extracting a surge characteristic frequency signal P of the current period from the intermediate-stage pulsation pressure data of the high-pressure compressor of the current period 2bcj ；
Extracting a surge characteristic frequency signal P of the previous period from the intermediate-stage pulsation pressure data of the high-pressure compressor of the previous period 2bcn ；
If it is
Identifying that the high pressure compressor is surging;
if the high-pressure compressor is identified to be surging
Identifying a high pressure compressor surge cancellation;
wherein, the liquid crystal display device comprises a liquid crystal display device,
engine low pressure conversion speed n 1 When the U is positioned between 0.3 and 1.05 1max 0.40;
engine low pressure conversion speed n 1 When the U is positioned between 0.3 and 1.05 1min 0.20;
high-pressure conversion speed n of engine 2 When the U is positioned between 0.7 and 1.05 2max 0.40;
high-pressure conversion speed n of engine 2 When the U is positioned between 0.7 and 1.05 2min 0.20;
the values of the parameters are obtained by adopting a plurality of groups of pulse pressure signals for engine stall and stall recovery to carry out simulation verification.
The aeroengine compressor disclosed for the above embodimentsThe pneumatic instability identification method is understood by those skilled in the art to adopt U for surge of a low-pressure compressor in an aero-engine 1max 、U 1min Double threshold value identification is carried out, and U is adopted for surge of high-pressure compressor in aero-engine 2max 、U 2min The double threshold is identified, the threshold parameter is related to the converted rotating speed of the engine, the anti-interference capability and fault tolerance of the identification of the compressor surge are good, in addition, the surging of the low-pressure compressor and the high-pressure compressor is identified, and the initial position of the compressor surge can be determined when the compressor surging occurs.
For the method for identifying the pneumatic instability of the air compressor of the aeroengine disclosed by the embodiment, those skilled in the art can understand that the method adopts a separate algorithm to identify the stall and surge of the high-pressure air compressor and the low-pressure air compressor respectively, and can determine the type and the initial position of the pneumatic instability of the air compressor when the pneumatic instability of the air compressor occurs.
In the method for identifying pneumatic instability of air compressor of aero-engine disclosed in the above embodiment, U 1max 、U 1min 、U 2max 、U 2min The values of the pulse pressure signals are obtained by adopting simulation verification of a plurality of groups of engine surge and surge recovery, the pulse pressure signals have strong universality, and when the technical scheme disclosed by the application is applied, related technicians can also determine the specific values according to specific actual conditions.
In some optional embodiments, in the aero-engine compressor pneumatic instability identification method, the low-pressure compressor intermediate-stage pulsation pressure data is acquired at a frequency not lower than 5 k/s;
the intermediate stage pulsation pressure data of the high-pressure compressor are acquired at a frequency of not less than 5 k/s.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments illustrated in the accompanying drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the relevant technical features without departing from the principles of the present application, and those changes or substitutions will now fall within the scope of the present application.
Claims (3)
1. The method for identifying the pneumatic instability of the aero-engine compressor is characterized by comprising the following steps of:
extracting stall characteristic frequency signal P of the current period from the intermediate stage pulsating pressure data of the low-pressure compressor of the current period 1ps Low frequency signal P 1bs ；
If |P 1ps /P 1bs |≥C 1max Identifying that the low-pressure compressor stalls;
if |P after recognizing stall of low-pressure compressor 1ps /P 1bs |<C 1min Identifying stall elimination of the low pressure compressor;
extracting stall characteristic frequency signal P of the current period from intermediate stage pulsating pressure data of the high-pressure compressor of the current period 2ps Low frequency signal P 2bs ；
If |P 2ps /P 2bs |≥C 2max Identifying that the high-pressure compressor stalls;
after recognizing that stall occurs in the high-pressure compressor, |P 1ps /P 1bs |<C 2min Identifying stall elimination of the high pressure compressor;
wherein, the liquid crystal display device comprises a liquid crystal display device,
engine low pressure conversion speed n 1 C when the temperature is between 0.3 and 1.05 1max 0.15;
engine low pressure conversion speed n 1 C when the temperature is between 0.3 and 1.05 1min 0.10;
high-pressure conversion speed n of engine 2 C when the temperature is between 0.7 and 1.05 2max 0.15;
high-pressure conversion speed n of engine 2 C when the temperature is between 0.7 and 1.05 2min 0.10.
2. The method for identifying aerodynamic instability of an aircraft engine compressor according to claim 1, wherein,
further comprises:
extracting a surge characteristic frequency signal P of the current period from the intermediate-stage pulsation pressure data of the low-pressure compressor of the current period 1bcj ；
Extracting a surge characteristic frequency signal P of the previous period from the intermediate stage pulsation pressure data of the low-pressure compressor of the previous period 1bcn ；
If it is
Identifying that the low pressure compressor is surging;
if the low-pressure compressor is identified to be surging
Identifying a low pressure compressor surge cancellation;
extracting a surge characteristic frequency signal P of the current period from the intermediate-stage pulsation pressure data of the high-pressure compressor of the current period 2bcj ；
Extracting a surge characteristic frequency signal P of the previous period from the intermediate-stage pulsation pressure data of the high-pressure compressor of the previous period 2bcn ；
If it is
Identifying that the high pressure compressor is surging;
if the high-pressure compressor is identified to be surging
Identifying a high pressure compressor surge cancellation;
wherein, the liquid crystal display device comprises a liquid crystal display device,
engine low pressure conversion speed n 1 When the U is positioned between 0.3 and 1.05 1max 0.40;
engine low pressure conversion speed n 1 When the U is positioned between 0.3 and 1.05 1min 0.20;
high-pressure conversion speed n of engine 2 When the U is positioned between 0.7 and 1.05 2max 0.40;
high-pressure conversion speed n of engine 2 When the U is positioned between 0.7 and 1.05 2min 0.20.
3. The method for identifying aerodynamic instability of an aircraft engine compressor according to claim 1, wherein,
the intermediate stage pulsation pressure data of the low-pressure compressor are acquired at the frequency of not lower than 5 k/s;
the intermediate stage pulsation pressure data of the high-pressure compressor are acquired at a frequency of not less than 5 k/s.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111255872.9A CN113931866B (en) | 2021-10-27 | 2021-10-27 | Pneumatic instability identification method for aero-engine compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111255872.9A CN113931866B (en) | 2021-10-27 | 2021-10-27 | Pneumatic instability identification method for aero-engine compressor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113931866A CN113931866A (en) | 2022-01-14 |
| CN113931866B true CN113931866B (en) | 2023-06-20 |
Family
ID=79284494
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111255872.9A Active CN113931866B (en) | 2021-10-27 | 2021-10-27 | Pneumatic instability identification method for aero-engine compressor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113931866B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4622808A (en) * | 1984-12-20 | 1986-11-18 | United Technologies Corporation | Surge/stall cessation detection system |
| CN110005628A (en) * | 2019-03-27 | 2019-07-12 | 南京航空航天大学 | Compressor aerodynamic unstability on-line identification method and system based on dystopy variance analysis |
| CN110162858A (en) * | 2019-05-14 | 2019-08-23 | 中国科学院工程热物理研究所 | Compressor Stability prediction technique |
| CN110735669A (en) * | 2019-10-08 | 2020-01-31 | 中国航发沈阳发动机研究所 | Method and device for judging rotating stall of aviation gas turbine engine |
| CN113482960A (en) * | 2021-06-23 | 2021-10-08 | 中国航发沈阳发动机研究所 | Method for judging surge of aviation gas turbine engine |
-
2021
- 2021-10-27 CN CN202111255872.9A patent/CN113931866B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4622808A (en) * | 1984-12-20 | 1986-11-18 | United Technologies Corporation | Surge/stall cessation detection system |
| CN110005628A (en) * | 2019-03-27 | 2019-07-12 | 南京航空航天大学 | Compressor aerodynamic unstability on-line identification method and system based on dystopy variance analysis |
| CN110162858A (en) * | 2019-05-14 | 2019-08-23 | 中国科学院工程热物理研究所 | Compressor Stability prediction technique |
| CN110735669A (en) * | 2019-10-08 | 2020-01-31 | 中国航发沈阳发动机研究所 | Method and device for judging rotating stall of aviation gas turbine engine |
| CN113482960A (en) * | 2021-06-23 | 2021-10-08 | 中国航发沈阳发动机研究所 | Method for judging surge of aviation gas turbine engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113931866A (en) | 2022-01-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110131193B (en) | Method and system for monitoring surge fault of aircraft engine | |
| CN110735669B (en) | Method and device for judging rotating stall of aviation gas turbine engine | |
| CN110410336B (en) | Automatic pump cavitation state identification method | |
| CN102721545A (en) | Rolling bearing failure diagnostic method based on multi-characteristic parameter | |
| CN107991706B (en) | Coal seam hydraulic fracturing microseismic signal combined noise reduction method based on wavelet packet multiple threshold and improved empirical mode decomposition | |
| CN110146291A (en) | A kind of Rolling Bearing Fault Character extracting method based on CEEMD and FastICA | |
| CN113931866B (en) | Pneumatic instability identification method for aero-engine compressor | |
| CN109598255B (en) | Energy operator k-gradient-based self-adaptive extraction method for impact start points of reciprocating mechanical vibration signals | |
| CN109297713A (en) | It is a kind of based on steadily with the steam turbine hostdown diagnostic method of Non-stationary vibration signal feature selecting | |
| CN109826816B (en) | Intelligent early warning system and method for fan stall | |
| CN113482960B (en) | Method for judging surge of aviation gas turbine engine | |
| CN110991544B (en) | Axial plunger pump cavitation level identification method based on PICA-VMD and Hilbert marginal spectrum | |
| CN110987433B (en) | Bearing fault early warning method based on high-frequency signal characteristic amplitude | |
| CN112233695A (en) | Oiling machine abnormal sound analysis and fault early warning system based on artificial intelligence and big data | |
| CN109781245B (en) | Objective evaluation method for pulse noise of diesel engine | |
| CN110030110B (en) | Method and device for improving aerodynamic stability of shipboard aircraft engine based on state recognition | |
| CN208221189U (en) | A kind of turbocharger pressure shell structure of low induction noise | |
| CN104314618A (en) | Low-pressure turbine blade structure and method for reducing loss of blade | |
| CN114151320A (en) | Identification algorithm for instability of compressor flow system | |
| CN110362065B (en) | State diagnosis method of anti-surge control system of aircraft engine | |
| CN203614172U (en) | A silencer | |
| CN108266356A (en) | The control system and control method of air inlet off-load air compressor machine | |
| CN106949054A (en) | The control method and system of pure electric vehicle " sliding vane type " air pump | |
| CN116698385A (en) | Strong noise interference resistant mechanical equipment health state monitoring method and device | |
| CN110347666B (en) | Method and device for improving time sequence data quality and early warning |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |