CN110907120B - Real-time feedback control method for pressure drop ratio of outlet of injection type nacelle - Google Patents
Real-time feedback control method for pressure drop ratio of outlet of injection type nacelle Download PDFInfo
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- CN110907120B CN110907120B CN201811079624.1A CN201811079624A CN110907120B CN 110907120 B CN110907120 B CN 110907120B CN 201811079624 A CN201811079624 A CN 201811079624A CN 110907120 B CN110907120 B CN 110907120B
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
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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
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/065—Measuring arrangements specially adapted for aerodynamic testing dealing with flow
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D27/00—Simultaneous control of variables covered by two or more of main groups G05D1/00 - G05D25/00
- G05D27/02—Simultaneous control of variables covered by two or more of main groups G05D1/00 - G05D25/00 characterised by the use of electric means
Abstract
The invention discloses a real-time feedback control method for the pressure drop ratio of an outlet of an injection type nacelle, which takes the pressure drop ratio of the outlet of the injection type nacelle as a control target, measures and feeds back the pressure drop ratio in real time, actually converts the pressure drop ratio into real-time feedback and control on pipeline flow, and finally realizes the real-time high-precision measurement and control on the air supply flow and the pressure drop ratio of the outlet; the method can realize that the control precision of the gas supply flow is better than 0.3 percent, the control precision of the pressure drop ratio is better than 0.01, the automatic real-time quick adjustment of the pressure drop ratio during the test is realized, the pressure drop ratio can be set as the input condition during the test, and the setting and control flow of the jet flow state during the jet flow test is greatly simplified.
Description
Technical Field
The invention relates to the field of wind tunnel tests, in particular to a real-time feedback control method for the pressure drop ratio of an outlet of an injection type nacelle.
Background
The jet-propelled nacelle is an aircraft engine power simulation device used in a wind tunnel test, and realizes the simulation of air intake and exhaust of an engine through the jet action of high-pressure gas introduced into the nacelle. The drop pressure ratio of the outlet of the injection type nacelle is an important control parameter when the jet type nacelle works, and the working state of an engine is basically simulated by simulating the drop pressure ratio.
In the wind tunnel test, the pressure drop ratio is given for a certain test state, and the relevant equipment of the high-pressure air supply system is controlled to achieve the required simulated pressure drop ratio. The general control method is to give a pipeline flow, roughly estimate the pipeline flow regulating quantity by measuring the outlet pressure drop ratio of the injection type nacelle, and repeatedly regulate to finally make the outlet pressure drop ratio of the injection type nacelle reach a given value. The control method has low realization efficiency and low control precision of flow and pressure drop ratio.
Disclosure of Invention
The invention aims to provide a real-time feedback control method for the exit pressure ratio of an injection type nacelle based on the above situation, which can carry out real-time feedback and control on the exit pressure ratio of the injection type nacelle and realize that the pressure ratio is used as a direct input parameter of a test.
In order to achieve the purpose, the invention adopts the following technical scheme:
a real-time feedback control method for the pressure drop ratio of an ejection type nacelle outlet comprises the following steps:
the drop pressure ratio of the outlet of the injection type nacelle is controlled by adopting an outer ring, the drop pressure ratio required to be simulated is given, the drop pressure ratio is corrected according to the test Mach number, the required given pipeline flow is obtained by interpolation according to the flow drop pressure ratio calibration characteristic curve, the actual drop pressure ratio fed back by the outlet of the injection type nacelle under the given pipeline flow is compared with the given drop pressure ratio to obtain the drop pressure ratio compensation quantity, and the positive compensation quantity of the flow is obtained through the flow drop pressure ratio calibration characteristic curve;
the pipeline flow regulation adopts inner loop control, corresponding flow is obtained according to a given flow control main pipeline digital valve position obtained by outer loop control, negative feedback is carried out on the given flow according to actual flow measured by a flow meter positioned in front of the injection type nacelle, and the given high-pressure air supply system flow required by the injection type nacelle outlet pressure drop ratio reaching the given pressure drop ratio is obtained.
In the technical scheme, the control method needs to obtain a correction relation between the drop pressure ratio of the outlet of the injection type nacelle and the test Mach number and a calibration characteristic curve of the drop pressure ratio and the air supply flow through a test.
In the above technical solution, when the average error of the continuous flow rate for 5s is higher than the configuration accuracy in the inner loop control, the system is determined to be in a stable state.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
1. the method takes the pressure drop ratio of an outlet of an injection type nacelle as a control target quantity, realizes the control of the target quantity by controlling the air supply flow in the control process, and takes a digital valve and a needle valve in a flow control unit (MCU) as control objects. On the premise that the digital valve controls the total flow, the flow is regulated and distributed by controlling the valve position of a needle valve of the flow control unit, so that the test control target amount is respectively controlled;
2. the method comprises the steps of calculating total flow on the premise of giving a test control target flow according to calibration and wind tunnel debugging results, enabling the total flow of air supply to be close to a given value by controlling a digital valve, carrying out real-time feedback regulation on the total flow by measuring the target flow, and judging stably by a system when a target pressure drop ratio reaches a given control precision (the average error of continuous 5s is lower than configuration precision);
3. the method carries out real-time monitoring on key parameters in the operation process and mainly comprises the following steps: the monitoring parameters are judged abnormally to realize abnormal alarming and emergency stopping by the pressure of a high-pressure air source, the pressure behind a high-pressure reducing valve, the pressure behind a digital valve, the temperature behind a heating system, the test control target quantity, the work of each spray pipe of the digital valve, the internal pressure and temperature state of a flowmeter and the like;
4. the method can realize that the control precision of the gas supply flow is better than 0.3 percent, the control precision of the pressure drop ratio is better than 0.01, the automatic real-time quick adjustment of the pressure drop ratio during the test is realized, the pressure drop ratio can be set as the input condition during the test, and the setting and control flow of the jet flow state during the jet flow test is greatly simplified.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
FIG. 1 is a schematic diagram of the scheme of the present invention;
wherein: the broken line frame is internally provided with a real-time feedback control flow of the pressure drop ratio, and the outside of the broken line frame is provided with high-pressure gas supply system hardware and an injection type nacelle.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
As shown in fig. 1, firstly, a corrected relationship between the exit pressure drop ratio of the jet type nacelle and the test mach number and a calibration characteristic curve of the pressure drop ratio and the supply air flow are obtained through tests.
And when the drop pressure ratio required to be simulated is given, correcting the drop pressure ratio according to the test Mach number, and then carrying out interpolation according to the flow drop pressure ratio calibration characteristic curve to obtain the required given pipeline flow. And comparing the actual falling pressure ratio fed back by the outlet of the injection type nacelle at the given pipeline flow with the given falling pressure ratio to obtain the compensation quantity of the falling pressure ratio, and obtaining the positive compensation quantity of the flow through the calibration characteristic curve of the flow falling pressure ratio.
The flow regulation of the main pipeline of the high-pressure gas supply system adopts inner loop control, corresponding flow is obtained according to a given flow control main pipeline digital valve position obtained by outer loop control, and negative feedback is carried out on the given flow according to actual flow measured by a flow meter positioned in front of the injection type nacelle. When the average error of the continuous flow for 5s is higher than the configuration precision, the system judges stably. Finally, the flow of the high-pressure air supply system required by the ejection type nacelle outlet pressure drop ratio reaching the given pressure drop ratio is obtained.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.
Claims (3)
1. A real-time feedback control method for the pressure drop ratio of an ejection type nacelle outlet is characterized by comprising the following steps:
the drop pressure ratio of the outlet of the injection type nacelle is controlled by adopting an outer ring, the drop pressure ratio required to be simulated is given, the drop pressure ratio is corrected according to the test Mach number, the required given pipeline flow is obtained by interpolation according to the flow drop pressure ratio calibration characteristic curve, the actual drop pressure ratio fed back by the outlet of the injection type nacelle under the given pipeline flow is compared with the given drop pressure ratio to obtain the drop pressure ratio compensation quantity, and the flow compensation quantity is obtained through the flow drop pressure ratio calibration characteristic curve;
the pipeline flow regulation adopts inner loop control, corresponding flow is obtained according to a given flow control main pipeline digital valve position obtained by outer loop control, negative feedback is carried out on the given flow according to actual flow measured by a flow meter positioned in front of the injection type nacelle, and the given high-pressure air supply system flow required by the injection type nacelle outlet pressure drop ratio reaching the given pressure drop ratio is obtained.
2. The real-time feedback control method for the exit pressure drop ratio of the injection type nacelle according to claim 1, wherein the control method comprises the steps of obtaining a correction relation between the exit pressure drop ratio of the injection type nacelle and a test Mach number and a calibration characteristic curve of the pressure drop ratio and an air supply flow through a test.
3. The method for real-time feedback control of the exit pressure drop ratio of the injection type nacelle according to claim 1, wherein in the inner-loop control, when the average error of 5s of continuous flow is higher than the configuration precision, the system is determined to be in a stable state.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811079624.1A CN110907120B (en) | 2018-09-17 | 2018-09-17 | Real-time feedback control method for pressure drop ratio of outlet of injection type nacelle |
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| CN201811079624.1A CN110907120B (en) | 2018-09-17 | 2018-09-17 | Real-time feedback control method for pressure drop ratio of outlet of injection type nacelle |
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| CN110907120B true CN110907120B (en) | 2021-05-11 |
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| CN114136643B (en) * | 2021-10-20 | 2024-01-09 | 中国航发四川燃气涡轮研究院 | Aeroengine air flow measuring point layout method |
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| JPH11337440A (en) * | 1998-05-27 | 1999-12-10 | Mitsubishi Heavy Ind Ltd | Method for predicting region generating white smoke |
| CN103267644A (en) * | 2012-06-28 | 2013-08-28 | 沈阳黎明航空发动机(集团)有限责任公司 | Engine performance simulation method |
| CN106596036A (en) * | 2016-12-14 | 2017-04-26 | 中国航天空气动力技术研究院 | Low-speed wind tunnel thrust vector test's stagnation pressure measuring device |
| CN106951634A (en) * | 2017-03-20 | 2017-07-14 | 南京航空航天大学 | A kind of aero-engine robust tracking controller method for designing |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9327202B2 (en) * | 2014-06-30 | 2016-05-03 | Airborne America, Inc. | Wind tunnel design with expanding corners |
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| JPH11337440A (en) * | 1998-05-27 | 1999-12-10 | Mitsubishi Heavy Ind Ltd | Method for predicting region generating white smoke |
| CN103267644A (en) * | 2012-06-28 | 2013-08-28 | 沈阳黎明航空发动机(集团)有限责任公司 | Engine performance simulation method |
| CN106596036A (en) * | 2016-12-14 | 2017-04-26 | 中国航天空气动力技术研究院 | Low-speed wind tunnel thrust vector test's stagnation pressure measuring device |
| CN106951634A (en) * | 2017-03-20 | 2017-07-14 | 南京航空航天大学 | A kind of aero-engine robust tracking controller method for designing |
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