Test system and control method for flow control of aero-engine particle separator
An aero-engine and flow control technology, applied in general control systems, control/regulation systems, testing/monitoring control systems, etc., can solve the problem that the flow control accuracy and adjustment speed cannot be guaranteed, the flow adjustment is not timely, and the test results are comparable. problems such as poor performance, to achieve the effect of ensuring flow control accuracy and adjustment rate, and stable and rapid control
Active Publication Date: 2019-12-20
AECC HUNAN AVIATION POWERPLANT RES INST
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Problems solved by technology
[0003] The invention provides a test run system and control method for the flow control of an aero-engine particle separator to solve the problems caused by the untimely flow adjustment, flow control accuracy and adjustment speed in the existing aero-engine test run system. Technical problems such as poor comparability of results and high risk of damage to test pieces
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[0035] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.
[0036] The preferred embodiment of the present invention provides a kind of test run system of flow control of aeroengine particle separator, with reference to figure 2 The test run system of this embodiment includes a test flow channel 1, the test flow channel 1 is provided with an inlet 11 for connecting the test piece 2 to be tested, an outlet 12 for discharging the test air flow, and a fan for driving the air flow in the test flow channel 1 3. It also includes a data acquisition system for collecting the working state corresponding to the test flow channel 1. 4. A control system for controlling the working state of the fan 3. The control system includes a frequency converter 7 connected to...
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The invention discloses a test run system and a control method for flow control of an aero-engine particle separator. The test run system includes a test flow channel. The test flow channel is provided with an inlet for connecting the sample to be tested, an outlet for discharging the test air flow and a fan to drive the air flow in the test flow channel. The test flow channel also includes a datacollection system for collecting the corresponding working state of the test flow channel and a control system for controlling the working state of the fan. The control system comprises a frequency converter connected with the control end of the fan and a programmable controller connected with the frequency converter; a communication connection of an upper computer of LABVIEW software, used for closed loop control of flow in test flow channel, is arranged between the programmable controller and the data collection system. According to the invention, closed loop control is realized by a data collection system, a LABVIEW upper computer, a programmable controller and a frequency converter, so that the flow control accuracy and the regulation rate of the aero-engine test system are guaranteed.
Description
technical field [0001] The invention relates to the field of aero-engine test run, in particular to a test run system and control method for flow control of an aero-engine particle separator. Background technique [0002] In order to prevent the sand and gravel on the ground from being inhaled by the engine with the airflow and damage the compressor blades or other mechanical parts, a particle separator is added before the engine inlet. Therefore, the flow rate of the particle separator needs to be controlled during the engine test to detect particle separation. device performance. In the prior art, refer to figure 1 , In the flow control of IPS (Particle Separator) of aviation test bench, open-loop control is usually adopted, WINCC upper computer 1' or touch screen is the man-machine interface, PLC controller 2' is the lower computer, and PLC controller 2' controls the test The opening of the valve 3' is adjusted on the pipeline to further control the flow of the flow cha...
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IPC IPC(8): G05B23/02
CPCG05B23/0213G05B2219/24065
Inventor 李伟蔡衍支明陈珩
Owner AECC HUNAN AVIATION POWERPLANT RES INST