Aero-engine fuel pump low-temperature test system and test method
An aero-engine and low-temperature test technology, which is applied in the direction of engine testing, jet engine testing, gas turbine engine testing, etc., can solve problems such as damage to seals, limited low-temperature tolerance, and shortened life, so as to improve service life and reduce Equipment failure rate, the effect of flexible use
Pending Publication Date: 2020-08-28
NANJING VOCATIONAL UNIV OF IND TECH
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Problems solved by technology
However, due to the limited low-temperature tolerance of industrial pumps, valves and other components commonly used in the test system, long-term pumping of low-temperature media will cause problems such as damage to seals and shortened life.
Method used
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[0025] In order to make the technical means, creative features, goals and effects achieved by the present invention easy to understand, the present invention will be further described below in conjunction with specific embodiments.
[0026] Such as Figure 1 to Figure 2 As shown, an aero-engine fuel pump low-temperature test system includes a fuel supply tank 1, a fuel supply pump 2, an accumulator 3, a filter 4, a heat exchanger 5, a heat transfer oil cooling and temperature control unit 7, a fuel pump 12 to be tested and Controller 15; the oil supply tank 1 is connected to the heat transfer oil cooling and temperature control unit 7 through the oil supply pump 2, accumulator 3, filter 4 and heat exchanger 5 in sequence, and the heat transfer oil cooling and temperature control unit 7 is passed through the exchange The heater 5 is connected to the fuel pump 12 to be tested, and the fuel pump 12 to be tested is directly connected to the fuel supply tank 1;
[0027] A self-ope...
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The invention discloses an aero-engine fuel pump low-temperature test system and an aero-engine fuel pump low-temperature test method and relates to the technical field of aero-engine tests. The system comprises an oil supply tank, an oil supply pump, an energy accumulator, a filter, a heat exchanger, a conduction oil refrigeration temperature control unit, a to-be-tested fuel pump and a controller. The oil supply tank is connected with the heat conduction oil refrigeration temperature control unit through the oil supply pump, the energy accumulator, the filter and the heat exchanger in sequence. The heat conduction oil refrigeration temperature control unit is connected with a fuel pump to be tested through a heat exchanger; the fuel pump to be tested is directly connected with the fuel supply tank, by changing the low-temperature test process and the temperature control scheme, it is avoided that an industrial pump, a valve and other parts used by the test equipment tolerate the extreme low temperature for a long time in the low-temperature test process, the service life of the test equipment can be prolonged, and the equipment failure rate is reduced.
Description
technical field [0001] The invention relates to the technical field of aero-engine testing, in particular to an aero-engine fuel pump low-temperature testing system and an experimental method. Background technique [0002] When the aircraft is flying at high altitude, the environment is in a low temperature state (11O00m altitude temperature is about -56°C), and the low temperature will have a harmful effect on the fuel system and components. Therefore, components such as aero-engine fuel pumps need to be tested at low temperature during the stages of design finalization and mass production to verify the reliability of the product under extreme low temperature conditions. The current low-temperature test system often cools the fuel in the fuel tank to the required temperature first, and then sends the low-temperature fuel in the fuel tank to the fuel pump to be tested through an industrial pump. However, due to the limited low-temperature tolerance of industrial pumps, valv...
Claims
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IPC IPC(8): G01M15/14G01M15/02G05D23/19
CPCG01M15/02G01M15/14G05D23/19
Inventor 刘龙龙
Owner NANJING VOCATIONAL UNIV OF IND TECH