Air inlet system of ultrasonic engine testing platform

An air intake system, supersonic technology, applied in the field of test measurement, can solve the problems of no mature technology, high cost, long test period, etc., and achieve the effect of high simulation accuracy and simple method

Pending Publication Date: 2019-01-29
BEIJING AEROSPACE SANFA HIGH TECH
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Problems solved by technology

With the maturity of the engine, the application of the supersonic engine is becoming more and more extensive. On this basis, the engine intake system needs to simulate the supersonic speed of the supersonic engine when it is used for the supersonic engine of the aircraft, especially the unmanned aerial vehicle, and the ground test of the en...

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  • Air inlet system of ultrasonic engine testing platform
  • Air inlet system of ultrasonic engine testing platform
  • Air inlet system of ultrasonic engine testing platform

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Embodiment Construction

[0022] In describing the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", " Back", "Left", "Right", "Vertical", "Horizontal", "Top", "Bottom", "Inner", "Outer", "Clockwise", "Counterclockwise", "Axial", The orientation or positional relationship indicated by "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying the referred device or element Must be in a particular orientation, be constructed in a particular orientation, and operate in a particular orientation, and therefore should not be construed as limiting the invention. In addition, the features defined as "first" and "second" may explicitly or implicitly include one or more of these features. In the description of the prese...

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Abstract

An air inlet system of an ultrasonic engine testing platform comprises a supply source, a temperature simulation unit, a simulation cabin and an ultrasonic jet pipe. The supply source comprises a fueloil supply source, an oxygen supply source an engine air inlet supply source, and an alcohol supply source; the temperature simulation unit comprises a tube and a casing, the tube is positioned in the casing, the internal of the tube serves as a first medium channel, and a space between the outer wall of the tube and the inner wall of the casing forms a second medium channel; a tested engine is positioned in the simulation cabin; and the ultrasonic jet pipe comprises an inlet unidiameter segment, a subsonic speed convergence segment, an initial ultrasonic expansion segment and an ultrasonic expansion segment which are fixedly connected in the same axis successively. According to the air inlet system of the ultrasonic engine testing platform, the Laval type ultrasonic jet pipe is arrangedbetween the temperature simulation unit and the engine air inlet, so that the ultrasonic air inlet state of the ultrasonic engine is simulated during ultrasonic engine and engine ground test.

Description

technical field [0001] The invention relates to the technical field of test and measurement, in particular to an air intake system of a supersonic engine test bench. Background technique [0002] Before the test flight of the aero-engine, a high-altitude simulation test needs to be done on the ground. During the engine test, a set of intake air parameters are required, including intake air total pressure, intake air flow rate, intake oxygen content, intake air total temperature, and engine fuel supply. The oil quantity is called the intake state point, and when it reaches the set value and stabilizes at the same time, record its performance and parameters or evaluate its performance. With the maturity of the engine, the application of the supersonic engine is becoming more and more extensive. On this basis, the engine intake system needs to simulate the supersonic speed of the supersonic engine when it is used for the supersonic engine of the aircraft, especially the unmanne...

Claims

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Application Information

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IPC IPC(8): G01M15/02
CPCG01M15/02
Inventor 王文彬康宏博李强徐元元
Owner BEIJING AEROSPACE SANFA HIGH TECH
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