Flow test system suitable for supersonic/hypersonic channel and test method

A flow test and hypersonic technology, which is applied in the testing of machines/structural components, volume/mass flow generated by mechanical effects, and detection of fluid flow by measuring differential pressure, can solve problems such as blockage of supersonic flow channels, and achieve pressure measurement Fewer points, wide Mach number range, and improved measurement accuracy

Active Publication Date: 2015-12-16
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS +1
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Problems solved by technology

However, Venturi flowmeters can only measure the flow of subsonic fluids. How to extend the measurement range of Venturi flowmet

Method used

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  • Flow test system suitable for supersonic/hypersonic channel and test method
  • Flow test system suitable for supersonic/hypersonic channel and test method
  • Flow test system suitable for supersonic/hypersonic channel and test method

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Embodiment Construction

[0019] See figure 1 The invention discloses a flow measurement system suitable for supersonic / hypersonic flow channel. It is composed of Venturi flowmeter, throttling module and rectifier module. The Venturi flowmeter (3) is a standard part produced and calibrated according to the national standard GB / T2624-2006; the throttle module is composed of a plugging cone (5) and a linear stepping motor (6) The rectifier module is composed of the front rectifier section (1) and the rear equal straight rectifier section (4); the entire flow test system, in accordance with the front rectifier section (1), Venturi flowmeter (3), rear rectifier section (4) ), the throttling module is connected through the flange in turn, and is connected to the experimental model through the front rectification section (1); the front rectification section is composed of a diffuser and an equal straight pipeline, and a rectifier ( 2) To further break up the large-scale vortex formed by the upstream shock wa...

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Abstract

The invention discloses a flow test system suitable for supersonic/hypersonic channel, which mainly comprises a Venturi tube, a throttling module and a rectification module. By adjusting the outlet area of the throttling module, a shock wave structure inside the pipeline is formed; the shock wave and the designed diffuser are used to decelerate the supersonic/ hypersonicin flow fully to a subsonic speed so as to satisfy the requirement of the Venturi tube to the inlet speed and Reynolds number. The system has the advantages of simple structure, small size, rapid response speed and high measurement precision; the throttling module adjusts the throttling degree according to pipe flow speed; the suitable Mach number scope is side; the demanded pressure measuring points are few; additional obstruction to the experiment channel is avoided compared to traditional flow test methods like * shaped rake; the throttling characteristic experiment of an air intake duct can be carried out at the same time; test cost is greatly saved; air-flow non-uniformity inside the channel is not sensitive; the system is particularly suitable for measuring flow of complex inner flow apparatuses like air intake ducts and diffusers whose inflow are supersonic/hypersonic.

Description

Technical field [0001] The invention relates to the field of aerodynamic experiment testing, in particular to a flow measurement method for inlets, diffusers and other internal flow devices operating in the supersonic / hypersonic range. Background technique [0002] For the intake duct and diffuser, the flow rate reflects its flow capture ability and will directly affect the thrust of the engine. Therefore, it is very important to accurately measure the flow rate. Due to the short running time of the supersonic / hypersonic wind tunnel experiment, the flowmeter must have fast response characteristics. On the other hand, the cross section of the outer contour of the flowmeter should not be too large, otherwise it will easily affect the establishment of the supersonic flow field of the wind tunnel itself. The size of the flow channel in the flowmeter should not be too small, and there can be no large-scale obstacles, otherwise it will affect the establishment of the supersonic flow fi...

Claims

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Application Information

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IPC IPC(8): G01M9/02G01M9/06G01F1/44
Inventor 谭慧俊黄河峡程林袁永青孙姝李光胜
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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