A flow test system and test method suitable for supersonic/hypersonic flow channels
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: 2016-08-17
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 flowmeters to supersonic speeds without blocking the supersonic flow channels is the key problem to be solved by the present invention.
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[0019] see figure 1 , The invention discloses a flow measurement system suitable for supersonic / hypersonic flow channels. It consists of Venturi flowmeter, throttling module and rectification 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 blocking cone (5) and a linear stepping motor (6) ; The rectification module is made up of front rectification section (1) and rear equal straight rectification section (4); whole flow test system, according to front rectification section (1), Venturi flowmeter (3), rear rectification section (4) ), the throttling modules are connected by flanges in turn, and are connected to the experimental model through the front rectification section (1); the front rectification section is composed of a diffuser and a straight pipeline, and a rectifier ( 2), to further break up the large-scale vortex formed by the separation induced by th...
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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 experiments and tests, in particular to a flow measurement method for internal flow devices such as air inlets and diffusers working in the supersonic / hypersonic range. Background technique [0002] For the intake port and diffuser, the flow rate reflects its flow capture capability and will directly affect the thrust of the engine, so it is very important to measure the flow rate accurately. Since the running time of the supersonic / hypersonic wind tunnel experiment is very short, the flowmeter must have fast response characteristics. On the other hand, the outer profile cross-section 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 should be no large-scale obstacles, otherwise it will affect the establishment of the supersoni...
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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