A low Reynolds number plane cascade high-altitude flow simulation device

Abstract

The invention discloses a high-altitude flow simulation device for a low Reynolds number plane cascade. The device sequentially includes an intake gate valve group, an intake fast valve group, an intake pressure regulating valve group, a straight pipe section, an expansion section, a stable section, a contraction section, a test body, an exhaust restrictor, and a three-stage ejector along the airflow direction. The test body and the small hole exhaust section, the test model of the turbine cascade or the test model of the compressor cascade is installed in the test body, and the test body is connected with the vacuum suction component and the secondary flow component. The intake pressure regulating valve group controls the total pressure in the stable section, the suction component controls the static pressure and the boundary layer before the cascade test piece; the three-stage ejector and the exhaust restrictor control the supersonic or subsonic test body. Chamber back pressure to achieve Reynolds number adjustment, especially high-altitude low Reynolds number adjustment. The device can realize flow simulation at sub-transonic speed and wide Reynolds number range, and is suitable for carrying out experimental research and technical verification of aerodynamic performance of aeroengine turbine plane cascade.

Description

technical field [0001] The invention belongs to the field of aero-engine basic research test equipment, and in particular relates to a high-altitude flow simulation device for low Reynolds number plane blade cascades. Background technique [0002] Aviation turbines (including fans / compressors and turbines) and gas turbines are key components for maintaining thermal cycles and generating thrust, and the aerodynamic shape of their rotor / stator blades determines the aerodynamic performance of aviation turbines and gas turbines. In order to design high-performance aerojet engines and gas turbines, it is necessary to study the design method and flow characteristics of the turbine at the cascade (two-dimensional airfoil) level. In order to conduct experimental research on the aerodynamic characteristics of cascade passage flow under real flight conditions on the ground, it is necessary to build ground equipment that can simulate parameters such as the Mach number and Reynolds numb...

AI Technical Summary

Problems solved by technology

[0003] At present, the flow simulation devices commonly used in aero-engine turbine (including fan / compressor and turbine) and gas turbine blade cascade tests at home and abroad have the following disadvantages: First, multiple sets of single-point Mach numbers are generally used when simulating supersonic flow The solid-state nozzle requires frequent replacement of the nozzle when changing the flow state, which is extremely inconvenient and inefficient; second, there is no chamber structure and no back pressure regulating valve in the test section, and the vacuum suction method is generally used for Reynolds number simulation. The suction equipment is complicated, the efficiency is low, the sealing guarantee is difficult, the Reynolds number simulation method is single, the simulation range is narrow, and the high-altitude simulation capability is insufficient; the third is the secondary flow system with a single function, and only has the heat and mass transfer test capability of one medium air flow; The flow simulation device generally adopts the open jet structure, the exhaust collector is simple, the exhaust collection effect is poor, and the noise pollution is large

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