A sealed air supply device for the experiment of transonic turbine plane cascade

Abstract

The invention discloses a sealed air supply device for the experiment of transonic turbine plane blade cascade. The end wall of the wind tunnel is provided with the transonic turbine blade cascade. The top of the air supply cavity is provided with a sealing air outlet extending perpendicular to the mainstream direction and located upstream of the leading edge of the transonic turbine cascade. It enters the main flow channel of the wind tunnel and interacts with the main flow gas therein. Utilizing the characteristic that the cold air velocity direction in the sealed air supply chamber is tangent to the circumferential direction of the transonic turbine blade cascade, the circumferential velocity of the sealed flow can be reproduced without rotating parts, and at the same time, the flow rate of the sealed flow and the sealed flow can be changed independently. The effect of the circumferential velocity of the tight flow can fully simulate the sealing jet conditions required for the transonic turbine cascade test, reproduce the characteristics of the sealing flow inside the real turbine, and easily obtain a more accurate three-dimensional flow field structure.

Description

technical field [0001] The invention belongs to the field of aero-engine / gas turbine transonic turbine plane cascade experiments, and relates to a sealed gas supply device used for transonic turbine plane cascade experiments. The present invention utilizes the characteristic that the velocity direction of the cold air in the air supply chamber of the seal is tangent to the circumferential direction of the transonic turbine cascade, so that the circumferential velocity of the seal flow can be reproduced without the rotation of parts, and at the same time, the seal flow can be changed independently The effect of the flow rate and the peripheral velocity of the sealing flow can fully simulate the sealing jet flow conditions required for the transonic turbine flat cascade experiment, which can greatly reduce the cost of the turbine sealing experiment. Background technique [0002] In modern advanced aero-engines, a large amount of cooling air and sealing air are required to ensu...

AI Technical Summary

Problems solved by technology

Most of the existing turbine sealing experiments are carried out on the turbine-level component test bench or the low-speed large-scale rotating test bench. Although the full-stage experiment on the turbine can obtain the real influence characteristics of the seal flow on the mainstream, the full-stage experiment has no effect on The requirements for laboratory equipment and instruments are high, the cost of experiments is high, and it is difficult to achieve fine measurement of the flow field inside the turbine channel

In comparison, the planar cascade can conveniently, quickly and economically study some basic flow phenomena in the turbine, and has the characteristics of low cost, easy measurement, and convenient controllability. It has always been an important means for people to study the internal flow of turbomachinery, but The sealed outflow inside the real engine is a complex rotating flow with large axial, radial and circumferential velocities. However, due to the limitation that the planar cascade does not have rotating parts, it is difficult to reproduce the real flow in the planar cascade experiment. The jet conditions of the engine turbine seal flow, especially the circumferential velocity of the seal flow, are difficult to simulate, which severely restricts the understanding of the interaction mechanism between the real turbine seal flow and the mainstream

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