Turbine disc cavity structure with closely-sealing and cooling guide plate

Abstract

The invention discloses a turbine disc cavity structure with a closely-sealing and cooling guide plate. The turbine disc cavity structure comprises a large bent pipe, a turbine guider, the guide plate, a turbine disc, a turbine blade and a bearing seat installing edge; the large bent pipe, the turbine guider and the guide plate are fixed to the bearing seat installing edge through screws to form a first cold air cavity, a second cold air cavity, a third cold air cavity, a fourth cold air cavity, a fifth cold air cavity, a sixth cold air cavity and a seven cold air cavity. According to the turbine disc cavity structure, by designing the step blade type closely-sealing structure and circular throttle holes on the portions, with the different radiuses, of the guide plate and optimizing the profile surface of the guide plate, the amount of cooling and closely-sealing gas entering the different portions of a turbine disc cavity can be reasonably allocated, the circulating area of the cooling gas in the turbine disc cavity is greatly decreased, the cooling gas approximately flows along the surface of a turbine disc, therefore, the utilization efficiency and the cooling effect of the cooling gas are greatly improved, and backward fuel gas flowing can be effectively prevented.

Description

technical field [0001] The invention relates to the field of aero-engines, and relates to a turbine disk cavity structure with sealing and cooling deflectors, and is especially suitable for the front cavity of the turbine disk of an aero-engine. Background technique [0002] As the thrust-to-weight ratio of aero-engines continues to increase, its hot-end components are subjected to higher temperatures and greater loads. The temperature before the turbine of the pre-researched thrust-to-weight ratio 10 engine is about 1850-1950°C. Turbine disk is a key part of aero-engine, it bears severe thermal load and mechanical load, and the working conditions are very harsh. In order to ensure the safe and reliable operation of the turbine disk within the required lifespan, under the condition of reasonable material selection, the cooling gas drawn from the main channel of the compressor and the two streams of the combustion chamber is usually used to cool the turbine disk through the ...

AI Technical Summary

Problems solved by technology

However, due to the large space in the turbine disk cavity, the turbine disk is irregularly folded, and the gas flow rate at the folded corner is very slow, which is easy to form a relatively dead angle for cooling, resulting in poor cooling effect and low utilization rate of cooling gas

In addition, due to the frictional pump effect or the interference of rotating and stationary blades, gas intrusion will occur at the sealing structure of the turbine disk rim

The intrusion of the main gas will deteriorate the cooling of the rotor, which will greatly damage the safe and reliable operation of the engine

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