Arrangement structure of high pressure turbine cooling air passage for aero-engine

Abstract

The invention provides a flow channel arrangement structure of aero-engine high-pressure turbine cooling air. The flow channel arrangement structure comprises a plurality of front air guiding pipes and a plurality of rear air guiding pipes, wherein the front air guiding pipes are arranged around the outer side of a case of a primary turbine in an engine outer duct and used for guiding the cooling air, and the rear air guiding pipes are arranged around the outer side of a case of a secondary turbine in the engine outer duct and used for guiding the cooling air. The inlet ends of the front air guiding pipes are mounted in mounting holes of a front mounting seat of the case of the primary turbine, the outlet ends of the front air guiding pipes are mounted in mounting holes of a rear mounting edge of the primary case, and inlets of the front air guiding pipes are communicated with an air gathering cavity of a primary turbine guider. The outlet ends of the rear air guiding pipes are mounted in mounting holes of a rear mounting seat of the case of the secondary turbine, the inlet ends of the rear air guiding pipes are mounted in mounting holes of a front mounting edge of the secondary case, and outlets of the rear air guiding pipes are communicated with an air gathering cavity of a secondary turbine guider. Inlets of the rear air guiding pipes are oppositely communicated with outlets of the front air guiding pipes. According to the flow channel arrangement structure, an air guiding mode and structure can be simplified, the temperature of the cooling air is lowered, and therefore the heat exchange efficiency and the cooling efficiency are improved.

Description

technical field [0001] The invention relates to a component structure of an aero-engine turbine cooling system, in particular to an arrangement structure of an aero-engine high-pressure turbine cooling air passage. Background technique [0002] In the design of aero-engine turbine cooling components, on the premise of ensuring the overall performance of the engine, the operating temperature of the components should be reduced as much as possible to ensure that all parts can work within the allowable temperature range of the material, so as to ensure the effectiveness of the structure, function and life. Design requirements. In addition, the weight of components should be reduced as much as possible to reduce the load of the aircraft itself. The high-pressure turbine of a certain type of engine is composed of a first-stage turbine and a second-stage turbine. The guide blades of the first-stage turbine and the second-stage turbine are cooled by hollow forced convection, and t...

AI Technical Summary

Problems solved by technology

The conventional way of introducing air through the annular space of the double-layer casing has obvious deficiencies in its air path structure: 1. Double-layer structure casing, the casing structure is complex and heavy; 2. There are many connection structures, and the outer layer The casing is mostly a sheet metal component, with large processing deformation and complicated assembly; 3. Although the secondary air flow can exchange heat with the outer duct through the outer casing, it also absorbs heat from the surface of the inner casing, so the cooling airflow cools down low effect

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