Gas guide structure and flow guide groove of gas compressor

Abstract

The invention belongs to the technical field of gas guide design of aircraft engines, and particularly relates to a gas guide structure of a gas compressor. The gas guide structure comprises a statorouter ring, a stator casing and a gas guide pipe, wherein the stator outer ring is provided with a gas guide hole, the inner side of the stator outer ring is provided with a flow guide groove, one endof the flow guide groove extends to the gas guide hole, the other end of the flow guide groove obliquely extends towards an incoming flow direction of an airflow channel in the stator outer ring, thestator outer ring is arranged in the stator casing, an air collection cavity communicating with the gas guide hole is formed between the stator casing and the stator outer ring, an air outlet hole communicating with the air collection cavity is formed in the stator casing, and an inlet of the gas guide pipe communicates with the air outlet hole. In addition, the invention further relates to a gascompressor flow guide groove which has all characteristics of the flow guide groove in the gas compressor gas guide structure.

Description

technical field [0001] The application belongs to the technical field of aircraft engine bleed air design, and in particular relates to a compressor bleed air structure and a drainage groove thereof. Background technique [0002] Air conditioning and pressurization in the cockpit, thermal anti-icing of wings, and cooling of hot-end parts of the engine often require air sources of appropriate temperature and pressure. The outer ring of the stator is located between two adjacent stator blades, and a circular or special-shaped air-introduction hole is provided, through which the airflow in the gas flow channel in the stator outer ring of the compressor is introduced to the space between the stator outer ring and the stator casing. Afterwards, the airflow entering the air collection chamber is led to the relevant parts of the aircraft cockpit, wing, and engine hot end parts through the bleed air pipe, so as to serve as air conditioning and pressurization of the aircraft cockpit,...

AI Technical Summary

Problems solved by technology

[0002] Air conditioning and pressurization in the cockpit, thermal anti-icing of wings, and cooling of hot-end parts of the engine often require an air source of appropriate temperature and pressure. Currently, this air source is mostly obtained from the engine compressor, and most of the solutions are in the compressor. The outer ring of the stator is located between two adjacent stator blades, and a circular or special-shaped air-introduction hole is provided, through which the airflow in the gas flow channel in the stator outer ring of the compressor is introduced to the space between the stator outer ring and the stator casing. Afterwards, the airflow entering the air collection chamber is led to the relevant parts of the aircraft cockpit, wing, and engine hot end parts through the bleed pipe, so as to serve as air conditioning and pressurization of the aircraft cabin, wing thermal anti-icing, engine The air source for cooling the hot end parts. In this technical scheme, when the air flow in the gas flow channel in the outer ring of the stator enters the gas collection cavity from the gas flow channel in the outer ring of the stator through circular or special-shaped air holes, there will usually be a large gap. The airflow turning angle increases the loss of airflow flow, which easily leads to insufficient air supply flow or pressure to the relevant parts of the aircraft cockpit, wings, and engine hot-end components, and it is difficult to meet the air conditioning and pressurization of the aircraft cockpit, wing thermal anti-icing, engine Cooling of hot-end components is required, which may lead to dangerous accidents in severe cases

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