Composite impact gas film cooling wall type flame stabilizer and combustion chamber

Abstract

The invention discloses a composite impact gas film cooling wall type flame stabilizer and a combustion chamber. The wall type flame stabilizer comprises a deflector extending horizontally, a front air-cooling inclined plate, an air-cooling flat plate, a rear air-cooling inclined plate and an oil cooling splitter plate arranged at the rear end of the rear air-cooling inclined plate. The front air-cooling inclined plate, the air-cooling flat plate and the rear air-cooling inclined plate are hollow to form air-cooling cavities which communicate with one another, and each air-cooling cavity is divided into a first cavity and a second cavity located below the first cavity; a fuel oil guide pipe is arranged on the oil cooling splitter plate; and the oil cooling splitter plate is hollow to form an oil cooling evaporation cavity. Impact cooling and gas film cooling are combined in the cavity area of the wall type stabilizer, oil cooling is used in the splitter plate of flame wake radiation of the wall type stabilizer, the temperature of the hot side wall face of the stabilizer is effectively reduced, and the service life of the stabilizer in high-temperature fuel gas is prolonged.

Description

technical field [0001] The invention relates to the technical field of aerodynamic propulsion systems, in particular to a compound impingement gas film cooling wall flame stabilizer and a combustion chamber. Background technique [0002] With the continuous improvement of modern advanced aircraft's requirements for maximum engine thrust and maneuverability, the temperature rise requirements of thrust enhancement devices are also gradually increasing, which brings new challenges to the design of key hot-end components. At present, the conventional materials used in the hot end parts of aero-engines are high-temperature alloys, and their temperature resistance limit is below 1200-1300K. The temperature of the wall surface in the high-temperature flame will be much higher than this temperature, and the thermal protection design of the hot side wall surface of the flame stabilizer must also become a key part. In addition, the inlet velocity of advanced aeroengine afterburner an...

AI Technical Summary

Problems solved by technology

[0004] Purpose of the invention: The present invention provides a composite impingement film cooling wall flame stabilizer, which can reduce the temperature of all hot side walls in contact with the flame, realize the active control of the cooling effect and the flame of the concave cavity, and obtain better ignition at the same time and flame stability, which solves the difficulty of ignition and flame stabilization in high-temperature and high-speed incoming flow, and the temperature of the hot side wall surface in direct contact with the flame exceeds the temperature resistance limit of conventional high-temperature alloys and requires thermal protection, ensuring the work of the flame stabilizer reliability

Images