Double-wall turbine guide blade with small air entraining amount

Abstract

The invention discloses a double-wall turbine guide blade with small air entrainment amount, and belongs to the technical field of aero-engines. The guide blade comprises a blade front edge, a middle chord blade basin, a blade back middle chord and a blade tail edge, the blade front edge is subjected to double-layer partition plate impact and film cooling, the middle chord blade basin and the blade back middle chord are subjected to double-wall impact and film cooling, and the blade tail edge is cooled by a radial turbulent flow column. The technology can be applied to the design of a high-cycle-parameter small-cold-air-capacity gas turbine guider, and a cooling system has the advantages of being small in heat exchange area, high in cooling effect, very suitable for a high-cycle-parameter aero-engine and a gas turbine and beneficial to heat management and cooling design optimization of the turbine guider. Small air entrainment amount can be achieved, engine performance is improved, micro-channel flowing and impacting are adopted, a higher heat exchange coefficient of an inner cavity can be achieved, the positions and angles of partition plate holes are adjusted, the temperatures of different positions of the blade are adjusted, and the metal temperature gradient of the blade is reduced.

Description

technical field [0001] The invention belongs to the technical field of aero-engines, in particular to a double-walled turbine guide vane with a small amount of bleed air. Background technique [0002] In order to improve the performance and power of aero-engines and gas turbines, the engine cycle parameters are continuously improved. The increase in the temperature resistance of turbine blade metal materials cannot meet the increase in engine cycle parameters, and the demand for thermal protection of turbine blades is increasing. The most commonly used thermal protection method for turbine blades is to cool the blades. Usually, the interior of the blades is hollowed out, and different cooling structures are arranged in the inner cavity of the blades according to the requirements of different positions, so as to reduce the metal temperature of the blades and improve the life of the turbine blades. [0003] Existing cooling of turbine guide vanes mainly includes cooling forms ...

AI Technical Summary

Problems solved by technology

[0008] The purpose of the present invention is to address the deficiencies of the prior art and provide a double-walled turbine guide vane with a small air-introduction volume to solve the technical problem of insufficient cooling of the gas turbine guide under the conditions of existing high cycle parameters and small air-induction volume

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