Method for cooling high-temperature turbine blade by utilizing supercritical characteristics of working medium

Abstract

The invention discloses a method for cooling a high-temperature turbine blade by utilizing the characteristics of a working medium under the supercritical state. The method comprises the following steps: step 1, arranging a cooling channel in a high-temperature area of the turbine blade, wherein the high-temperature area generally is the front edge of the blade; step 2, enabling the working medium in the cooling channel to efficiently and quickly transmit heat from the high-temperature area of the turbine blade to a relatively-low temperature area inside a flow channel of a turbine and the outside of the turbine through a cooling channel loop under the supercritical state, thereby providing a novel method for cooling an aircraft engine, a ground gas turbine, a missile engine and other high-temperature turbine blades.

Description

technical field [0001] The invention relates to the technical field of high-temperature turbine blade cooling, in particular to a method for cooling high-temperature turbine blades by utilizing the supercritical properties of working fluids, which can be applied to the cooling of high-temperature turbine blades such as aero-engines, ground gas turbines, and bomb-used missile engines. It is a new, efficient and fast cooling method for high temperature turbine blades. Background technique [0002] At present, the most commonly used cooling methods for high-temperature turbine blades include enhanced convective heat transfer, impingement cooling, and film cooling. However, with the rapid increase in the temperature in front of the turbine, the biggest disadvantage of these cooling methods is that the amount of cooling gas required also increases sharply. Taking the current advanced aero-engine as an example, the cooling air consumption has reached 20% or even higher of the tota...

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Problems solved by technology

[0002] At present, the most commonly used cooling methods for high-temperature turbine blades include enhanced convective heat transfer, impingement cooling, and film cooling. However, with the rapid increase in the temperature in front of the turbine, the biggest disadvantage of these cooling methods is that the amount of cooling gas required also increases sharply.

Taking the current advanced aero-engine as an example, the cooling air consumption has reached 20% or even higher of the total inlet flow, which greatly reduces the actual working fluid flow and lowers the performance of the whole machine; The cooling structure generally adopts a composite cooling method, which leads to complex cooling structure, difficult processing, and reduces the reliability of the blade

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