Zero cooling air consumption super-strength cooling device for aircraft engine turbine blade

Abstract

The invention discloses a zero cooling air consumption super-strength cooling device for a turbine blade of an aircraft engine and relates to the cooling technology of turbine blades. A plurality of round hole channels are transversely processed inside the turbine blade from the front edge to the tail edge of the blade; the adjacent round hole channels are mutually communicated into a channel end to end; head and tail round holes nearby the front edge and the rear edge of the turbine blade are respectively communicated with an inlet and an outlet of a heat radiator through two conduits to form closely-communicated internal cooling channels; and high-pressure fluid is filled in the internal cooling channels. When the turbine blade feels high-temperature gas, the high-pressure fluid in the internal cooling channels forms inner circulation under the heat drive of the high-temperature gas, and the heat in the circular flow of the high-pressure fluid is taken away by the heat radiator, so that the super-strength cooling to the turbine blade is realized under the situation that the cooling air is not required. The zero cooling air consumption super-strength cooling device can improve the cooling the turbine blade under the situation that cooling air is not required and increase the inlet temperature of a turbine, thereby increasing the thrust-weight ratio of the aircraft engine and reducing the manufacturing cost of the aircraft engine.

Description

technical field [0001] The invention relates to the technical field of turbine blade cooling, and is a zero-cooling air consumption, super-strength gas turbine blade cooling device, which is especially suitable for high-performance aeroengines. Background technique [0002] The improvement of the thrust-to-weight ratio of an aero-engine mainly depends on increasing the gas temperature T before the turbine. 3 * At present, the turbine inlet temperature of domestic engines with a thrust-to-weight ratio of 10 has reached 1580 ℃ ~ 1680 ℃, and the temperature before the turbine of foreign advanced engines has reached about 2000K. The increasing gas temperature has seriously deteriorated the working environment of high-temperature parts of the engine, especially the turbine blades. At present, the temperature of the gas in many gas turbine engines has exceeded the limit that the turbine blade materials can withstand. At the same time, in order to ensure the efficiency of the com...

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Problems solved by technology

[0004] The purpose of the present invention is to propose a zero-cooling air consumption super-strength cooling device for aero-engine turbine blades, so as to overcome the problems of complex cooling structure of gas turbine blades in aero-engines and low cooling efficiency per unit air volume, and at the same time in order to avoid cooling air and mainstream gas The aerodynamic and heat loss caused by the blending of

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