Turbine rotor blade of gas turbine
A technology for turbine rotors and gas turbines, which is applied to the supporting elements of blades, mechanical equipment, engine elements, etc., can solve the problems of aggravation, high temperature and thermal stress, high temperature oxidation in the root region of the trailing edge of turbine rotor blades, etc., to reduce losses. The effect of coefficients
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[0022] The principle, specific implementation and working process of the present invention will be further described below in conjunction with the accompanying drawings.
[0023] Accompanying drawing has provided a concrete embodiment of the present invention. figure 1 is a three-dimensional view of a high temperature rotor blade of a gas turbine, which includes a blade profile 13, a blade root 11, and a blade platform 12 between the blade profile and the blade root. Cutting the blade along the arc line 20 of the blade shape, the internal structure of the blade can be obtained, such as figure 2 shown. Inside the blade there are multiple cooling channels for cooling gas flow. The cooling gas is extracted from a suitable position of the compressor, and delivered to the root cooling channel inlet 1 of the rotor blade along the gas turbine rotor shaft system. The size and number of root cooling channel inlets are selected according to the comprehensive consideration of the requ...
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