The gas drawn to the compressor passes through the center and acts as a cooler.

Turbine engines rely on high-temperature (more than 1,500 degrees) gas impact turbine blades, driving the rotor high-speed rotation, the higher the temperature of the gas, the more work done.

Turbine engine blades are generally subjected to greater working stress and higher operating temperatures, and stress and temperature changes are more frequent and violent, in addition to corrosion and wear problems, the requirements of its working conditions are very harsh, therefore requiring high precision machining of the blade.

Expanded Information:

Development of Wheel Blade Cooling Technology

Early turbine blades did not utilize cooling technology, and due to the limitations of blade materials, it was difficult for the RIT to exceed 1,323 K. With the development of cooling technology and high-temperature-resistant composites, the RIT with cooling topped out at 1203 K in the 1950's, and by the 1960's, an air-cooled turbine blade was used. In the 1960s, R1T exceeded 1273 K after the adoption of air-cooled turbine.

By the end of the 1960s R1T reached 1423 K, and within a decade the R1T increased by 493 K. In the 1970s and the early 1980s the RIT increased to 1643 K, and within a decade it increased again by 493 K, as shown in Fig. l. The R1T of a turbine with air-cooling was 1,623 K in the 1970s and the early 1980s. With the increasing maturity of cooling technology. A variety of basic turbine blade air cooling techniques have been developed cited.

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