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    • 5. 发明专利
    • GAS TURBINE ENGINE
    • JPH0242140A
    • 1990-02-13
    • JP9508989
    • 1989-04-14
    • ROLLS ROYCE PLCRASUTON GAS TAABINSU LTD
    • JIYON MAIKURU OOUENPOORU KURAGO AIBII
    • F01D5/08F01D25/02F02C7/047
    • PURPOSE: To enhance the waterproof effect of a spherical portion by arranging a tubular member for delivering relatively high temperature air in the central portion of a rotary front spherical portion of a gas turbine engine, providing a double structure to the spherical portion and communicating the space therein with the tubular member. CONSTITUTION: In a gas turbine 1 comprising low and high pressure compressors 2, 3, a combustion device 4, a high pressure compressor 5 and a low pressure compressor 6, a front spherical portion assembly 10 is arranged at the end portion upstream thereof to form the radial inner wall of an air inlet. A tubular member 14 is arranged in the center of the assembly 10. The rear end thereof is connected to the front end of a hollow drive shaft 7. The assembly 10 is formed by an inner skin 16 and an outer skin 17. A space 20 communicating with the tubular member 14 is formed between the two skins 16, 17. The relatively high temperature air delivered through the tubular member 14 is blown to the central portion of the outer skin 17 and discharged through the space 20 and a hole 22, so that the surface of the assembly 10 is provided with a waterproof property.