发明名称 METHOD OF COOLING GAS TURBINE BLADE
摘要 PURPOSE:To permit high temperature operation and improve output by cooling compressed air with injection of normal temperature water into high pressure air extracted from a compressor and cooling the movable blade with air containing water droplets. CONSTITUTION:Air 11 led into a compressor 12 is compressed there, and then its major proportion is led to a combuster 14 to cause combustion of fuel 13. With the combustion gas formed in the combuster 14 a turbine 16 is driven to drive a genmerator 18. In this case, compressed air is partly extracted from the main path at a position near the last stage of the compressor 12 for cooling the turbine blade, and cooling water 19 is injected into a separately provided water injection chamber 22 from a nozzle 20. Thus, while cooling the compressed air, a suitable quantity of water droplets is introduced, and the air containing the introduced water droplets is led through an inlet port 31 into an air cavity 35 and thence led through supply discs 32 in a turbine disc 6 and passages 34 through the movable blade 7 for cooling.
申请公布号 JPS5477820(A) 申请公布日期 1979.06.21
申请号 JP19770143870 申请日期 1977.12.02
申请人 HITACHI LTD 发明人 SAKAMOTO TAKESHI;ANZAI SHIYUNICHI;KOBAYASHI SHIGEYOSHI;OOSHIMA RIYOUICHIROU
分类号 F01D5/08;F01D5/18;F02C3/30;F02C7/18 主分类号 F01D5/08
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