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    • 18. 发明专利
    • Performance diagnosis method for gas turbine
    • 气体涡轮机性能诊断方法
    • JP2003083089A
    • 2003-03-19
    • JP2001278981
    • 2001-09-14
    • Ishikawajima Harima Heavy Ind Co Ltd石川島播磨重工業株式会社
    • YAMAMOTO SEIJINARUKAWA MASAHIRO
    • F01D25/00F02C9/00
    • PROBLEM TO BE SOLVED: To provide a performance diagnosis method for a gas turbine capable of accurately grasping the deterioration of performance of the gas turbine from measurement data PWR, CIT, CDP, WGF, TOT, η, NOx obtained from the gas turbine during operation.
      SOLUTION: (A) At least one of gas turbine outlet temperature TOT, generating end efficiency η or exhaust gas NOx concentration NOx is selected as performance index I of the gas turbine, (B) the selected performance index is put into a model by linear function including a plurality of unknown parameters by intake air temperature, compressor outlet pressure, a change amount of gas turbine output and noise components, (C) gas turbine output PWR of the gas turbine during operation, intake air temperature CIT, compressor outlet pressure CDP, and the selected performance index I of the gas turbine are continuously obtained at a predetermined time interval, and (D) a plurality of unknown parameters of linear function model are inferred by multiple regression analysis based on the obtained data to obtain performance index excluding external fluctuation components.
      COPYRIGHT: (C)2003,JPO
    • 要解决的问题:提供一种能够从运行中从燃气轮机获得的测量数据PWR,CIT,CDP,WGF,TOT,η,NOx获得的能够精确地掌握燃气轮机的性能劣化的燃气轮机的性能诊断方法 。 解决方案:(A)选择燃气轮机出口温度TOT,产生最终效率η或排气NOx浓度NOx中的至少一个作为燃气轮机的性能指标I,(B)选择的性能指标通过线性 功能包括进气温度,压缩机出口压力,燃气轮机输出和噪声分量变化量的多个未知参数,(C)运行中燃气轮机的燃气轮机输出PWR,进气温度CIT,压缩机出口压力CDP ,并且以预定的时间间隔连续地获得所选择的燃气轮机的性能指标I,并且(D)通过基于所获得的数据的多元回归分析来推导出多个未知参数的线性函数模型,以获得不包括外部的性能指标 波动成分。
    • 19. 发明专利
    • METHOD FOR MEASURING FLUTTER OF TURBINE BLADE
    • JP2000220410A
    • 2000-08-08
    • JP2436999
    • 1999-02-01
    • ISHIKAWAJIMA HARIMA HEAVY IND
    • YAMAMOTO SEIJI
    • F01D5/10F01D21/00F01D25/00
    • PROBLEM TO BE SOLVED: To detect and measure the flutter phenomenon of a rotor blade and prevent the cracking of the rotor blade so as to avoid the operation stop by providing an analyzing device for frequency-analyzing the pressure fluctuation detected by a pressure sensor for detecting the pressure of the rotor blade rear part. SOLUTION: This turbine blade flutter measuring device 10 comprises a pressure sensor 12 mounted on a turbine casing 5 to detect the rear pressure of a rotor blade 1, and an analyzing device 16 for frequency-analyzing the pressure fluctuation detected by the pressure sensor 12. Further, the measuring device 10 comprises a data recorder 14 for recording the detected pressure fluctuation. From the pressure fluctuations mainly of about 340 Hs, the pressure fluctuation near a frequency about 3 times is extracted by a FFT or band pass filter, whereby the generating state of flutter can be detected. Even if an additional working can not be performed directly to the rotor blade rotating position of an engine casing, the flutter phenomenon of the rotor blade can be detected and measured.
    • 20. 发明专利
    • Gas turbine engine, device for preventing surging of gas turbine engine and method for preventing surging of gas turbine engine
    • 气体涡轮发动机,用于防止气体涡轮发动机的冲击的装置和用于防止气体涡轮发动机的冲击的方法
    • JP2005009371A
    • 2005-01-13
    • JP2003172844
    • 2003-06-18
    • Ishikawajima Harima Heavy Ind Co Ltd石川島播磨重工業株式会社
    • YAMAMOTO SEIJI
    • F02C9/46F02C3/30F02C9/00
    • PROBLEM TO BE SOLVED: To provide a device for preventing surging of a gas turbine engine capable of preventing surging due to atmospheric pressure change during operation without reduction of engine efficiency.
      SOLUTION: A surging prevention device 35 for the gas turbine engine for preventing surging of the gas turbine engine 1 includes an atmospheric pressure detector 39 capable of detecting atmospheric pressure during operation of the gas turbine engine 1, a compressor pressure detector 41 capable of detecting pressure of fluid compressed by a compressor of the gas turbine engine 1 during operation of the gas turbine engine 1, and a fuel control device 37 controlling fuel supply quantity to a combustor 13 of the gas turbine engine 1 corresponding to each pressure detected by each detector for preventing surging of the gas turbine engine 1 during operation of the gas turbine engine 1.
      COPYRIGHT: (C)2005,JPO&NCIPI
    • 解决的问题:提供一种用于防止燃气涡轮发动机的喘振的装置,其能够防止由于运行中的大气压力变化而引起的浪涌,而不降低发动机效率。 解决方案:用于防止燃气涡轮发动机1的喘振的燃气轮机的喘振防止装置35包括能够检测燃气轮机1运转时的大气压的大气压检测器39,能够检测燃气轮机1的压缩机压力检测器41 在燃气涡轮发动机1的运行期间检测由燃气涡轮发动机1的压缩机压缩的流体的压力;以及燃料控制装置37,其控制与燃气轮机1的燃烧器13对应的燃料供给量, 每个检测器用于在燃气涡轮发动机1的运行期间防止燃气涡轮发动机1的喘振。版权所有(C)2005,JPO&NCIPI