Mitsubishi Heavy Industries Limited

Kazuya Kobayashi

Shigemi Mandai

Koichi Nishida

Shinji Akamatsu

Kotaro Miyauchi

Koichi Akagi

Hideki Haruta

Rintaro Chikami

Masataka Ota

Yoshichika Sato

Yoji Kochi

Masataka Ohta

A dual fuel nozzle is provided with two different size injection holes. The first injection holes have larger diameters and are used only for injecting gaseous fuel into a combustion chamber. On the other hand, the second injection nozzles have smaller diameters and are used for injecting either gaseous fuel or liquid fuel as required. When gaseous fuel is used, if the fuel injection amount is large or medium, both of the first and the second injection holes or first injection holes only are used for injecting gaseous fuel depending upon the required fuel injection amount. When the fuel injection amount is low, only the second injection hole is used for injecting gaseous fuel. Therefore, the pressure drop across the fuel nozzle can be kept at sufficiently high level even when the fuel injection amount is low, and thereby combustion vibration is suppressed. Further, when liquid fuel is used, a premixed fuel and steam mixture is injected from the second injection holes. This also keep the pressure drop across the fuel nozzle at high level in order to suppress combustion vibration when the fuel injection amount is low.

Dual fuel nozzle

In a central portion of inner tube,of combustor,pilot fuel nozzle,and pilot cone,are arranged and main fuel nozzles,and main swirlers,therearound. Air intake portion (X-,) is provided with rectifier tube,for making air intake uniform. In air intake portion (X-,), air holes of appropriate number of pieces are provided in circumferential wall of the inner tube,In main swirler portion (X-,) and pilot cone portion (X-,), bolt joint of the main swirlers,is employed and optimized welded structure having less influence of thermal stress of the pilot swirler,is employed, respectively. Tail tube cooling portion (X-,) is provided with cooling structure having less influence of thermal stress to cool flange,portion of tail tube,uniformly. By the improvements in the portions (X-,) to (X-,), obstacles in attaining higher temperature in the combustor,is dissolved and combustor performance is enhanced.

Gas turbine combustor

In a central portion of inner tube 28 of combustor 20, pilot fuel nozzle 22 and pilot cone 33 are arranged and main fuel nozzles 21 and main swirlers 32 therearound. Air intake portion (X-1) is provided with rectifier tube 11 for making air intake uniform. In air intake portion (X-2), air holes of appropriate number of pieces are provided in circumferential wall of the inner tube 28. In main swirler portion (X-3) and pilot cone portion (X-4), bolt joint of the main swirlers 32 is employed and optimized welded structure having less influence of thermal stress of the pilot swirler 33 is employed, respectively. Tail tube cooling portion (X-5) is provided with cooling structure having less influence of thermal stress to cool flange 71 portion of tail tube 24 uniformly. By the improvements in the portions (X-1) to (X-5), obstacles in attaining higher temperature in the combustor 20 is dissolved and combustor performance is enhanced.

For obtaining a highly compressed air in an axial compressor, a load per blade row must be reduced and blade rows must be increased in number by so much that the apparatus becomes unavoidably larger. The present invention provides an axial compressor stationary blade wherein a blade portion near an end wall face is twisted so as to coincide with a direction of a boundary layer flow occurring in the vicinity of the blade portion. This blade portion and a blade portion for the main flow are turned differently from each other over a distortion or twist angle, and thereby growth of the boundary layer flow is suppressed, an increase of losses is prevented, and the apparatus can be made compact.

Axial compresssor stationary blade

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Takasago, Japan

Kazuya Kobayashi