Mitsubishi Heavy Industries Limited

Mistubishi Heavy Industries, Ltd.

Masataka Ota

Shigemi Mandai

Koichi Nishida

Hideki Haruta

Shinji Akamatsu

Satoshi Tanimura

Kotaro Miyauchi

Koichi Akagi

Yoshichika Sato

Kazuya Kobayashi

Katsunori Tanaka

Tatsuo Ishiguro

Hajime Suzuki

Rintaro Chikami

Mitsuru Inada

Eiji Akita

Ichiro Fukue

Hiroshi Yoshizumi

Yoji Kochi

Tetsuo Gora

Teruya Tachibana

Tomohisa Takasaki

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.

A combustor includes a pilot fuel nozzle and a plurality of main premixing nozzles arranged therearound for forming a premixture of air and fuel supplied from a main fuel nozzle, and is improved so as not to cause vibratory combustion. Pilot fuel nozzle unit,comprises a plurality of pilot fuel nozzles,A plurality of main premixing nozzles,are disposed on a coaxial circumference of the pilot fuel nozzle unit,The pilot fuel nozzles,are arranged irregularly in a circumferential direction of the pilot fuel nozzle unit,so as to form portion,where there is no pilot fuel nozzle,Premature in the main premixing nozzles,positioned corresponding to the pilot fuel nozzle,burns with comparatively short flames. Premature in the main premixing nozzles,positioned corresponding to the portion,of no pilot fuel nozzle,burns with long flames because of flames spreading from adjacent main fuel nozzles. Thus, by differences in flame length, heat generation rate distribution is dispersed.

Combustor

Liquid fuel purge device uses water, not compressed air as in the prior art, thereby prevented are rapid load change of gas turbine due to sudden discharge of liquid fuel and coking of remaining liquid fuel. Upon supply of liquid fuel to fuel nozzle (,) being stopped, water purge system (,) having stop valve (,) supplies water into fuel system including liquid fuel system (,) and fuel nozzle (,) and liquid fuel remaining therein is purged by water into combustion chamber (,) from the fuel nozzle (,).

Gas turbine combustion system and combustor ignition method therefor

In gas turbine combustor in which combustion air flows on outer periphery of cylinder body and turns to enter the cylinder body while being mixed with fuel in main burner to form pre-mixture, there is provided upstream of the main burner 101 in the combustor 103 a rectifier 106 or 108 for rectifying the combustion air so as to make flow velocity of the combustion air uniform, thereby shortcomings in the prior art of concentration non-uniformity of the pre-mixture of main fuel and combustion air, high concentration of NO.sub.x generated from the main burner 101 in combustion, etc. are eliminated and larger combustion range to maintain stable combustion is attained.

A gas turbine combustor having a combustion chamber (10) with a steam-cooled peripheral wall (2) has an air hole (1) for injecting dilution air therethrough bored in the peripheral wall (2) on an upstream side of the combustion chamber (10). The air is thereby supplied through the air hole (1) into the vicinity of an inner surface of the peripheral wall (2) to form a film flow of air, and an increase of the fuel concentration there is suppressed. The dilution air is preferably supplied from a gas turbine compressor (6).

A combustor has a pilot nozzle 02 arranged at a central portion of an inner cylinder 01 opening at its end into a combustion chamber 018 and includes a plurality of main nozzles 03 arranged around its outer circumference. Along the outer circumference of a flame holding cone 014 for igniting a fuel F injected from the main nozzles 03 there are disposed elliptical extension pipes 016 of an elliptical sectional shape which are extended from the fronts of the main nozzles 03 to have openings at the axial position of the opening of the flame holding cone 014. As a result, a hot premixed flame 013 does not flow back to a main swirler zone 015 of the circumferential edges of the openings of the main nozzles 03 so that mixing between the fuel F and an air flow A can be improved, reducing the Nox emission while eliminating the burning of a base plate 04 and the main nozzles 03.

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Takasago, Japan

Masataka Ota