Power plants – Combustion products used as motive fluid – Combustion products generator
Reexamination Certificate
2000-07-06
2001-10-16
Casaregola, Louis J. (Department: 3746)
Power plants
Combustion products used as motive fluid
Combustion products generator
C060S748000
Reexamination Certificate
active
06301900
ABSTRACT:
TECHNICAL FIELD
The present invention relates to a combustor for a gas turbine.
BACKGROUND ART
As is well known, a combustor for a gas turbine is adapted so that a fuel ejected from one or more nozzle holes of a nozzle body is mixed with swirling air blowing from a swirl path formed around the nozzle body.
Particularly, when the nozzle body is of a cylindrical columnar shape having a wall at a tip end, i.e., a downstream end, and the one or more nozzle holes is located at the center of the downstream end wall as in a case of a pilot combustor, the swirl air flowing along the outer circumference of the nozzle body separates therefrom at the periphery of the downstream end wall of the nozzle body and generates circulation vortices into which the fuel ejected from the one or more nozzle holes is involved. This causes a problem in that smoke may be generated because the fuel burns while remaining therein (see FIG.
2
).
The present invention has been made to solve the above-mentioned problem, and an object thereof is to provide a combustor for a gas turbine wherein fuel, ejected from the one or more nozzle holes at the center of a downstream end wall of a nozzle body is mixed with swirling air blowing from a swirl path formed around the nozzle body, is burnt without remaining near the one or more nozzle holes to prevent smoke from being generated.
DISCLOSURE OF THE INVENTION
According to the present invention, provision is made of a combustor for a gas turbine, wherein fuel ejected from one or more nozzle holes at the center of a downstream end wall of a nozzle body is mixed with swirling air blowing from a swirl path formed around the nozzle body. The combustor is characterized in that a nozzle cap of a generally conical shape diverging downstream from the one or more nozzle holes in a nozzle body is provided. According to the combustor for a gas turbine of such a type, the fuel ejected from the one or more nozzle holes flows along the nozzle cap without remaining thereon.
Preferably, the downstream end of the nozzle cap is united with the inner wall of the swirl path so that the nozzle cap forms a fuel-jet guide for smoothly guiding the fuel ejected from the one or more nozzle holes into the swirl path.
Also, a path for directing cooling air toward the one or more nozzle holes may be provided at the upstream end of the nozzle cap so that the nozzle cap is cooled by a flow of the cooling air along the fuel-jet guide to prevent fuel mist from sticking to the fuel-jet guide.
Further, a partition may be provided between the swirl path and a circumference of the nozzle body to define a narrow path between the circumference of the nozzle and the partition, the downstream end of the narrow path being connected to the upstream end of the cooling air path to take in cooling air from the upstream of the narrow path.
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patent: 4170108 (1979-10-01), Mobsby
patent: 5303554 (1994-04-01), Faulkner
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patent: 10-2558 (1998-01-01), None
Akamatsu Shinji
Haruta Hideki
Kamogawa Masahiro
Mandai Shigemi
Nishida Koichi
Casaregola Louis J.
Mitsubishi Heavy Industries Ltd.
Paul & Paul
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