Patent
Ring connection for porous combustor wall panels
TLDR
In this paper, a gas turbine engine combustor assembly of unique configuration has an outer wall made up of a plurality of axially extending multi-layered porous metal panels joined together at butt joints therebetween by a reinforcing and heat dissipation ring and a unique weld configuration to prevent thermal erosion of the ends of the polygonal panels at the butt joints.Abstract:
A gas turbine engine combustor assembly of unique configuration has an outer wall made up of a plurality of axially extending multi-layered porous metal panels joined together at butt joints therebetween by a reinforcing and heat dissipation ring and a unique weld configuration to prevent thermal erosion of the ends of the porous metal panels at the butt joints; the combustor further including a unique inner wall made up of a plurality of like axially extending multi-layered porous metal panels joined at butt joints by a reinforcing and heat dissipation ring on the inner surface of the inner wall panels and an improved butt weld joint that prevents thermal erosion of the ends of the porous metal inner wall panels.read more
Citations
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Patent
Gas turbine combustor
Eigo Takasago Res. Dvlpt Ctre Mitsubishi Kato,Mitsuru Takasago Res. Dvlpt Ctre Mitsubishi Kondo,T. Takasago Res Dvlpt Ctre Mitsubishi Ishiguro,Masaki Ono,Tetsu Konishi,T. Takasago Machinery Works Mitsubishi Iwamoto +5 more
TL;DR: In this article, a gas turbine combustor with a fuel injection nozzle using a fluid other than liquid fuel to atomize the liquid fuel and that can suppress a reduction in power generation efficiency resulting from a heat loss while promoting the atomization of liquid fuel.
Patent
Method and apparatus for cooling combustor liner and transition piece of a gas turbine
Ronald Scott Bunker,Jeremy Clyde Bailey,Stanley Kevin Widener,Thomas Edward Johnson,Intile John Charles +4 more
TL;DR: In this paper, a method and apparatus for cooling a combustor liner and transitions piece of a gas turbine was proposed, in which a plurality of circular ring turbulators arranged in an array axially along a length defining a length of the combustor lintern and located on an outer surface thereof.
Patent
Double dome combustor
TL;DR: In this paper, the first and second domes are joined together by two load transmitting structural paths for providing increased rigidity of the first-and second-domes for accommodating pressure loading from compressed airflow.
Patent
Single-cast, high-temperature thin wall structures and methods of making the same
Kurt Francis O'connor,James Paul Hoff,Donald James Frasier,Ralph Edmund Peeler,Heidi Mueller-Largent,Floyd Freeman Trees,James Rodney Whetstone,John Henry Lane,Ralph Edward Jeffries +8 more
TL;DR: In this article, a single-cast, thin wall structure capable of withstanding impinging gases at temperatures of 4300° F and higher is described, and a method of making the same.
Patent
Combustor cooling with angled segmented surfaces
TL;DR: In this article, a method of fabricating a combustor liner includes forming a plurality of angled strips on an outside surface of the combustor and arranged in an array about the outside surface, each of the angled strips is disposed so as to be spaced apart to create vortices in a cooling air flowing in a longitudinal direction across said outside surface.
References
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Patent
Ceramic combustion liner
TL;DR: In this article, a T-section metal ring is disposed between each adjacent pair of liner wall segments to align the segments with each other, and a resilient compressive connection between the upstream ring and the dome.
Patent
Combustion apparatus, e. g. for a gas turbine engine
TL;DR: In this paper, the wall of a gas turbine engine is made of compressed layers of nickel alloy mesh to form cooling air pores, whose maximum diameter does not exceed 400 microns and is preferably in the range 5 to 300 microns.