Turbine inlet nozzle guide vane mounting structure for...

Power plants – Combustion products used as motive fluid – Having expansible connection

Reexamination Certificate

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C060S805000, C060S806000, C415S116000, C415S136000, C415S164000, C415S173100, C415S173200, C415S175000, C415S176000, C415S178000, C029S889220

Reexamination Certificate

active

08001792

ABSTRACT:
Apparatus for channeling combustion gases to a turbine in a gas turbine engine. The engine has a compressor for providing compressed air, a combustor for combusting fuel with the compressed air to provide combustion gases, and a radial inflow turbine having an inlet configured to receive the combustion gases. The turbine is rotatable about an axis for expanding the combustion gases to produce work. The apparatus includes a subassembly of plurality of nozzle guide vanes fixed between a pair of spaced apart, ring-shaped sidewalls. A pair of spaced apart supports is configured to position the subassembly therebetween, concentric with the axis, and adjacent the turbine inlet. The apparatus further includes a plurality of bolt assemblies extending axially through the pair of supports, apertures in the sidewalls, and holes in the guide vanes. The sidewall apertures and guide vane holes each have an internal dimension in the radial direction sized and configured to accommodate thermal expansion and/or contraction sliding radial movement of the subassembly relative to the supports.

REFERENCES:
patent: 3362681 (1968-01-01), Smuland
patent: 3907457 (1975-09-01), Nakamura et al.
patent: 4054398 (1977-10-01), Penny
patent: 4247247 (1981-01-01), Thebert
patent: 4657476 (1987-04-01), Berg
patent: 5078576 (1992-01-01), Hayton
patent: 5344284 (1994-09-01), Delvaux et al.
patent: 5380154 (1995-01-01), Norton et al.
patent: 5459995 (1995-10-01), Norton et al.
patent: 6863495 (2005-03-01), Halliwell et al.
patent: 2006/0245926 (2006-11-01), Hillier et al.

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