Flow inhibitor of turbomachine shroud
AssigneeGeneral Electric Company
InventorsIain Robertson Kellock, Charles Alan Bulgrin, Tagir Robert Nigmatulin, Ralph Chris Bruner
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Abstract
Disclosed is a shroud for a turbomachine including at least one support structure and at least one inner shroud disposed at a gas path of a turbomachine. The at least one inner shroud and the at least one support structure have at least one gap therebetween. The at least one gap alternates between at least one restrictive gap and at least one unrestrictive gap and is capable of creating at least one pressure loss mechanism to reduce a hot gas flow in the at least one gap. Further disclosed is a turbomachine and a method for reducing ingestion of hot gas in a turbomachine.
Claims20
A shroud for a turbomachine comprising:
- at least one support structure;
- at least one inner shroud disposed at a gas path of a turbomachine;
- and
- at least one gap between the at least one inner shroud and the at least one support structure, the at least one gap alternating between at least one restrictive gap and at least one unrestrictive gap capable of creating at least one pressure loss mechanism to reduce a hot gas flow in the at least one gap.
A turbomachine comprising:
- a plurality of nozzles disposed in a gas path;
- a plurality of buckets rotatable about a central axis of the turbomachine, the plurality of buckets disposed downstream of the plurality of nozzles;
- and
- at least one shroud disposed radially outboard of the plurality of buckets, the at least one shroud including:
- at least one support structure;
- at least one inner shroud disposed at the gas path;
- and
- at least one gap between the at least one inner shroud and the at least one support structure, the at least one gap alternating between at least one restrictive gap and at least one unrestrictive gap capable of creating at least one pressure loss mechanism to reduce a hot gas flow in the at least one gap.
A method for reducing ingestion of hot gas in a turbomachine comprising:
- flowing hot gas into a gap between at least one inner shroud and at least one support structure;
- flowing the hot gas in the gap in a circumferential direction relative to a central axis of the turbomachine;
- and
- inducing a pressure loss in the hot gas in the gap via alternating the gap between at least one restrictive gap and at least one unrestrictive gap.
Dependencies are inferred from the claim text.