Abstract: A turbomachine includes a casing defining a hot gas path, and a shroud member attached to the casing. The shroud member is spaced from the casing to define a gap. The shroud member includes a first end having a first hook member provided with a first sealing surface and a second end including a second hook member provided with a second sealing surface. At least one of the first and second sealing surfaces includes a plurality of labyrinth seal elements that reduce air leakage through the gap into the hot gas path.

Abstract: The present application provides an angel wing seal for a turbine bucket. The angel wing seal may include a first wing with a sinusoidally-shaped outer edge and a number of wing teeth positioned thereon.

Abstract: A uniquely configured rotating seal tooth is used in conjunction with commonly used labyrinth-type seals that provide a seal between a rotating component and a stationary component. The uniquely configured rotating seal tooth produces a compression mechanism to counter leakage flow through the labyrinth of seal teeth, thereby lessening the pressure gradient that drives leakage and reversing the direction of some of the leakage flow.

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.

Abstract: The present application provides an angel wing seal for a turbine bucket. The angel wing seal may include a first wing with a sinusoidally-shaped outer edge and a number of wing teeth positioned thereon.

Abstract: A turbomachine includes a casing defining a hot gas path, and a shroud member attached to the casing. The shroud member is spaced from the casing to define a gap. The shroud member includes a first end having a first hook member provided with a first sealing surface and a second end including a second hook member provided with a second sealing surface. At least one of the first and second sealing surfaces includes a plurality of labyrinth seal elements that reduce air leakage through the gap into the hot gas path.

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.

Abstract: A uniquely configured rotating seal tooth is used in conjunction with commonly used labyrinth-type seals that provide a seal between a rotating component and a stationary component. The uniquely configured rotating seal tooth produces a compression mechanism to counter leakage flow through the labyrinth of seal teeth, thereby lessening the pressure gradient that drives leakage and reversing the direction of some of the leakage flow.