General Electric Company

James Adaickalasamy

Kenneth Damon Black

Biju Nanukuttan

Debabrata Mukhopadhyay

Pugalenthi Nandagopal

Hariharan Sundaram

Prasad Punna

Pramod Akulu

Rakesh Adoor

A turbine engine assembly is provided. The assembly includes a compressor, and an air duct coupled in flow communication with the compressor. The air duct is configured to channel a flow of bleed air from the compressor therethrough. The assembly also includes a fluid supply system coupled in flow communication with the air duct, wherein the fluid supply system is configured to channel a flow of fluid towards the air duct to modify a temperature of the bleed air based on an operating condition of the turbine engine assembly.

Turbine engine assembly and method of operating thereof

A support assembly for externally adjusting an inner casing with respect to an outer casing for a turbomachine includes a carrier plate, a carrier block that is fixedly connected to the carrier plate, a restrictor block fixedly connected to the carrier plate, a rod coupled to the carrier plate, and a plate threadably connected to the rod. The carrier block includes an inclined side and a carrier side. The restrictor block includes a restrictor side and an inclined side. The restrictor side is generally oriented towards the carrier side. A vertical gap for receiving a support arm of an inner turbine casing is defined between the restrictor side and the carrier side. The plate may be rotated about the rod to cause simultaneous movement of the rod, the carrier plate, the carrier block and the restrictor block, thus adjusting the inner casing with respect to the outer casing.

Apparatus and method for adjusting an inner casing of a turbomachine

A rotary turbomachine includes a rotor mounting at least one disk having an outer surface and at least one bucket extending radially from said outer surface. A stationary stator component is located adjacent the disk, and a seal plate extends from a portion of the stationary stator component. An angel wing seal extends from the bucket, thereby defining a clearance gap between the seal plate and the angel wing seal. An abradable seal element is disposed on the seal plate, and the abradable seal element and the seal plate are canted at an acute angle relative to a center axis of the rotor extending radially outwardly in a direction toward the angel wing seal.

Retrofittable interstage angled seal

A system for operating a turbine includes a rotating component and a non-rotating component separated from the rotating component by a clearance. A first actuator is connected to the non-rotating component, and the first actuator comprises a shape-memory alloy. A method for operating a turbine includes sensing a parameter reflective of a clearance between a non-rotating component and a rotating component and generating a parameter signal reflective of the clearance. The method further includes generating a control signal to at least one actuator based on the parameter signal and moving at least a portion of the non-rotating component relative to the rotating component to change the clearance.

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Bengaluru, India

James Adaickalasamy