Siemens Energy, Inc.

Stephen Erick Holland

Chad W Heinrich

Matthew H Lang

Gerard McQuiggan

Veronica Arocho Pettit

Andrew Medla

A cooled turbine component in a turbine engine is provided. The cooled turbine component includes a brazed in heat transfer feature, the brazed in heat transfer feature including a thin film including a heat transfer feature incorporated into a surface of the film. The thin film is capable of conforming to a surface of the cooled turbine component and is attached to the surface of the cooled turbine component via a braze material. A method for cooling a turbine component in a turbine engine is also provided.

Brazed in heat transfer feature for cooled turbine components

A converging-diverging nozzle that has particular application for providing a cooling air flow to ring segments in a gas turbine engine. The engine includes a turbine section that receives a hot working gas. The turbine section includes at least one row of vanes, at least one row of blades and a plurality of ring segments forming at least one ring. The ring segments and the vanes are mounted to a vane carrier, where the vane carrier includes a cooling flow channel for each of the ring segments that receives an air flow to cool the ring segments. A plug is provided in each channel and has an internal bore shaped to define the converging-diverging nozzle through which the air flows so as to create a supersonic flow that reduces the temperature of the air and thus provides more cooling for the same amount of air flow.

Cooling air temperature reduction using nozzles

A method for inspecting a turbine blade of a turbine. The method includes operating the turbine and providing a plurality of ablative material strips on the turbine blade. Each strip is fabricated from a common base material and is configured to ablate after exposure to a corresponding predetermined temperature for a corresponding predetermined time period Ablation of a strip indicates a corresponding amount of creep has occurred in the blade. In addition, the method includes visually inspecting the strips at predetermined intervals to determine whether one or more of the strips is ablated.

Method for tracking turbine blade creep

A gas turbine engine is provided comprising a compressor, a fuel supply apparatus, a combustor, and a turbine. The fuel supply apparatus comprises a fuel source, a cooling apparatus including a heat exchanger and structure for defining a first path for fuel to travel from the fuel source to the heat exchanger and a second path for fuel to travel away from the heat exchanger. The combustor functions to receive the compressed air from the compressor and the fuel from the heat exchanger, combine the air and fuel to create an air/fuel mixture and ignite the air/fuel mixture to create combustion products. The cooling apparatus further comprises structure coupled to and extending between the heat exchanger and at least one of a plurality vanes in the turbine for circulating a coolant fluid through at least one vane and the heat exchanger. In another embodiment, pipe supply structure extends from a fuel source through an end section of a turbine casing. In a further embodiment, a heat exchanger of a heat recovery steam generator is provided in a turbine casing end section.

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Oviedo, FL, United States of America

Stephen Erick Holland