Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A gas turbine engine that includes a heat exchanger for heating a fuel gas using compressed air generated by the engine. The heat exchanger is positioned within an outer housing of the engine and receives the fuel gas at a first input prior to the fuel being mixed with a combustion portion of the compressed air and receives a cooling portion of the compressed air at a second input prior to the cooling portion of the compressed gas being sent to cooling flow channels. The heat exchanger also includes a first output that directs the fuel from the heat exchanger to be mixed with the combustion portion of the compressed gas and a second output that directs the cooling portion of the compressed gas to the cooling flow channels.

Abstract: 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.