Abstract: 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.

Abstract: Disclosed is a turbulated arrangement of thermoelectric elements for utilizing waste heat generated from a turbine engine. The turbulated arrangement of thermoelectric elements is located within the turbine casing at a heat exhaust end of the turbine engine. The turbulated arrangement of thermoelectric elements convert heat exhaust generated from the turbine engine into electrical energy. In one embodiment, the electrical energy generated from the turbulated arrangement of thermoelectric elements can be used to power electrical components located about the turbine engine.

Abstract: A gas turbine inlet system includes a first passage that delivers inlet air to a compressor, a second passage that delivers fuel to a combustor, and a heat pump that transfers heat from the inlet air to the fuel by consuming electric power. The heat transfer causes the turbine inlet air temperature to drop and fuel temperature to increase with favorable effects on both turbine output and heat rate.

Abstract: A process for applying a hard coating to a turbine rotor comprising providing a turbine rotor having at least one surface; applying a first coating to the at least one surface, the first coating being cold sprayed onto the at least one surface; applying a second coating onto the first coating to form the hard coating, wherein the hard coating is configured to substantially resist wear of a brush seal in physical communication with the turbine rotor.

Abstract: An exhaust strut is provided and includes a body having an airfoil-shaped cross-section defining a lead edge portion and a trailing edge portion opposite the lead edge portion, the lead edge portion and the trailing edge portion being connected by a pressure side and a suction side opposite the pressure side, at least the lead edge portion and respective sections of the pressure side and the suction side proximate to the lead edge portion being formed of shape memory alloy, and a temperature control system operably disposed at the lead edge portion and the respective sections of the pressure side and the suction side proximate to the lead edge portion to modify a temperature of the shape memory alloy.

Abstract: A mating structure is provided and includes a first article having a first mating surface formed of a metallic material, a second article having a second mating surface, the second article being disposed such that the first and second mating surfaces mate with one another and a coating disposed on the first mating surface, which is formed of a material having a hardness that is higher than that of the metallic material of the first article. The coating has dimensions exceeded by corresponding dimensions of the first article.

Abstract: A system for passively controlling clearance in a turbine engine comprises a static assembly arranged circumferentially about an engine rotor assembly and defining a gap between a tip end of the rotor assembly and an adjacent inner surface of the static assembly. The static assembly includes a gap control member that defines the inner surface, is exposed to the engine working fluid, and comprises a shape memory material selected and preconditioned to deform in a pre-selected manner in response to a temperature of the engine working fluid. Alternatively, airfoil blades of the rotor assembly include a gap control member. A method for passively controlling clearance in a turbine engine comprises assembling the engine so as to define an initial set of build clearances, operating the engine to observe running clearances, configuring a gap control member comprising a shape memory material and re-assembling the engine with the gap control member.

Abstract: 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.

Abstract: The invention is a class of nickel-base alloys for gas turbine applications, comprising, by weight, about 13.7 to about 14.3 percent chromium, about 5.0 to about 10.0 percent cobalt, about 3.5 to about 5.2 percent tungsten, about 2.8 to about 5.2 percent titanium, about 2.8 to about 4.6 percent aluminum, about 0.0 to about 3.5 percent tantalum, about 1.0 to about 1.7 percent molybdenum, about 0.08 to about 0.13 percent carbon, about 0.005 to about 0.02 percent boron, about 0.0 to about 1.5 percent niobium, about 0.0 to about 2.5 percent hafnium, about 0.0 to about 0.04 percent zirconium, and the balance substantially nickel. The nickel-base alloys may be provided in the form of useful articles of manufacture, and which possess a unique combination of mechanical properties, microstructural stability, resistance to localized pitting and hot corrosion in high temperature corrosive environments, and high yields during the initial forming process as well as post-forming manufacturing and repair processes.

Abstract: Disclosed is a turbulated arrangement of thermoelectric elements for utilizing waste heat generated from a turbine engine. The turbulated arrangement of thermoelectric elements is located within the turbine casing at a heat exhaust end of the turbine engine. The turbulated arrangement of thermoelectric elements convert heat exhaust generated from the turbine engine into electrical energy. In one embodiment, the electrical energy generated from the turbulated arrangement of thermoelectric elements can be used to power electrical components located about the turbine engine.