Abstract: A turbine exhaust case assembly includes a frame which includes an outer ring, an inner ring, a plurality of struts that connect the inner ring and the outer ring and a monolithic fairing assembly that surrounds the frame.

Abstract: Aspects of the disclosure are directed to a system for maintaining a seal about an engine centerline, comprising: a first component, a second component, and a dog-bone seal coupled to the first component and the second component, wherein the first component is configured with at least one spline that is configured to engage a slot in the dog-bone seal to radially center the dog-bone seal relative to the first component and the second component.

Abstract: A gas turbine engine article includes a substrate and a bond coating that covers at least a portion of the substrate with a step formed in at least one of the substrate and the bond coating. A thermally insulating topcoat is disposed on the bond coating. The thermally insulating topcoat includes a first topcoat portion separated by at least one fault that extends through the thermally insulating topcoat from a second topcoat portion.

Abstract: A high efficiency power plant for a UAV with a high pressure ratio gas turbine engine used for low power operation such as loiter speed and a low pressure ratio gas turbine engine used for high power operation. A power turbine receives hot gas flows from the two engines to drive an output shaft. At low power operation, only the high pressure ratio engine is operated. At high power operation, both engines are operated where the exhaust from the high pressure ratio engine is used to drive a turbine of the low pressure ratio engine. A compressor of the low pressure ratio engine supplies compressed air to a combustor that produces a hot gas stream that is passed through the power turbine.

Abstract: A variable bypass ratio augmented gas turbine engine system for a UAV with a high pressure ratio gas turbine engine used for low power operation such as loiter speed and a low pressure ratio gas turbine engine used for high power operation. A power turbine receives hot gas flows from the two engines to drive an output shaft. At low power operation, only the high pressure ratio engine is operated. At high power operation, both engines are operated where the exhaust from the high pressure ratio engine is mixed with bleed off air form the second compressor to produce a second hot gas flow in a second combustor to drive the second turbine. The remaining compressed air from the second compressor is passed into a third combustor to produce a third hot gas flow that then flows into the power turbine.

Abstract: A hybrid power plant with a gas turbine engine that produces a hot gas flow that is passed through a power turbine to drive an output shaft. A second compressor and second combustor is driven by an electric motor to produce a second hot gas flow that is passed through the power turbine to drive the output shaft. at a cruise speed, only the gas turbine engine is operated to supply hot gas to the power turbine. At low speed or idle, only the second compressor and second combustor is used to produce a hot gas flow for the power turbine. At maximum power, both the gas turbine engine and the second compressor and combustor produces hot gas for the power turbine.

Abstract: An industrial gas turbine engine capable of operating at higher temperatures than air cooled nickel based alloy airfoils in the turbine. The engine burns stoichiometric or rich to produce a hot gas stream that is mostly without oxygen, and the turbine airfoils are made from a high temperature resistant material such as a refractory material that also has poor oxidation resistance. A second small gas turbine engine is used to compress nitrogen gas that is used to pass through the turbine airfoils for cooling where the film cooling nitrogen gas is injected into the hot gas stream but without igniting the fuel rich gas stream.