The present disclosure relates generally to system and method for detecting fuel shutoff valve failures in a system including multiple fuel shutoff valves connected in series. By commanding different fuel shutoff valves to close and detecting changes in the system operating conditions, the system and method may determine if any of the fuel shutoff valves are not working properly.

One exemplary embodiment of this disclosure relates to a gas turbine engine. The engine includes a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The engine further includes a bearing assembly including an inner race, an outer race, and a plurality of rolling elements. A seal assembly is also included. The seal assembly includes a seal plate mounted for rotation with the rotatable shaft. The seal plate establishes a boundary of a tortuous passageway.

A turbine assembly is provided. The turbine assembly includes a gas turbine engine including at least one hot gas path component formed at least partially from a ceramic matrix composite material. The turbine assembly also includes a treatment system positioned to receive a flow of exhaust gas from the gas turbine engine. The treatment system is configured to remove water from the flow of exhaust gas to form a flow of treated exhaust gas, and to channel the flow of treated exhaust gas towards the at least one hot gas path component. The at least one hot gas path component includes a plurality of cooling holes for channeling the flow of treated exhaust gas therethrough, such that a protective film is formed over the at least one hot gas path component.

A closed loop thermal cycle expander bypass flow control is described. An expander is positioned within and surrounded by a housing to receive a working fluid and rotate in response to expansion of the working fluid flowing through the expander. A bypass channel is positioned within and surrounded by the housing to define a fluid flow path that bypasses the expander. A fluid flow control sub-assembly is fluidically coupled to the expander and the bypass channel, and attached to the housing. The fluid flow control sub-assembly can receive the working fluid at a housing inlet and either flow the working fluid through the expander and block the working fluid from flowing through the bypass channel, or flow the working fluid through the housing bypassing the expander, flow the working fluid out via a housing outlet, and block the working fluid from flowing through the expander.

A gas turbine engine includes a fan section and a compressor section. The compressor section includes both a first compressor section and a second compressor section. A turbine section includes at least one turbine and driving the second compressor section and a fan drive turbine driving at least a gear arrangement to drive the fan section. A power ratio is provided by the combination of the first compressor section and the second compressor section, with the power ratio being provided by a first power input to the first compressor section and a second power input to the second compressor section, the power ratio being equal to, or greater than, about 1.0 and less than, or equal to, about 1.4.

A method for purifying an asphaltene-containing fuel where the asphaltene-containing fuel is supplied to a deasphalting unit in which asphaltene contained in the fuel is separated using a solvent, thereby forming a substantially deasphalted fuel. The solvent is separated from the deasphalted fuel in a solvent recovery unit after a successful separation of the asphaltene from the fuel, and the waste heat of turbine exhaust gas produced in a gas turbine when converting fuel into electricity is used in order to purify the asphaltene-containing fuel. A corresponding device is used for purifying an asphaltene-containing fuel.

A pumped heat energy storage system is provided. The pumped heat energy storage system may include a charging assembly configured to compress a working fluid and generate thermal energy. The pumped heat energy storage system may also include a thermal storage assembly operably coupled with the charging assembly and configured to store the thermal energy generated from the charging assembly. The pumped heat energy storage system may further include a discharging assembly operably coupled with the thermal storage assembly and configured to extract the thermal energy from the thermal storage assembly and convert the thermal energy to electrical energy.

A single, unitary fuel/oil manifold for a gas turbine engine is provided which comprises one or more interfaces for mounting various fuel system and lubricating system components directly to the fuel/oil manifold. The fuel/oil manifold also defines fluid passages for transferring fuel or lubricant from one component to another component. Packing numerous fuel system and lubricating system components within the fuel/oil manifold reduces cost and weight and simplifies maintenance.

Airplanes and jet engines are provided that includes an engine compressor; a combustor in flow communication with the engine compressor; an engine turbine in flow communication with the combustor to receive combustion products from the combustor; and a bleed air cooling system in fluid communication with bleed air from the engine compressor. The bleed air cooling system can include a first precooler in fluid communication with the bleed air from the engine compressor; a cooling system turbine in fluid communication with and downstream from the first precooler; and a discharge conduit from the cooling system turbine that is configured to be in fluid communication with at least one of an aircraft thermal management system and an aircraft environmental control system. Methods are also described for providing cooling fluid from a jet engine.

Various embodiments relate to combined heat and power (CHP) systems. A CHP system can include a turbine system, a turbocharger system, and a refrigeration system. The refrigeration system can receive combustion products from the turbine system and compressed air from the turbocharger system. The refrigeration system can cool the combustion products and the compressed air to generate a cooled combustion product mixture that is provided to the turbine system.