A heat shielded assembly includes a fuel structure of a combustor of a gas turbine engine and a woven heat shield at least partially conformally surrounding the fuel structure and spaced from an exterior of the fuel structure by a distance where it surrounds the fuel structure. The fuel structure is configured to deliver fuel to the combustor. The woven heat shield comprises a first set of strands, a second set of strands interwoven with the first set of strands, and a weave pattern comprising the first set of strands and the second set of strands. Each strand of the first set of strands extends in a first direction, each strand of the second set of strands extends in a second direction transverse to the first direction, and the first set of strands and the second set of strands are not attached where they intersect in the weave pattern.

A system is provided with an ejector having an outer wall extending circumferentially about a flow path, wherein the outer wall has a throat section along the flow path, and a diverging section downstream from the throat section along the flow path. The ejector includes a gas inlet configured to supply a gas into the flow path, and a water inlet configured to supply water into the flow path. The ejector is configured to produce steam in response to mixing of the water and the gas along the flow path. The system also includes a controller configured to control flows of the gas and the water to produce the steam for a steam purge of a liquid fuel circuit.

A structure for damping at a fluid manifold assembly for an engine is generally provided. The fluid manifold assembly includes a first walled conduit defining a first fluid passage therewithin. A flow of fluid defining a first frequency is permitted through the first fluid passage. A second walled conduit includes a pair of first portions each coupled to the first walled conduit. A second portion is coupled to the pair of first portions. A second fluid passage is defined through the first portion and the second portion in fluid communication with the first fluid passage. The flow of fluid is permitted through the second fluid passage at a second frequency approximately 180 degrees out of phase from the first frequency.

A tube spacing and fastening system for a gas turbine engine includes a plurality of tubular structures, a wear sleeve, a spacer element, and a fastening element. The plurality of tubular structures provides a fluid flow to a component of the gas turbine engine. The wear sleeve is located around each of the plurality of tubular structures. The spacer element receives the plurality of tubular structures. The fastening element extends around the wear sleeves and is configured to secure the plurality of tubular structures to the spacer element. An interference between the fastening element and wear sleeves is configured to allow the fastening element to slide with respect to the wear sleeves and to provide a damping effect under gas turbine engine vibrations and operating conditions. A method of damping vibrations in the plurality of tubular structures includes allowing the fastening element to slide with respect to the wear sleeve.

A fuel system can include a first fuel circuit, a second fuel circuit, and an inert gas purge system operatively connected to both the first fuel circuit and the second fuel circuit to purge at least a portion of either or both of the first and/or second fuel circuit. The first fuel can be a liquid fuel and the second fuel can be a gaseous fuel. The first fuel circuit can include a first fuel manifold configured to fluidly communicate a first fuel supply with at least one dual fuel nozzles downstream of the first fuel manifold.

Aircraft fuel ice capturing filter device housings, aircraft fuel ice capturing filter devices, and methods of use are provided.

Fuel distribution manifolds and combustors are provided. A fuel distribution manifold includes a main body and a fuel circuit that is defined within the main body. The fuel circuit includes an inlet section extending generally axially from an inlet to a first branch section and a second branch section. The first branch section and the second branch section diverge circumferentially away from each other as they extend axially from the inlet section to a respective first outlet and a respective second outlet.

A fuel pump system, comprising an inlet line and a motorized pump, a first selector valve in fluid communication with an inlet line at a first inlet port and in fluid communication with the motorized pump outlet via a first outlet branch at a second inlet port to receive fuel from the motorized pump outlet. The system can also include a main fuel pump in fluid communication with the first selector valve and a second selector valve, wherein the second selector valve can be in fluid communication with the main fuel pump and in fluid communication with the motorized pump outlet.

A combined-cycle power plant comprises a gas turbine engine for generating exhaust gas, an electric generator driven by the gas turbine engine, a steam generator receiving the exhaust gas to heat water and generate steam, and a duct burner system configured to heat exhaust gas in the steam generator before generating the steam and that comprises a source of hydrogen fuel, a fuel distribution manifold to distribute the hydrogen fuel in a duct of the steam generator, and an igniter to initiate combustion of the hydrogen fuel in the exhaust gas. A method for heating exhaust gas in a steam generator for a combined-cycle power plant comprises directing combustion gas of a gas turbine engine into a duct, introducing hydrogen fuel into the duct, combusting the hydrogen fuel and the combustion gas to generate heated gas, and heating water in the duct with the heated gas to generate steam.

A component susceptible to the formation of deposits, such as a component of a hydrocarbon system in a gas turbine engine. The component includes a substrate having a surface susceptible to the formation of a deposit thereon. A shape memory alloy coating is formed on the surface of the substrate. The shape memory alloy coating is a plurality of particles formed on the surface, and each particle of the plurality of particles is formed from a shape memory alloy.