A gas turbine engine including a core having in serial flow order a compressor, a combustor, and a turbine—the compressor, combustor, and turbine together defining a core air flowpath. The gas turbine engine additionally includes a fan section mechanically coupled to the core, the fan section including a plurality of fan blades, and each of the plurality fan blades defining a pitch axis. An actuation device is operable with the plurality fan blades for rotating the plurality fan blades about their respective pitch axes, the actuation device including an actuator located outward of the core air flowpath to, e.g., simplify the gas turbine engine.

A multipoint injection system includes a manifold with a plurality of flow passages defined through the manifold in the circumferential direction. The flow passages are spaced apart from one another in an axial direction. A plurality of feed arms extends radially inward from the manifold. Feed arm portions of the flow passages extend through each of the feed arms to respective outlets. The feed arm portions of the flow passages are within the axial width of the manifold. A plurality of injection nozzles are included, each in fluid communication with a respective one of the outlets. Each injection nozzle includes an air passage therethrough with an air inlet. The feed arms each follow a path that is circumferentially offset from the air inlets so each of the feed arms is clear from a flow path directly upstream in the axial direction of each of the air inlets.

A clamp for securing a component to an isogrid case of a gas turbine engine includes a top having an attachment feature for coupling the clamp to the component. The clamp further includes a bottom. The clamp further includes two sides extending from the top towards the bottom, each of the two sides being thicker at the bottom than at the top, and the two sides defining a shaped slot closer to the bottom than the top for receiving a rib of the isogrid case.

A blade is provided for a gas turbine engine. The blade includes an airfoil portion with at least one internal cavity and a damper located within the internal cavity. The damper includes a cantilever spring arm. A fan blade is provided for a gas turbine engine. The fan blade includes an airfoil portion with at least one internal cavity; and a damper located within the internal cavity. The damper includes a cantilever spring arm that terminates with a rub surface pad adjacent to a friction bridge between a concave pressure side and a convex suction side of the airfoil portion. A method is also provided for damping a blade of a gas turbine engine. The method includes deflecting a cantilever spring arm to contact a rub surface pad with a friction bridge between a concave pressure side and a convex suction side of an airfoil portion of the blade.

A compressor rotor assembly including a plurality of rotor disks axially spaced from each other, each rotor disk extending radially from an inner end to an outer end. Also included is a spacer extending axially from each rotor disk to engage an adjacent spacer extending from an adjacent rotor disk, the spacer and adjacent spacer disposed proximate the outer end of the respective rotor disks, the spacers forming an outer backbone of the compressor rotor assembly. Further included is an inner backbone of the compressor rotor assembly, the inner backbone comprising a plurality of backbone segments, each of the backbone segments extending axially from each rotor disk to engage an adjacent backbone segment extending from an adjacent rotor disk, the backbone segment and the adjacent backbone segment disposed proximate the inner end of the respective rotor disks.

A composite blade is formed by laying up composite material layers in which reinforcement fibers are impregnated with resin in a thickness direction of the blade. The composite blade includes a blade root on a base end side, an airfoil on a tip side, a first lay-up in which some composite material layers are laid up in the blade root so as to space parts of the composite material layers to form spacing parts and to extend from the distal toward the base end side in the thickness direction, and second lay-ups in which some composite material layers are laid up in the spacing parts so as to be lined up in the thickness direction. Among the second lay-ups, a second lay-up closer to a center side than to an outer side in the thickness direction is a larger distance from a proximal position to a top position.

A turbine housing includes: a housing body which includes a turbine housing part housing a turbine wheel, an inlet section forming an inlet flow passage for guiding exhaust gas to the turbine housing part, an outlet section forming an outlet flow passage for discharging the exhaust gas from the turbine housing part, and a waste-gate flow passage which brings the inlet flow passage and the outlet flow passage into communication so as to bypass the turbine housing part; and a sleeve disposed along an inner wall surface of the housing body forming the waste gate flow passage, at least on a downstream side of the waste-gate flow passage of the housing body with respect to a flow direction of the exhaust gas.

A hydrocarbon production system includes a well at a remote location. The well is configured to produce hydrocarbon production fluids comprising natural gas. The system also includes a turbo-generator coupled to the well and configured to receive the natural gas and produce electricity from the natural gas. In addition, the system includes a high performance computing (HPC) data center coupled to the turbo-generator and configured to be powered by the electricity from the turbo-generator.

A pump for a fuel system include a housing, a pumping element, and a takeoff. The housing has an inlet, an outlet, and channel connecting the inlet to the outlet. The pumping element is supported within the housing and bounds the channel. The takeoff is connected to the housing and is in fluid communication with the channel at a location downstream of the inlet, and upstream of the outlet, to divert partially pressurized fuel for cooling an electronic device. Fuel systems and methods of cooling electronic devices are also described.

A gas turbine engine has a compressor section with a low pressure compressor and a high pressure compressor having a downstream end. A cooling air system includes a tap from a location upstream of the downstream most location. The tap passes air to a boost compressor, and the boost compressor passes the air back to a location to be cooled. The boost compressor is driven by a shaft in the engine through an epicyclic gear system. A speed control changes the relative speed between an input and an output to the epicyclic gear system.