A gas turbine engine component includes a supply cavity and a manifold cavity that shares a common divider wall with the supply cavity. The common divider wall includes inlet metering holes that connect the supply cavity and the manifold cavity. An exterior wall has an exterior surface and an opposed interior surface that bounds portions of the supply cavity and of the manifold cavity. Outlet cooling holes extend through the exterior wall and connect the manifold cavity with the exterior surface. The number of the inlet metering holes is equal to or less than the number of the outlet cooling holes, and at least one of the inlet holes is coaxial with at least one of the outlet holes.

A power generation system includes a shroud that defines a fluid flow path. A gas turbine engine is in the fluid flow path, and the gas turbine engine includes a compressor, a combustor downstream from the compressor, and a turbine downstream from the combustor. An electric generator is in the fluid flow path upstream from the turbine, and the electric generator includes a rotor coaxially aligned with the turbine. A plurality of non-lubricated bearings rotatably support the gas turbine engine.

A nested lattice structure for use in a damping system for a turbine blade includes a first lattice structure including: a first outer passage including a hollow interior; a second outer passage including a hollow interior; and an outer node including a hollow interior and forming an intersection of the first outer passage and the second outer passage. The nested lattice structure includes a second lattice structure nested within the hollow interior of the first lattice structure. The second lattice structure includes: a first inner passage; a second inner passage; and an inner node forming an intersection of the first inner passage and the second inner passage. Each of the first inner passage, the second inner passage, and the inner node are nested within the respective first outer passage, the second outer passage, and the outer node.

A gas turbine engine includes a rotatable first shaft, a first disk connected to the first shaft, a second disk connected to the first shaft, a combustor radially outward from the first disk and the second disk, and a heat exchanger connected to the combustor aft of the second disk. The first disk includes a row of low pressure compressor blades and a row of high pressure turbine blades connected to a radially outer end of the row of low pressure compressor blades. The second disk includes a row of high pressure compressor blades and a row of low pressure turbine blades connected to a radially outer end of the row of high pressure compressor blades.

A method of axially separating an annular system, such as a gas turbine engine (10), comprising first (34) and second (36) annular components. An annular array of fastenings (42) couples the first (34) and second (36) components together axially. The first (34) and second (36) components are supported by support tooling. The fastenings (42) are removed to leave one fastening (42) located on each side of the system. One of the remaining fastenings (42) is removed. The relative height of the first (34) and second (36) components is adjusted so that the apertures (46, 48) for the fastening (42) removed at the previous step are aligned. Then the final fastening (42) is removed.

An airfoil includes a dovetail root having a base. A grooved slot is disposed in the base and a plurality of root lightening cavities is disposed in the grooved slot.

An alignment system includes a first visual indicia and a second visual indicia disposed on a first mobile unit, and a third visual indicia and a fourth visual indicia disposed on a second mobile unit. The alignment system also includes a visual inspection area configured to enable collective viewing of the first visual indicia, the second visual indicia, the third visual indicia, and the fourth visual indicia along a single direction. The alignment system is configured to align the first mobile unit with the second mobile unit along a vertical axis, a horizontal axis, and a rotational axis to help align a rotational coupling between the first mobile unit and the second mobile unit.

An aerospike nozzle for an upper stage rocket of a multi-stage rocket system includes a throat, a centerbody extending aft of the throat, and an expansion surface defined by the centerbody, wherein the centerbody is an annular aerospike having a base that at least partially defines an aft end of the upper stage rocket. An engine includes a high pressure chamber and the aerospike nozzle. A vehicle for supersonic flight includes the engine with the aerospike nozzle.

A nested lattice structure 29 for use in a damping system includes a first lattice structure 26 including: a first outer passage 30 including a hollow interior 45; a second outer passage 32 including a hollow interior; and an outer node 42 including a hollow interior and forming an intersection of the first outer passage 30 and the second outer passage 32. The nested lattice structure 29 includes a second lattice structure 28 nested within the hollow interior of the first lattice structure 26 including: a first inner passage 44; a second inner passage 46; and an inner node 50 forming an intersection of the first inner passage 44 and the second inner passage 46. Each of the first inner passage 44, the second inner passage 46 and the inner node 50 are nested within the respective first outer passage 30, the second outer passage 32 and the outer node 42.

An axial flow turbomachine (102) for producing thrust to propel an aircraft is shown. The turbomachine has an inner duct (202) and an outer duct (204), both of which are annular and concentric with one another. An inner fan (206) is located in the inner duct, and is configured to produce a primary pressurised flow (P). An outer fan (207) is located in an outer duct, and is configured to produce a secondary pressurised flow (S). The outer fan has a hollow hub (208) through which the inner duct passes. The inner fan is configured to have, in operation, a tip speed of from 1 to 3 times that of the outer fan.