Abstract: A compliant foil radial bearing (100) comprising: a bushing (110) comprising a bore defined therethrough; a spring foil (120, 130) arranged to conform to a radially inner surface of the bore; a fluid foil (140, 150) arranged to conform to a radially inner surface of the spring foil for rotatably receiving a rotor, wherein: the spring foil comprises one or more retaining portions (160) arranged to extend axially and radially outside the radially inner surface of the bore.

Abstract: A rotational component includes a monolithic compressor component for rotation about a rotor axis defining proximal and distal directions, the monolithic compressor component including a compressor shaft defining a rotor core and a compressor wheel disposed distally from the rotor core.

Abstract: A compliant foil thrust bearing subassembly comprising: a fluid plate comprising an annular mating ring and a plurality of fluid foil elements disposed radially inwardly from the fluid plate mating ring; a force transfer plate comprising an annular mating ring and a plurality of force transfer elements disposed radially inwardly from the force transfer plate mating ring; and a spring plate comprising an annular mating ring and a plurality of deflection elements disposed radially inwardly from the spring plate mating ring, wherein: the fluid plate, the force transfer plate and the spring plate are stackable such that each fluid foil element is axially supported by a corresponding pair of overlapping force transfer elements and deflection elements.

Abstract: A compliant foil radial bearing (100) comprising: a bushing (110) comprising a bore defined therethrough; a spring foil (120, 130) arranged to conform to a radially inner surface of the bushing; a fluid foil (140, 150) arranged to conform to a radially inner surface of the spring foil for rotatably receiving a rotor, wherein: the radially inner surface of the bore comprises a plurality of axially oriented pads arranged around the circumference thereof.

Abstract: A gas turbine engine including: a rotor mounted for rotation about an axis defining proximal and distal directions; a compressor coupled to the rotor; a turbine coupled to the rotor and disposed distally from the compressor; a combustion chamber; a gas turbine exhaust; and a recuperator comprising: an annular heat exchanger comprising: an axial intake disposed at a distal end of the heat exchanger and an axial exhaust disposed at a proximal end of the heat exchanger; and a radial intake disposed at a proximal end of an inner radius of the heat exchanger and a radial exhaust disposed at a distal end of the inner radius of the heat exchanger, wherein the heat exchanger defines a first flow path between the axial intake and the axial exhaust and a second flow path between the radial intake and the radial exhaust .

Abstract: A rotational component includes a monolithic compressor component for rotation about a rotor axis defining proximal and distal directions, the monolithic compressor component including a compressor shaft defining a rotor core and a compressor wheel disposed distally from the rotor core.

Abstract: A compliant foil thrust bearing subassembly comprising: a fluid plate comprising an annular mating ring and a plurality of fluid foil elements disposed radially inwardly from the fluid plate mating ring; a force transfer plate comprising an annular mating ring and a plurality of force transfer elements disposed radially inwardly from the force transfer plate mating ring; and a spring plate comprising an annular mating ring and a plurality of deflection elements disposed radially inwardly from the spring plate mating ring, wherein: the fluid plate, the force transfer plate and the spring plate are stackable such that each fluid foil element is axially supported by a corresponding pair of overlapping force transfer elements and deflection elements.

Abstract: A gas turbine engine arrangement comprising a first engine section (2), the first engine section (2) comprising a first compressor (4) and a first turbine (6) mounted on a first shaft (8), the gas turbine engine arrangement further comprising at least one further turbine (20) mounted on a second shaft (22) and arranged such that gases exiting the first engine section (2) are ducted to the further turbine (20), wherein said first and second shafts (8, 22) are not mechanically coupled to one another and have respective axes which are offset from each other.

Abstract: A method of contactlessly machining a workpiece (16) is disclosed. A tool (2) is advanced in a direction towards the face of the workpiece (20), thereby removing material from the face of the workpiece (20) by a change of state of the material induced by its proximity to the tool (2). Also disclosed are number of tools which allow rapid simultaneous machining of a plurality of bladed disks.