Abstract: A turbine engine is disclosed that is capable of operating in an emergency power mode, an air breathing auxiliary power mode and a bypass bleed environmental control mode. In a preferred embodiment of the invention, the engine comprises in working fluid flow order a compressor for compressing air, a combustion chamber and a power turbine for extracting mechanical work from heated and/or compressed air. The compressor and turbine are separately coupled by a shaft which is also coupled to a generator for supplying electrical power and a cooling turbine for supplying cooled air to the aircraft cabin and avionics. The combustion chamber has an upstream combustor inlet and a downstream combustor inlet, each of which may admit compressed air either to be mixed with fuel for combustion, or to pass directly to the combustor outlet which is operatively attached to the power turbine section inlet.

Abstract: An annular shaft seal apparatus of the labyrinth type includes at least two pair of axially stacked thin annular diaphragm members. Each of the diaphragm members includes an annular array of radially and circumferentially extending finger portions defining gaps therebetween. The diaphragms of each pair are so disposed that the fingers of each block the gaps of the other. One of the pairs of diaphragm members is right-handed with respect to circumferential angulation of the finger portions, while the other pair is left-handed. Thus, sealing integrity is maintained by the finger portions regardless of the direction of shaft rotation.

Abstract: A fluid bearing damper for damping radial motion of a bearing includes a plurality of concentric, circular, thin shims located in an annular damping chamber to present thin, radially stacked damping cavities. A portion of the shims have protruding radial lands that partially define the cavities, carry radial loads through the damper and produce a controlled mechanical centering force as well as serving to ensure replenishment of fluid film cavities.

Abstract: An uncooled (adiabatic) engine having an insulator sleeve in each cylinder o retard heat flow into the engine wall structure. Each sleeve is yieldably (springably) mounted in an engine bore, such that the sleeve can experience thermal growth in the axial direction without excessive stress or mechanical failure.

Abstract: A piston-cylinder assembly of an internal combustion engine is provided which includes a cylinder liner mounted within a bore formed in an engine block, and a cylindrical spacer extending axially and endwise from the liner and coacting therewith to form a cylinder in which a piston is mounted for reciprocatory movement. An end piece overlies an end of the spacer and is supported by the latter. The end piece substantially closes off one end of the cylinder and the piston is in close proximity thereto when at one stroke limit. When the piston is at the one stroke limit, it coacts with the end piece and the spacer to define a combustion chamber. The end piece is secured in assembled relation with the spacer by a first means. A second means is provided for effecting substantial thermal insulating of the block, liner and first means from the heat of combustion which is generated in the combustion chamber during operation of the engine.

Abstract: A combustion chamber for an internal combustion engine is provided having a cylindrical member, an end piece overlying one end of the member, and a piston mounted for reciprocatory movement within the member and when at a predetermined relative position, coacting with the end piece and member to form a combustion cavity. A compliant gas seal is positioned between the end piece and member and is in surface contact therewith. The seal encompasses the combustion cavity and has a portion thereof continuously exposed to the cavity.

Abstract: This disclosure relates to a turbocharged internal combustion engine. The exhaust manifold of the engine is divided into sections, and the engine exhaust from one of the sections is recirculated to the intake manifold. The engine cylinders that feed the EGR exhaust manifold section alternate in the engine firing order with the other cylinders, thereby providing a substantially uniform flow of exhaust gas to all of the cylinders. The turbine of the engine turbocharger is divided into two sections, one having a smaller flow area than the other. The turbine section having the smaller flow area is connected to receive the exhaust gasses from the exhaust manifold section that also supplies the EGR.