Abstract: An internal combustion engine having a cylindrical outer housing with inner cylindrical cylinders defining power cylinders circumferentially spaced in the engine. Each of the cylinder(s) has opposed intake and exhaust pistons. The intake and exhaust pistons use air bearings instead of conventional oil as a lubricant. The intake and exhaust pistons power a rotary cam mounted on opposed ends of the engine and a cam follower system positions the pistons. The rotary cam is operatively connected to a drive shaft or power take off shaft. A four bar linkage system is connected to the piston rod to minimize piston side loads. A jumper connects the ends of the power cylinders to pressurize air drawn into the engine and to admit heated air, indirectly heated during the combustion cycle, to charge the power cylinder for improved efficiency and to purge the pressure cylinder after combustion.

Abstract: An internal combustion engine having a cylindrical outer case(s) defining a base compression cylinder(s) with an inner cylindrical cylinder(s) defining power cylinder(s) circumferentially spaced in the engine and each housing opposing intake and exhaust pistons. Inlet ports for supplying pressurized air to the pistons included a small percentage of base compression air stored in an accumulator at a pressure that is the highest pressure in the engine. Flex tubes judiciously mounted in the piston and attached at either end to the piston and piston ring for supplying air from the accumulator to a plurality of pockets formed in the piston ring to hydrostatically support the pistons and piston rings. The pistons power a rotary cam mounted on opposing ends of the engine and a cam follower system positions the pistons for the 2-cycle operation. A four bar linkage system operatively connected to the piston rod to minimize piston side loads.

Abstract: Exit area control panels 18 are supported for movement at an angle with respect to the nozzle axis 12. A varying exit area is formed as actuator 26 axially positions the panels 18. In each exit area control panel 18, there is slidably supported a throat area control panel 28, driven by actuator 32. A sliding throat is achieved as the two panels 18,28 are moved in each quadrant. Yaw and pitch vectoring is accomplished with selective positioning of the two panels.

Abstract: Each of a pair of axially spaced turbine disks (12,14) has a plurality of blade retention fingers (20) at the periphery. Each blade has a pair of chevrons (64,66), one engaging a contiguous chevron (70) on a corresponding disk finger. The interacting chevron surfaces are located on the center plane (74) of a corresponding disk. Each finger is shaped to have a linear locus (75) of neutral axis (77) from the body of the disk to the chevron location. Each blade has a hollow platform structure (24), structural members (86,88,92,94) associated with a chevron (70), an airfoil extension (63) extending through the platform (28). High temperature cooling air (34) is directed into the blades (32,26,22) while being baffled away (42) from the turbine disks (12,14). Low temperature cooling air (48) bathes the live disks.

Abstract: A balance ring (18) which is shrunk fit within each disk (12) of a rotor is selectively ground for detail balance. A plurality of openings (20) through the outer edge of the balance ring receive weights during the assembly balance of the rotor. A snap ring (42) retains the weights within the openings.

Abstract: A variable area, convergent-divergent (10) nozzle for directing the flow of exhaust gas from an aircraft turbine engine to achieve thrust vectoring about yaw, pitch and roll axes includes a convergent section (16) and a divergent section (18) each comprised of hingedly connected planar members (201-214, 301-322) selectively positioned by actuators (101-114) for defining deformable gas directing flow ducts.

Abstract: A balance ring (18) which is shrunk fit within each disk (12) of a rotor is selectively ground for detail balance. A plurality of openings (20) through the outer edge of the balance ring receive weights during the asssembly balance of the rotor. A snap ring (42) retains the weights within the openings.

Abstract: A turbine rotor with air cooled blades has a turbine disk and a continuous hoop circumferential turbine rim bonded thereto. The rim has a plurality of circumferential rings extending toward the disk and forming circumferential chambers therebetween.Near the outer edge of the turbine rim are transversely extending openings. The rim is wire cut from these openings from the outer periphery forming segmented blade platforms, allowing the thermal expansion of the platform to occur. Tubes within the openings convey cooling air to the circumferential chambers, from which it passes to the blade interiors and through cooling openings in the platforms.

Abstract: A rotor has an inner disk member including a web and a circumferential widened outer portion. A blade member has a continuous circumferential inner edge. At least one of the members has a plurality of axially spaced circumferential rings extending toward the other member. The two members are diffusion bonded together. A stiff lightweight assembly is achieved.

Abstract: A flange construction is provided wherein two members have cooperating annular flanges for connecting them. Said flanges include annular projections which extend axially toward each other and provide for a "snap" engagement between inwardly and outwardly facing circumferentially surfaces on said flanges with bolts extending through said flanges with the bolt heads and nuts extending over an axial line forming an extension of the surfaces forming the "snap" engagement adjacent the bolt.

Abstract: A power plant is shown having a turbine power unit with a gas producer for directing gases into the unit while an exhaust duct delivers gas from the unit and a drive shaft extends from the unit for delivering power. The turbine power unit includes a turbine rotor mounted in bearing assemblies in its front and rear end. The rear assembly is supported by rigid struts while the front bearing assembly is supported by the first stage vanes and an interconnecting specially constructed diaphragm with heat shields. The outer ends of the vanes are fixed to a cantilevered ring fixed to the turbine casing while the inner circumference of the diaphragm has a large interference fit with a cylindrical surface on the front bearing assembly housing.