Abstract: A new kind of rotary piston machine with sealed work chambers and a wear resistant driving mechanism. Pivotal pistons move within respective cylinders and both the pistons and the cylinders revolve about circular orbits which are relative to one another. Both pistons and cylinders are included in a single piece rotor of unitary construction and can have either an axial or a radial configuration. Single-cylinder or multi-cylinder engines are included. This invention eliminates the necessity of piston bearings and thus, provides a wear-resistant, oil-free, driving mechanism. This invention further unites the sealing performance of the classical piston machine with the kinematic qualities of the rotary system.

Abstract: A fail-safe pivot door-type aircraft turbine engine thrust reverser which includes a plurality of pairs of pivoting doors on the blocker and deflector sides of openings in a fan jet nacelle. The doors form a flush surface along the nacelle exterior and the fan duct flow path when stowed during normal engine operation in flight. When the doors are deployed in thrust reversing mode, an extensible actuator causes them to translate aft in the opening, with one end of the blocker door moving to at least partially block airflow through the duct and divert it out along the door through the opening uncovered by door deployment. The deflector door pivots outwardly to extend the door length and further direct airflow out and forward along the outside of the nacelle. Upon initiation of deployment, a cooperating pin and track assembly causes the door to initially translate inwardly, then rearwardly, after which the pivoting action begins.

Abstract: An ejector for use in a refrigeration system has a mixing tube or diffuser which is partitioned into multiple flow passages. Selectively directing a continuously flowing primary high velocity fluid jet stream, which stream entrains a secondary fluid, cyclically into each of the multiple flow passages creates an effective pulsing of the primary high velocity fluid jet stream with respect to each flow passage. Pulsing the primary high velocity fluid jet stream in this manner enhances the mixing and compression of the primary high velocity fluid jet stream and the secondary fluid in the diffuser.

Abstract: A one-piece composite material torque box for the thrust reverser assembly of a jet engine. The torque box is made up of three composite material subassemblies, a generally planar flange subassembly, a tubular torque tube subassembly, and a cap subassembly. The flange subassembly is configured to transmit tension loads from the cascades of the reverser assembly to the V-blade ring which engages the engine, and the fibers in the composite material are aligned with these load paths. The torque tube subassembly is mounted to the flange subassembly, and is configured to transmit torsion loads from the actuators of the reverser assembly to the upper and lower latch members of the engine assembly; the fibers of the composite material therein are aligned at 45.degree. angles to the tube axis, so as to be in alignment with paths of the tension/compression components of the torsion loads.

Abstract: A burner comprises at least one swirl member for mixing a fuel with an air previously to burning of the fuel, and at least one eddy generating device which is arranged in a flow of a mixture of the fuel and air to generate an eddy flow in the flow so that the eddy flow maintains a shape of a flame of the burned fuel. The at least one eddy generating device is arranged apart from a downstream end of the swirl member by a fixed sufficient distance so that the shape of the flame maintained by the eddy flow is prevented from moving toward the downstream end of the swirler member.

Abstract: A steam deflector assembly for a steam injected gas turbine engine having an annular manifold as a part of the combustion chamber casing. The manifold has a port through the exterior of the casing and a plurality of evenly spaced steam passage holes leading to the interior of the casing. The deflector assembly comprises an exterior bracket surrounding the port to which a steam line is attached and a deflector plate and retainer member therefor located within the manifold. The assembly protects the casing from low cycle fatigue cracking and distributes the steam flow about the manifold.

Abstract: An oil pump device for a chain saw comprises a drive unit having a drive shaft and a gear fixed to the drive shaft and meshing with a worm gear fixed to a power output shaft of an engine. The oil pump device also comprises a pump unit having a pump casing and a plunger rotatably and axially reciprocatably received in the pump casing and drivingly connected to the drive shaft. The drive unit and the pump unit being formed as separate components and are drivingly connected to each other through a slide joint which permits the plunger to axially displace relative to the drive shaft.

Abstract: The invention relates to secondary power system apparatus and method for use aboard aircraft in place of conventional auxiliary power units (APU's) and emergency power units (EPU's). The invention integrated power unit (IPU) performs the function of both an APU and an EPU, while avoiding the use of hazardous monofuels. The IPU includes a turbine engine operable on pressurized ambient air, or on pressurized stored air, along with jet engine fuel. The structure of a combustion chamber for the engine which is able to use pressurized air from two separate sources; of a control able to selectively operate the engine as an EPU, as and APU, and to effect operating transition from EPU to APU; and of a complete secondary power system with the IPU are all disclosed.

Abstract: In order to reduce emissions of NO.sub.x, CO and unburned hydrocarbons, the flame temperature must be kept between 2500.degree.-2800.degree. F. Premixing combustor tubes are used to premix the fuel and air before the mixture is burned in the combustion chamber. The tubes are flashback resistant due to the flow of the fuel and air mixture through them. If it is desired to reduce the load operation of the combustor to substantially below 100% of its maximum load operation, as is the case during off-peak hours, the fuel and air flow rate can be regulated to reduce the load operation while still keeping the low emissions and the low flame temperature.

Abstract: A turbine engine includes adjacent compressor and turbine sections and an interstage seal assembly interposing therebetween in cooperation with a rotor assembly of the engine to inhibit leakage of pressurized air between the sections. The interstage seal assembly includes an annular wall portions at its outer perimeter cooperating with a housing of the engine and at its inner perimeter sealingly cooperating with the rotor assembly. The wall portions of the interstage seal includes nested conical sections of opposite axial dispositions which cooperatively resist both thermal and pressure differential induced distortion of the seal assembly.

Abstract: A fluid pressure energy translating device of the rotary, variable displacement type having a timing device providing gradual rise and reduction of pressure between the cylinder bores and the inlet and outlet ports. The timing device is in the form of a valve plate having a metering groove with a double notch design which exits into an associated outlet port, and a long single "V" notch metering groove which exits into a associated inlet port.

Abstract: A displacement controlling circuit system for a variable displacement pump, which system permits, following high or low rates of revolution of an engine for driving the pump, the displacement of the pump to be larger or smaller than a displacement determined on the basis of a difference between the pump delivery pressure and a load pressure. The displacement controlling circuit system comprises a revolution sensor (12) for detecting rates of revolution of the engine (9), and means (10, 11) for switching a load sensing valve (5) in such a manner that: when the detected rate of revolution of the engine is high, a displacement control member (2) of the variable displacement pump (1) is actuated in a displacement increasing direction; and, when the detected rate of revolution of the engine is low, the displacement control member (2) is actuated in a displacement decreasing direction.

Abstract: Cooling air to the 1-2 turbine stage seal is supplied in parallel with air to the second vane from a plenum. A modulatable valve in the supply line to the plenum regulates air flow in response to a sensed temperature in the 1-2 seal area at high sensed speeds. Valve and thermocouples are checked for proper operation. Immediate alerts and maintenance messages are established along with fail safe operating conditions upon fault detection. Over cooling of the seal area during low power operation, in anticipation of a power increase, is used to improve low cycle fatigue life of the turbine disk and seal runner.

Abstract: A low contamination double bellows pump suitable for providing relatively constant pressure and delivery. The illustrated pump includes two pumping chambers with bellows arranged in opposed relationship on opposite sides of a central section. The central section acts as a valve body for inlet and outlet valves. The bellows are provided with interior bellows tubes which connect to the free ends of the bellows and slide upon stationary support pistons mounted within each tube. Bellows tube head pieces slide upon piston rods which support the pistons. Pneumatic pressure is controllably supplied to opposing sides of the pistons within the bellows tubes to power the bellows and effect pumping.

Abstract: A gas turbine engine has a core frame separable from a vane frame for removably attaching the vane frame to a core structure through a mid ring. The mid ring includes an annular forward panel and an annular aft panel, each of which has a radially outer flange and a radially inner flange. The inner flanges are welded to the core frame and the outer flanges are bolted to the vane frame. A plurality of circumferentially spaced stiffeners extend between the forward and aft panels, with each of the stiffeners including a pair of stringers extending diagonally across the stiffeners. Panels may be incorporated with the stringers between the triangular shaped areas adjacent the forward and aft panels of the stiffener. The bolted connection between the mid ring and the vane frame includes a plurality of tongue and groove joints formed in the flanges of the mid ring and vane frame. The tongue and groove joints provide additional radial support for the core engine within the vane frame.

Abstract: The flow changing response of fluid systems having variable displacements pumps are greatly effected by the inertia of the displacement changing mechanisms, such as, the swashplate and at least half of the fluid pumping piston assemblies. In the present invention, a fluid system is provided which has a first flow changing mechanism operable to maintain a relatively constant pressure differential across a variable orifice device in a valve mechanism to change the flow of the fluid being delivered from the fluid pump to the fluid system. Simultaneously therewith, a second flow changing mechanism having a fast acting bypass mechanism acts in parallel with the first flow changing mechanism to more quickly bypass fluid being delivered from the fluid pump to the fluid system thus eliminating pressure spikes in the fluid system. The second flow changing mechanism is operable to establish a second larger differential pressure across the variable orifice device.

Abstract: A process of forming an igniter in an aft-end assembly for a solid rocket motor, the assembly having an internal cavity and comprising at least one element selected from the group consisting of a nozzle, a blast tube and an exit cone, which process comprises positioning an ignition package comprising pyrotechnic material and an initiator in the assembly cavity and causing a polymer foam to expand and cure in the assembly cavity and around the ignition package, so as to embed and secure the ignition package, form an aft closure, and for the igniter as an integral portion of the assembly.

Abstract: This gas turbine arrangement has a gas turbine which can be divided into a high-pressure part and a basic part and has a compressor (1) and at least one energy exchanger (7). In addition, it has a combustion-chamber arrangement and a separate combustion chamber (18) connected upstream of the energy exchanger (7). The intention is to provide a gas turbine arrangement in which an increased efficiency is achieved by simple means and which can be regulated more simply. This is achieved by providing at least two combustion chambers (9, 10) for the combustion-chamber arrangement. The first (9) of the combustion chambers cooperates with the high-pressure part of the gas turbine arrangement. The second (10) of the combustion chambers cooperates, via the interposed energy exchanger (7) having the upstream combustion chamber (18), with the basic part.

Abstract: A gas turbine cycle in which air is compressed to superatmospheric pressure, water is circulated in heat exchange relation with the compressed air to convert the sensible heat therein to heated water, the compressed air is humidified using the heated water, the humidified air is heated with sensible heat in the turbine exhaust gases, and a solid fuel such as coal is converted to a motive fluid for driving the gas turbine by substoichiometrically burning solid fuel under superatmospheric pressure using oxygen from the heated humidified air for combustion of the solid fuel and to produce combustible fuel gas and char, above stoichiometrically and adiabatically burning the char under superatmospheric pressure by supplying the heated humidified air in sufficient quantity to provide oxygen for combustion of the char and to control the temperature of such combustion, thereby to produce char combustion gases containing oxygen, cleaning the combustible fuel gas and the char combustion gasses to remove particulate mat

Abstract: A fuel injection pump plunger which enables the timing of the fuel injection to be controlled in accordance with the engine load, and can be used to prevent the emission of exhaust smoke and to achieve quieter engine operation, and under full-load conditions enables the engine to regain speed rapidly.