Abstract: The objective of the present invention is to provide a reciprocation switching device for a pump which will solve problems of conventional devices such as that, because coil springs are used for activating by their snap action valve operators or switching operators serving to control the pressure of pump working fluid in relation to reciprocating action of the pump, such devices require the numerous number of parts including spring fitting shafts, the structure to attach such fitting shafts, parts for spring holders, etc.; and that the assembling of those parts is troublesome. A device according to the present invention uses one or two wire springs made into a C-like shape as the springs for the aforementioned purpose and calls for fitting said springs directly between the spring fitting section(s) and the valve operator or the switching operator.

Abstract: An engine end and thrust reversing assembly comprising an annular thrust diverting structure which in the cruise configuration is a rearward extension of a fan duct cowl structure. For thrust reversal, the thrust diverting structure is swung rearwardly and inwardly about an inboard hinge axis to form a laterally and forwardly directed thrust reversing opening. A transversely curved blocking plate is pivotally mounted about a vertical axis to the fan duct structure, and in the cruise configuration it is positioned adjacent to a forward extension of the thrust diverting structure so as to surround a portion of the exhaust passageway. In the thrust reversing position, the blocking plate is swung to a position where it extends across the exhaust passageway defined by the thrust diverting structure.

Abstract: An engine shroud with integral honeycomb panel corners for use in the thrust reverser region of ducted fan gas turbine engines. The integral shroud is useful in a turbine engine having a core engine surrounded by an engine casing and nacelle, with a fan at the inlet directing air flow into the bypass duct between core engine and engine nacelle. The shroud basically consists of right and left ducts each having an approximately semicircular cross-section with radial flanges extending from the duct edges. The flanges permit the halves to be fastened together to produce a tubular shroud adapted to surround a gas turbine engine and form the inner wall of a bypass duct. The disclosed shroud eliminates the prior complex corner fittings connecting the semicircular center portion of the shroud to the extending flanges and provides simple, integral corners.

Abstract: There is disclosed in combination with a solid fuel-propellant grain 24 having an axially extending aperture 26, particularly of a hybrid rocket motor, an oxidizer inlet 20 at one end and a combustion gas outlet 22 at the other end, a tubular oxidizer injector 32 disposed in the inlet and extending axially in the grain aperture. The tubular injector comprises a tube 34 containing a plurality of oxidizer injection orifices 38 in the outer circumference of the tube to discharge fluid streams of oxidizer into the fuel grain aperture for combustion of the fuel grain. Additional oxidizer orifices, e.g. in the form of shower head orifices 44, are disposed in the downstream end of the tube.

Abstract: The problem of space and weight limitations for liquid ring pumps and regenerative pumps in aerospace applications is solved by a pump having a housing defining a first chamber (22) and a second chamber (24) independent of the first chamber. An impeller (10) is rotatably mounted in the housing and includes impeller blades (16) successively movable through the first chamber for cooperation therewith to provide a liquid ring portion of the pump, and through the second chamber for cooperation therewith to provide a regenerative portion of the pump. An inlet (26) admits fluid to the first chamber. A first outlet (28) from the first chamber feeds the fluid to an inlet (32) of the second chamber for pressurization therein. An outlet (34) from the second chamber feeds the pressurized fluid for appropriate use, such as in a fuel pump system.

Abstract: An integral "C" duct for the thrust reverser region of ducted fan gas turbine engines. The integral duct is useful in a turbine engine having a core engine surrounded by an engine casing and nacelle, with a fan at the inlet directing air flow into the bypass duct between core engine and engine nacelle. The "C" duct basically consists of right and left "C" shaped ducts with bifurcations (radial flanges) permitting the halves to be fastened together to produce a tubular duct adapted to surround a gas turbine engine and form the inner wall of a bypass duct. The disclosed duct eliminates the prior complex corner fittings connecting the "C" shaped portion of the duct and the bifurcations and provides simple, integral corners.

Abstract: A heat protective lining for a passage in a turbojet engine is formed of tiles arranged side by side to form rings which are themselves arranged end to end. Each tile comprises a panel provided at its upstream and downstream edges with radially outwardly directed flanges forming circumferential stiffeners, the upstream flange having on its upstream radial face male securing and sealing means cooperating with complementary female means on the downstream radial face of the downstream flange of the adjacent upstream tile.

Abstract: A plurality of gas diffusion openings (24) direct film cooling air (26) along the surface of sheet (20). Each opening (24) includes a baffle (28) extending into gas stream (10) defining gas chamber (30) with outlet opening (32). Cool air inlet opening (34) meters and directs impingement air against the upstream end (36) of the baffle. cooling air discharge is parallel to the surface to be cooled and the baffle directs the upstream hot air flow.

Abstract: A method for enhancing the thermal response of the engine case and annular shroud during the transient response period following a step change in engine power provides for the temporary reduction or elimination of the flow of cooling air supplied to the engine case by the active clearance control system. An alternate method additionally substitutes a flow of relatively warm air to further increase the response of the case.

Abstract: An arcjet thruster comprises a cathode body and anode body tandemly arranged and separated by an insulative propellant injection ring. The cathode body has a cathode cavity therein having a convergent and a divergent portion forming a throat therebetween. The anode body has a divergent cavity therein for producing thrust. The divergent cavity has an upstream portion and a downstream portion. The divergent portion of the cathode and the upstream portion of the anode cavity form a constrictor. A power supply connected between the anode and the cathode bodies is used to produce an arc between the anode and cathode that passes through the constrictor. Propellant is injected in a vortex flow radially into the constrictor so that it divides. A portion of the flow is directed upstream through the throat into the convergent portion of the cathode cavity thus also pushing the cathode arc attachment point into the convergent portion to cause diffuse attachment thereof.

Abstract: A rotary hydraulic machine which includes a housing having a shaft mounted for rotation within the housing about a shaft axis. A cylidner block is coupled to the shaft for co-rotation with the shaft within the housing and includes a plurality of cylinders disposed in a circumferential array parallel to and surrounding the shaft axis. A piston is disposed to reciprocate within each of the cylinders and is coupled to a yoke for determining displacement of the pistons within the cylinders. A valve plate is mounted on a valve block and includes kidney-shaped slots for registering with the cylinders as the cylinder block rotates, and thereby connecting the cylinders to pump input and output ports. A microprocessor-based controller is externally mounted on the pump valve block and includes internal memory having various remotely-selectable control programs prestored therein.

Abstract: Means and method are disclosed for reducing buckling loads across an afterburner combustion liner in an augmented gas turbine engine. Means for accelerating bypass cooling airflow and then decelerating the accelerated bypass airflow for creating pressure losses to provide reduced-pressure bypass airflow to a plenum surrounding the afterburner liner are disclosed. In a preferred embodiment, the bypass airflow is accelerated to a velocity greater than Mach 1 and is then decelerated to a velocity less than Mach 1 for incurring shock waves for generating pressure losses for reducing differential pressure acting across the liner.

Abstract: A heat protective lining for the afterburner or transition duct of a turbojet engine comprises an assembly of tiles overlapping laterally and longitudinally to form overlapping rings of tiles in which the tiles of each ring are offset laterally from those of each adjacent ring by half a tile width. The tiles are held together by eyelets projecting from the overlapped downstream portions of the tiles through apertures in the overlapping upstream portions, and locking members engaging through the eyelets. Fastening yokes for fixing the assembly to the duct casing are secured to the outside of the tiles.

Abstract: The invention comprises an expansion nozzle for a rocket engine destined to function successively in atmospheric and space conditions. The nozzle is comprised of a main wall defining a surface of revolution that splays outwardly and further comprises a complementary annular convergent divergent nozzle having an exhaust port and also having its axis coinciding with the principal axis of the main wall. The complementary annular nozzle is located outside the main wall and has a gas distribution torus cooperating with gas flow supply means to produce an annular flow of gas surrounding a main flow of gas exhausted at the down stream extremity of said main wall of the expansion nozzle. The annular flow of gas forms a source of static pressure P.sub.s that is substantially lower than atmospheric pressure P.sub.a. P.sub.s has a value of between 0.3 and 0.8 times P.sub.a.

Abstract: In an apparatus for pneumatically discharging concrete fed hydromechanically in a dense stream, using for the hydromechanical feed a concrete pump having a hydraulic drive comprising at least two cylinders with opposed pistons, said pump having synchronization control by a displacer circuit conducting the working medium displaced by a piston, and having a dosing means for an additive serving as an accelerating agent, whose drive is connected to the hydraulic circuit of the concrete pump drive, the inventive proposal is that the drive of the dosing means is connected to the displacer circuit and designed as a reciprocating piston drive whose absorption amount corresponds to the displacement amount of the working pistons and is added in both directions to the displacement amount of each working piston.

Abstract: A slant plate type compressor including a crank chamber and a suction chamber is disclosed. The slant plate is disposed in the crank chamber at a variable slant angle. The slant angle varies in dependence on the crank chamber pressure. The crank chamber is linked by a communication path to the suction chamber. The slant angle may be varied by controlling the link of the crank and suction chambers to thereby vary the capacity of the compressor. The link of the crank and suction chambers through the communicaton path is controlled by a valve mechanism. The valve mechanism includes a first valve control device which opens or closes the communication path in response to an external signal to vary the compressor capacity, and a second valve control device which is responsive to the suction pressure to open or close the communication path.

Abstract: In the representative embodiment of the new and improved methods and apparatus disclosed herein to provide effective real-time management of a spacecraft rocket engine powered by gaseous propellants, real-time measurements representative of the engine performance are compared with predetermined standards to selectively control the supply of propellants to the engine for optimizing its performance as well as efficiently managing the consumption of propellants. A priority system is provided for achieving effective real-time mangagement of the propulsion system by first regulating the propellants to keep the engine operating at an efficient level and thereafter regulating the consumption ratio of the propellants. A lower priority level is provided to balance the consumption of the propellants so significant quantities of unexpended propellants will not be left over at the end of the scheduled mission of the engine.

Abstract: A method for the repowering of an existing coal-fired facility used in the generation of electric power which makes the facility more efficient while reducing its emissions in a cost-effective manner using the following steps: a) processing the coal in use to co-produce a clean liquid fuel and a clean low Btu gas; b) replacing the pulverized coal burners of the boiler contained in the facility with burners adapted to burn low-Btu gas; c) burning clean low-Btu gas in the boiler instead of coal; d) making up the derate of the boiler by the addition of efficient combined cycle power generation; and e) crediting the revenue derived from the sale of the liquid fuel co-produced to the existing facility to render such repowering commercially viable.

Abstract: An integral cylinder liner and pump housing formed of a die cast aluminum workpiece of the type having a surface hardness extending a minimum depth into the workpiece, the housing further includng and integral pressure vessel and pressure control valve housing and fluid return path.

Abstract: A variable capacity vane compressor has a control element rotatable in response to the difference between suction pressure and control pressure for varying the compression starting timing and hence the capacity. A communication passage extends between the suction chamber and a high pressure chamber in which the control pressure is created. A spool valve opens and closes the communicating passage. An electromagnetic actuator generates an electromagnetic force to cause the spool valve to open the communication passage when energized. A control unit is arranged outside of the compressor and supplies the actuator with an external control signal for energizing the actuator.