Abstract: An enclosed pump motor includes an aluminum housing made by an impact extrusion process. The housing is cylindrical having an integrally-formed closed end with integral fastener bosses for attaching a pump thereto and an integrally-formed thickened cylindrical portion defining a shaft bore for receiving the motor shaft therethrough. At the other end, the cylindrical housing is open for receiving the motor therein. A motor cover is attached to the motor receiving end of the housing by crimping or bending a part of the housing into indents formed in the housing. The motor cover includes a threaded bore adapted to receive a threaded grommet wherein three connector pins are imbedded. The connector pins are connected to electrical power carrying conductors and/or switch conductors leading to a fluid level sensor switch. The conductor-to-pin connections are imbedded within the grommet and are hermetically sealed therein.

Abstract: A gas turbine jet engine is disclosed with a fan delivering into a bypass duct to generate mainly propulsion thrust, and with a thrust reversing device having flaps which for reverse thrust operation pivot into the fan air stream and cooperate with an axially extended extreme section of the outer wall of the bypass duct to uncover delection ports arranged at breakthroughs in the outer wall. The extreme section of the outer wall and the thrust reverser flaps are linked one with the other for relative movement between them such that in a first phase of actuation relative to a fixed extreme nozzle section, the extreme section provides an additional fan nozzle area which communicates with the inlet flow areas formed by the flaps relative to the bypass duct.

Abstract: A rocket injector is provided with multiple sets of manifolds for supplying propellants to injector elements. Sensors transmit the temperatures of the propellants to a suitable controller which is operably connected to valves between these manifolds and propellant storage tanks. When cryogenic propellant temperatures are sensed only a portion of the valves are opened to furnish propellants to some of the manifolds. When lower temperatures are sensed additional valves are opened to furnish propellants to more of the manifolds.

Abstract: A gas turbine combustor including a first-stage combustion chamber being arranged to serve as a premix chamber for a second-stage combustion chamber and an auxiliary burner provided in the first-stage combustion chamber and arranged to effect, when fired, combustion and holding of a flame in the first-stage combustion chamber and to effect, when extinguished, feed a flame from the first-stage combustion chamber to the second-stage combustion chamber; and a method of driving the gas turbine combustor including a step of preparing the auxiliary burner in the first stage combustion chamber, the auxiliary burner being sparked when said combustion is fired, and causing the first-stage combustion camber to serve as the premixing chamber for the second-stage combustion chamber by extinguished the auxiliary burner.

Abstract: A propulsion system for a reusable spacecraft is disclosed having turbojet, amjet and rocket modes of operation. Hydrogen or exhaust gases from a gas generator drives a gas turbine which powers an air compressor in the turbojet mode. An injection device injects hydrogen and exhaust from the gas driven turbine in the combustion chamber in the turbojet mode. In the ramjet mode, only hydrogen is injected into the combustion chamber. In the ramjet mode, hydrogen and oxygen are supplied to the rocket motor. An adjustable nozzle is provided to form a variable throat convergent-divergent nozzle in the turbojet and ramjet modes and to form a divergent nozzle in the rocket mode.

Abstract: A steam power plant for producing energy from tarry residual oils from a refinery includes a steam generator as well as a combustion system heating the steam generator and having a fuel side. A fired tubular furnace for heating high-viscosity refinery residues to 400.degree. to 600.degree. C., for instance, produces gaseous and vaporous products and other components of the residue. A separating column connected downstream of the fired tubular furnace separates the gaseous and vaporous products from the other components of the residue. The separating column has a lower end and an outlet line at the lower end connected upstream of the fuel side of the combustion system for the other components of the residue.

Abstract: A power source (14) rotates an eccentric (20) engaged within the center of a relatively large drive roller (22) to rotate the drive roller while simultaneously orbiting the center of the drive roller about a circular path so as to cyclically advance and retract from piston assemblies (24) located within pump assemblies (16a-16d). Rotation of the eccentric (20) causes each piston assembly (24) to cyclically advance against and retract from a flexible diaphragm (26) to cause fluid entering the pump assembly to be forced out under pressure. Each diaphragm (26) is "backed" by a spring-loaded support (27) that resiliently pushes against the side of the diaphragm opposite the piston assembly.

Abstract: A rocket motor having case segments which are attached together. A retaining member extends circumferentially thereabout to maintain attachment of the segments together. The retaining member is characterized by sensitivity to a predetermined temperature greater than ambient temperature and less than the ignition temperature of propellant material in the rocket motor to lose strength whereby the retaining member is released and the rocket motor may safely be rendered non-propulsive during a hazard such as a fuel fire or slow cook-off.

Abstract: A fuel injection pump for internal combustion engines, having a piston driven for simultaneous reciprocation and rotation and embodied both as a pump piston periodically pumping fuel and as a distributor piston rotatable in the guide bore. The piston includes distributor openings that discharge at its jacket face and communicate with various injection nozzles as a function of the rotational position of the distributor piston. During the supply stroke of the pump piston, a branch line is connected to the work chamber of the pump piston, which branch line is connectable, via separate distributor openings of the distributor piston with at least one injection nozzle different from the injection nozzle connected directly, via a different distributor opening to the work chamber (5).

Abstract: In an apparatus having a radial piston device, in particular a radial piston pump or motor or the like, a pump body rotates around a control tap. Radially moving pistons are supported in the pump body and with the control tap define a pumping chamber for a fluid medium. This pumping chamber can be connected to both an intake bore and a pressure bore. Further, pressure zones are found on the jacket face of the control tap, between the control tap and the pump body, so that as a result the pump body is mainly supported by hydrostatic forces. These pressure zones are intended to comprise intersecting conduits, with segments of the jacket face remaining between them.

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 communication 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: A rocket motor that has a solid propellant with closure means that is secd to the rocket motor housing by heat responsive means that melts before the solid propellant ignites to prevent the rocket motor from becoming propulsive when subjected to excessive external heat sufficient to cause the rocket propellant to ignite.

Abstract: A portable, hand-held blower/vacuum unit has a housing structure defined by an upper engine shroud removably connected to the top wall of a lower impeller housing. Disposed within the shroud is a small internal combustion engine having a vertical crankshaft which extends downwardly through a depending well section formed on the top wall of the impeller housing, the lower shaft end being drivingly connected to a centrifugal fan impeller positioned within the impeller housing and operative to force a flow of ambient air therethrough. The engine is resiliently and floatingly mounted within the shroud by a resilient support system which prevents rigid contact between the engine and the shroud or the impeller housing to thereby substantially reduce engine vibration transmitted to the housing structure, and permit deflection of the engine relative to the housing structure to lessen the possiblity of engine damage caused by impeller impact from ingested objects.

Abstract: A fluid injection system is disclosed. The fluid injection system incorporates an injection pump comprising an adjustable restriction device that is used to control the extent of the movement of the pumping mechanism in the injection pump. An adjustable gauge and an adjustable marker are used to accurately calibrate and accurately position the adjustable restriction device. When the adjustable restriction device is accurately calibrated and correctly positioned, a precise amount of additive is injected into the pipeline.

Abstract: An improved method of starting cyclic char fuel reaction plants is described wherein during compressor cranking for starting compressed air is heated by burning with a liquid fuel and then enters the pore spaces of the char fuel within the char fuel containers in order to increase the temperature of the char fuel to where it reacts rapidly with air.

Abstract: An arrangement for the supply of propellant for the propulsion systems of a satellite has a main fuel tank, a main oxidizer tank and an additional or auxiliary oxidizer tank. The auxiliary oxidizer tank becomes effective when the oxidizer in the main tank has been used up at the end of the useful life of the satellite. At that time the additional oxidizer is used to bring the satellite into a retirement orbit out of the way, so to speak, to reduce the crowding in the range of desirable orbits. For this purpose, the emptiness of the main oxidizer tank is sensed by a sensor for providing a control signal which closes the main supply line, thereby switching on the auxiliary tank for propelling the satellite into the retirement orbit.

Abstract: In a variable displacement vane-type rotary compressor, a rotational displacement of an adjust member relative to a front member fixedly closing a front end of a cam ring varies a compression starting point of a rotary vane in a working chamber formed in the cam ring. The front member is formed with an induction port and a bypass port, and the adjust member is formed with a bypass recess. The induction port and the bypass recess are in communication with each other in the working chamber irrespective of a position of the vane under all of the rotational displacement of the adjust plate to establish a communication between the induction port and the bypass port in the working chamber irrespective of the position of the vane when the bypass port overlaps with the bypass recess.

Abstract: An auxiliary-overload-bypass valve in a fluid-delivery system including a pump having its own internal, relatively low-volume-capacity bypass valve. The auxiliary valve relieves a defined high pressure condition which can occur in the system when the pump is overworking and the system is not delivering fluid. The valve includes a valve body with an inlet coupled to the system downstream of the pump and an outlet coupled to the system upstream of the pump. Disposed inside the body is a valve-opening mechanism for allowing fluid to pass through the valve to relieve the high pressure condition.

Abstract: A variable capacity type swash plate compressor has a shaft, a swash plate, pistons functionally connected with the swash plate, and a detector for detecting the reciprocating stroke of the piston. The reciprocating stroke of the piston is varied in accordance with an inclining angle of the swash plate in such a manner that a top dead point of the piston at a working chamber defined at one end of the piston is substantially constant. The detector detects the change of the width of the reciprocating stroke of the piston and calculating the capacity of the compressor. The detector employs a plurality of magnets provided on a center portion of the piston and an electromagnetic sensor provided on a cylinder block for facing to the magnets.

Abstract: In a reheat system of an aircraft gas turbine engine there is provided a cantilever mounting for a ceramic tubular flameholder 10 on a metal bracket 11, the bracket being provided with a face having an upstanding annular flange 16 adapted to mate with the outer surface 19 of an end portion of the flameholder, there being further provided fastener means 12 adapted to retain the end face of said end portion of the flame holder adjacent and facing said face of the bracket, characterized in that said end portion of the flameholder is provided by a frusto-conical section 27 having first and second surfaces 18, 19 of different angles such that line extensions of each surface coincide at respective imaginary vertices on the axis of the flame holder.