Abstract: A reciprocal plunger fuel injection pump has a plunger having an enlarged head at one end. A spring abutment is secured to the head, and has a flange for engagement by the plunger return spring and a surface engageable with the end of the plunger. A spring clip has an apertured base portion engaged beneath the head of the plunger and arms which extend at right angles to the base portion. Some of the arms are turned inwardly to define a hook portion which locate in a groove formed in the spring abutment thereby securing the abutment to the plunger.

Abstract: In the preferred and illustrated embodiment of a reciprocating pump, a plunger for pumping a liquid, a piston for reciprocating the plunger and a selector valve for changing a pilot flow passage between a supply passage communicating a pressure chamber with a supply port and a discharge passage communicating the pressure chamber with a discharge port are disclosed. The selector valve is switched by a pilot valve means. A pilot valve body of the pilot valve means is so designed to engage with the piston for predetermined distances to and from the ends of the respective forward and backward strokes of the piston and to be moved to the switching position where the pilot valve body opens one of the pilot supply passage working against the selector valve and the pilot discharge passage and close the other of the pilot passages and the pilot valve body is released from engagement with the piston and held at the switching position for a predetermined distance after the stroke of the piston is reversed.

Abstract: A jet pipe comprises a housing having a suction inlet for the medium to be taken in and an outlet, a conical tubular portion following the suction inlet towards the outlet and a section adjacent to the suction inlet provided with discharge openings arranged peripherally around the tubular interior for a discharge of a highly pressurized medium. When such jet pipes are used for processing contaminated soil, the wear of the individual parts of the jet pipe causes high expenses and non-productive time. In order to reduce wear and non-productive time, the section comprising the outlet openings is formed as a replaceable ring.

Abstract: An apparatus for cooling components of an airplane engine at least partially operated by a cryogenically stored propellant via cooling air includes an air supply line for supplying the cooling air from an outside environment. A heat exchanger exchanges the cooling air with the propellant to precool the cooling air and includes a condenser having an in-flow and an out-flow side connected to the air supply line for precooling the cooling air. A pump is coupled to a cooling air line for conveying the precooled air in a liquid or vapor state to the components to be cooled wherein the cryogenically stored propellant acts upon the condenser. A propellant tank is connected to the in-flow side of the condenser and stores the cryogenically stored propellant, wherein the out-flow side of the condenser is connected to at least one combustion system of the airplane engine.

Abstract: In order to control engine operation by exhaust gas measurement, while avoiding operating conditions that exceed the safe maximum temperature limit, a gas turbine engine (10) includes a thermocouple temperature probe (28). The gas turbine engine (10) has a rotary compressor (12), a turbine wheel (14) coupled to the compressor (12) for driven movement thereof, and an annular nozzle (16) proximate the turbine wheel (14) for directing gases of combustion at the turbine wheel (14). It also includes an annular combustor (18) defining an annular combustion space (20) disposed about the turbine wheel (14) and in fluid communication with both the compressor (12) and the nozzle (16). The combustor (18) receives fuel from a source and air from the compressor (12) and it combusts fuel and air in the combustion space (20) to generate the gases of combustion.

Abstract: Turboramjet engine having a variable air intake, a ram air duct annularly enveloping the basic turbojet engine, and shutoff devices with which the ram air duct is energized with air when the basic turbojet engine is shut off and with which the basic turbojet engine is energized with air when the ram air duct is shut off. An air tract communicates with the air intake on a tubular duct carried axially on the basic turbojet engine and expands to an annular inlet section to the ram air duct. The shutoff devices are associated at least on the inlet side with quadrilateral sections of the tubular duct. As shutoff means for the inlet flow, use is made of an axially adjustable and internally swept sleeve valve and at least one flap that can be pivoted against a partial inlet area of the inlet section, which flap seals off the sleeve valve in lid-fashion when the inlet section is in a jointly exposed position.

Abstract: A disposable infusion apparatus includes proximal, distal and intermediate segments of IV tubing connected via couplings. The intermediate segment has a length sufficient for operative engagement with a pumping member of a peristaltic pump throughout a pumping stroke thereof. The intermediate segment further has a maximum Durometer of seventy-five on the Shore A scale. The pumping member includes a plurality of fingers mounted in side-by-side substantially parallel relationship for individual reciprocation. Motor driven cams individually reciprocate respective ones of the fingers in a predetermined timed sequence so that when the linearly disposed intermediate segment is squeezed by the fingers, intravenous fluid in the tubing will be pumped therethrough. The disposable apparatus further includes a door connected to opposite ends of the intermediate segment and which is releaseably loadable in a case to place the intermediate segment into operative engagement with the pumping member.

Abstract: A method of starting a gas turbine (10) having a combustor (12) and a fuel supply system (14) supplying fuel to the combustor in accordance with the invention includes turning on a fuel valve (40) to control fuel flow to the combustor for combustion after a first starting condition (100) is reached; and cyclically turning (116) the main fuel valve on and off when a sensed exhaust gas temperature (114) initially reaches a first set temperature and continuing to cyclically turn the main fuel valve on and off until the sensed exhaust gas temperature falls to a second set temperature (118) lower than the first set temperature or until a second starting condition (102) is reached.

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 an APU, and to effect operating transition from EPU to APU; and of a composite secondary power system with the IPU are all disclosed.

Abstract: To provide smoother operation of a gas-operated purge pump, the pump housing receives a standpipe closed by a low-density, floatable check valve element at the inlet of a standpipe within the housing. Periodically, at timed intervals, air is forced through an air conduit into the housing. If there is liquid in the housing, a check valve element floats upwardly because it is less dense than the liquid and mounted for movement to and away from the valve seat. While it is off of the valve seat, the air forces water into the standpipe and it moves upwardly until the chamber of the tubular pump housing is free of the liquid, at which time the check valve drops back into position and seats to prevent further flow of liquid. Upon termination of the pumping of gas pressure, the check valve in the pump housing inlet is free to move under the pressure of water in the well and the pump housing chamber again fills with fluid, causing the valve element to lift and permitting flow of water into the standpipe.

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 an APU, and to effect operating transition from EPU to APU; and of a complete secondary power system with the IPU are all disclosed.

Abstract: A method and apparatus for suppressing jet noise in a gas turbine engine powerplant 10 is disclosed. Various construction details are developed for providing sound suppression at sea level take-off operative conditions and not providing sound suppression at cruise operative conditions. In one embodiment, the powerplant 10 has a lobed mixer 152 between a primary flowpath 44 and a second flowpath 46, a diffusion region downstream of the lobed mixer region (first mixing region 76), and a deployable ejector/mixer 176 in the diffusion region which forms a second mixing region 78 having a diffusion flowpath 72 downstream of the ejector/mixer and sound absorbing structure 18 bounding the flowpath throughout the diffusion region. The method includes deploying the ejector/mixer 176 at take-off and stowing the ejector/mixer at cruise.

Abstract: Cooling air to the 1-2 turbine stage seal is supplied in parallel with air to the second vane surface 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. A thermocouple is located in a bypass around a portion of the seal, being radially installed through a hollow vane and an opening in the seal shroud.

Abstract: A pod for a very high bypass ratio turbofan engine unit of the forward contrafan type suspended from a suspension mast under the wing of an aircraft comprises a generally cylindrical inner cowling surrounding the casing of the jet engine unit and a generally cylndrical outer cowling spaced outwardly of the inner cowling and defining therebetween the cold flow path in which the contrarotating fan propellers are located, the outer cowling being divided into three parts consisting of an openable forward casing surrounding the fan propellers and connected to the suspension mast, an intermediate casing rigidly connected to the engine casing by radial flow straightener arms disposed in the cold flow path to the rear of the fan propellers, and an openable rearward casing also connected to the suspension mast. The engine unit is attached to the suspension mast by first attachment means carried on top of the intermediate casing, and second attachment means provided on the rear part of the engine casing.

Abstract: A metering pump wherein the head is provided with internal threads terminating adjacent to internal shoulders at each of the pump cylinder, inlet valve and outlet valve ports. The cylinder, inlet valve and outlet valve each include a flange secured to the shoulder by a collar threadably received in each of the ports. O-rings are provided in a circumferential groove in the body or cylinder of the pump inlet valves and outlet valves downstream of the flange. A piston pump structure includes a bushing mounted to the piston rod between the piston head and a second breakaway stop connected to the piston rod. The piston head includes a plurality of circumferential grooves for receiving respectively a cup seal or an O-ring seal. A suck-back mechanism is provided in a bore in the head and includes a stem having an eccentric cam which interacts with the valve structure to adjust the degree of closure by rotation of the stem.

Abstract: An exhaust assembly is provided for a gas turbine engine effective for propelling an aircraft from takeoff through subsonic and supersonic velocity. The exhaust assembly is effective for receiving exhaust gases discharged from an outlet of a core engine of an aircraft gas turbine engine. The assembly includes a casing, a variable area converging-diverging nozzle attached to the casing and including a first throat and an outlet for channeling exhaust gases received from the core engine. A plurality of retractable chutes are disposed upstream of the nozzle outlet and are positionable in a deployed position forming a converging nozzle having a second throat with a flow area less than that of the first throat. Means are provided for channeling air along aft facing surfaces of the chutes into the CD nozzle for mixing with the exhaust gases when the chutes are disposed in the deployed position for reducing noise from the exhaust gases.

Abstract: A thrust vectoring exhaust nozzle structure for an engine, such as a ramjet, rocket or turbojet, which generates thrust by expulsion of gaseous fuel combustion products along a thrust axis is described which comprises a generally axisymmetric housing defined along a central thrust axis including a wall structure defining an exhaust duct, and an axially spaced radially inwardly convergent portion, throat and radically outwardly divergent portion, and at least one airfoil disposed on the wall structure of the divergent portion and mounted for rotation about an axis substantially perpendicular to the thrust axis.

Abstract: A powerplant comprising a first compressor for producing a downstream axial flow, a second compressor positioned downstream of the first compressor and combustor positioned downstream of the second compressor. A first turbine is positioned downstream of the combustor and the first turbine is drivingly connected to the second compressor through a first shaft. A second turbine is positioned downstream of the first turbine and the second turbine is drivingly connected to the first compressor through a second shaft. The powerplant is connected to a load which is primarily rotary as opposed to a downstream axial thrust and the load is coupled to the second shaft. Further the invention includes a method of converting an aircraft turbofan engine having a fan, and a compressor for producing a downstream flow adjacent the fan, to a non-aeronautical application comprising the steps of removing a fan from a shaft of the engine and attaching a connection for attaching a load to the shaft from which the fan is removed.

Abstract: An ion thruster is operable in an interplanetary space with plasma generated by microwaves in a propellant atmosphere. A vessel defines first, second and third hollow spaces and a window between the first hollow space and the second and third hollow spaces, the second hollow space having an opening. A microwave generating unit generates the microwave in the first hollow space as a standing wave penetrating into the second and thid spacers hollow. A propellant supplying unit supplies the propellant into the second and third hollow spaces, the propellant serving as a main and neutralizing propellant and absorbing the standing wave to produce main plasma comprising main ions and main elecrons. An accelerating unit accelerates only the main ions into an ion beam to inject the ion beam through the opening into the interplanetary space. A neutralizing unit defines a third space which is in communication to the first space and into which the standing wave penetrates.

Abstract: A gas turbine includes a cooling air supply device for supplying compressed cooling air to moving blades, and a heat exchanger provided in the cooling air supply device for cooling the compressed cooling air. Compressed air withdrawn at an intermediate-stage portion of a compressor is used as a cooling medium for the heat exchanger. With this construction, the moving blades can be sufficiently cooled without the use of any special cooling medium.