Abstract: The present invention provides a valve for preventing contamination of a fuel management system connected to a pneumatic sense line by closing communication of compressed air from a scroll of the engine through a passageway in the valve to the pneumatic circuitry of the fuel management system. A detent is located on one side of the valve for receiving a raised surface on the knob of the valve and for holding the valve in the open position. A pair of stops on a camming surface separately engage a second pin on the valve to stop a handle of the valve from rotating past the selected open or closed position. The valve has all metal surfaces isolated so it may withstand vibrations. A method of washing a compressor of an aircraft engine is disclosed.

Abstract: The fuel spray bars and a compressor air bar is disposed in the cavities of the extended vanes of the turbine exhaust case to flow a fuel/air mixture perpendicular to the gas path and the pilot burner encased in the tail cone ejects a hot stream of combustion products adjacent the fuel air mixture to ignite the mixture and the ejected compressor air serves to create a recirculation zone adjacent the apertures of the spray bars to sustain combustion during the actuation of the augmentor.

Abstract: A coupling system for joining articulated fence segments at a desired relative angle.

Abstract: A turbine nozzle support assembly includes nozzle segments each having an inner band with an integral retention flange extending radially inwardly therefrom. A plurality of retention tabs extend radially inwardly and are spaced axially aft of the retention flange to define a capture slot therebetween. A nozzle support includes a radially outwardly extending upper flange having a plurality of support pins extending axially, forwardly therefrom and disposed in complementary retention apertures in the retention flanges of the nozzle segments. A retention key is disposed in the capture slot axially between the upper flange and the retention tabs for axially retaining the nozzle segments on the nozzle support.

Abstract: An integral, one-piece afterburner structure for a turbojet engine is disclosed which is formed of composite material. The afterburner structure has an outer casing formed as a body of revolution about a central axis, an inner casing also formed as a body of revolution about the central axis, which casings are integrally joined by a plurality of connecting arms extending between the inner and outer casing. The connecting arms are also formed of a composite material and are integrally molded with both the inner and outer casings. The afterburner structure also has a plurality of secondary support arms formed of composite material which extend either from the outer, or the inner casing in a generally radial direction relative to the central axis. Integrally formed with the plurality of secondary support arms is at least one annular flameholder ring which extends around the central axis and is supported by the secondary support arms.

Abstract: A burner for gas turbine engines is provided in which a ring-shaped swirling device is coaxially assigned to a fuel nozzle. The swirling device forms tangential ducts for an adjustable feeding of combustion air between profiled surfaces arranged along the circumference. Two components, which are axially adjustable relative to one another, are to form, on mutually opposite faces, the ducts between profiles and recesses which are arranged offset relative to one another along the circumference, in such a manner that, when at least one component is adjusted, the profiles can be moved into the recesses for a reduction of the duct cross-sections or can be moved out of the recesses for an enlargement of the duct cross-sections.

Abstract: A fuel injection system is disclosed which incorporates a plurality of bowl or shroud members extending upstream of an end wall of the combustion chamber between the end wall and an air swirler in which the shroud member has an end joined with the end wall of the combustion chamber having a substantially elongated elliptical cross-sectional configuration. The end wall of the combustion chamber defines an elliptical shaped opening corresponding to the shape of the end of the shroud or bowl member to enable the fuel/air mixture to be atomized as it enters the combustion chamber. The bowl or shroud member may also define a plurality of openings to enable additional air to be mixed with atomized fuel cone.

Abstract: A method and assembly are effective for air-starting an aircraft gas turbine engine having a fan powered by a low pressure turbine through a first shaft, and a compressor powered by a high pressure turbine through a second shaft disposed coaxially therewith. A gear train is selectively operatively joined between the first and second shafts by selectively engaging a first clutch for transmitting torque through the first clutch only in one direction from the first shaft to the second shaft when the fan is windmilling for driving the second shaft to allow an air-start of the gas turbine engine during flight. In a preferred embodiment, a second clutch is operatively joined to the gear train and is selectively engageable at speeds of the second shaft below a predetermined release speed, and disengageable at the release speed and above for disconnecting the air-start assembly once the engine has been started.

Abstract: A composite/metal hybrid rocket motor case made by rolling sheets of continuous, unidirectional fiber reinforcement pre-impregnated with an uncured, thermoset or thermoplastic resin about the mandrel using a tube rolling machine to form a liner having discontinuous layers of fiber reinforcement. The liner is inserted into a metal shell configured with elongated slots. A mold is placed around the shell with a bladder placed within the liner. The bladder within the mold is then pressurized to force the liner against the metal shell while the contents of the mold are heated. As the liner cures, it bonds to the shell. Fins, launch lugs, domes and bulkheads may be attached to the metal shell by known attachment methods.

Abstract: A highly efficient partial oxidation process with the production of power comprising the steps of producing fuel gas by the partial oxidation of hydrocarbonaceous fuel, cooling said fuel gas at high pressure by quenching in water to produce quenched fuel gas and by indirect heat exchange with BFW to maximize the production of IP and MP steam, cleaning said fuel gas, preheating scrubbing water comprising process condensate and make-up water by direct contact and direct heat exchange with clean fuel gas and using said preheated scrubbing water in the cleaning of said fuel gas, reducing the pressure of said cooled fuel gas stream prior to heating water for fuel gas saturation, cooling the process fuel gas stream in stages and condensing water for use as said scrubbing water, purifying the process fuel gas and saturating it with water, and burning said purified and saturated fuel gas in the combustor of a power-producing gas turbine along with saturated nitrogen to produce exhaust gas with a reduced NO.sub.x.

Abstract: This invention provides a method to mix a relatively large amount of non-condensable gas with fuel prior to gasification heating thus reducing the residence time of the fuel adjacent to hot surfaces. The non-condensable gas may be air, a cryogenic such as methane, or a chemical fraction of the gasified fuel which by itself does not promote the formation of significant amounts of gums or coke deposits.

Abstract: A rocket engine protection system for a recoverable rocket booster which is arranged to land in a salt water body for recovery. The system includes an inflatable water impermeable elastomeric bladder that may be fabricated of a silicone impregnated woven Kevlar material and which is stowed in a deflated condition on a rotatable arm that is journalled to the lower portion of the nozzle of a liquid rocket booster. The deflated bladder and the rotatable arm are protected by a pod cover that is hinged to the outer portion on the nozzle. During the controlled descent of the liquid rocket booster by parachute for landing in a salt water body the pod cover is released and opened upwardly by a gas cylinder actuator. The rotatable arm which is biased by a torsion spring is then permitted to rotate around to position the deflated bladder in a deployed position within the interior of the lower portion of the nozzle. The bladder is then inflated to form a plug within the nozzle.

Abstract: An annular combustor for a gas turbine engine having a rotatable fuel slinger has a first plurality of effusion cooling holes for directing air flow radially inwardly toward said fuel slinger and circumferentially in the direction of rotation of the fuel slinger and a second plurality of effusion cooling holes on the opposite side of the fuel slinger for directing air radially inwardly and circumferentially in the direction of rotation of the fuel slinger, thereby to produce a pair of annular axially spaced helical air flow patterns having a confluence in the direction of fuel flow radially outwardly from the fuel slinger.

Abstract: A counterrotating turbine support assembly includes outer and inner rotors having respective outer and inner blades disposed in an outer casing. A mid-frame is disposed forwardly of the rotors and fixedly joined to the outer casing. A rear frame is disposed axially aft of the rotors and is fixedly joined to the outer casing. A forward support shaft is joined at one end to a forward end of the outer rotor and is rotatably supported at an inner end to the mid-frame by a forward bearing. An aft support shaft is joined at one end to an aft end of the outer rotor and is rotatably supported at an inner end to the rear frame by an aft bearing. An intermediate support shaft is fixedly joined at one end to the inner rotor and is rotatably supported at an inner end to the mid-frame by an intermediate bearing.

Abstract: A flywheel engine includes a flywheel body made up of laminated disks, pressed one into another on a central drive shaft. Individual ones of the disks are stamped with recesses which accommodate jet or rocket propulsion housings, electrical wiring, and fuel delivery passages. The propulsion housings are removably mounted in the flywheel body to permit interchange with other propulsion devices according to thrust requirements. The propulsion housings are oriented to produce thrust on thrust axes that are substantially tangential to the rotational path of the flywheel body edge surface. Fuel and combustion supporting oxygen are delivered to the individual propulsion housings through the central shaft.

Abstract: A lubrication system for a gas turbine engine includes first and second coaxially rotor shafts having at least one differential bearing disposed in outer and inner seats thereof. An annular first scoop extends axially from a first portion of the first shaft, and an annular second scoop extends axially from the inner seat of the second shaft. A plurality of first holes extend axially through the first shaft and radially below the first scoop, and a plurality of second holes extend axially through the inner seat of the second shaft and below the second scoop. An annular first shell extends axially between the second scoop and the first shaft from above the first holes. And, oil is injected under the first scoop for flow by centrifugal force from rotation of the first shaft through the first holes and along the first shell into the second scoop for flow through the second holes to lubricate the bearing.

Abstract: An exhaust gas turbocharger having rotor runners disposed in roller bearings protects the roller bearings from shocks and vibrations by a pressure-oil-filled oil film damper. By a shut-off device arranged in the main lubricating oil duct, the lubricating oil supply of the roller bearings is shut off when the rotor runners are stopped. However, the pressure oil supply of the oil film damper remains operative so that the oil film damper retains its operability.