Abstract: A fuel nozzle guide and method of assembly/disassembly is disclosed with the nozzle guide having a frusto-conical hub section, an annular base, a pair of retaining tabs for securing the guide to the outer wall of a combustor bulkhead for limited movement relative to the bulkhead, and a radial inflow swirler. The method of assembly/disassembly comprises assembling/disassembling the nozzle guide in the bulkhead from the outer wall (cold) side of the bulkhead and mechanically connecting/disconnecting the nozzle guide to/from the outer wall of the bulkhead with mechanical fasteners.

Abstract: A Compact blower is provided having a housing defining an engine compartment, cooling air compartment and a volute chamber all coaxially aligned along a vertical axis. An internal combustion engine is oriented within the engine compartment with a vertically aligned output shaft and a forwardly facing fin cylinder. The rotary impeller is affixed to the engine output shaft provided with a plurality of cooling air pump blades projecting upward from a circular disc and oriented within the cooling air pump compartment. The impeller is further provided with a plurality of blower fan blades which project outwardly into the volute chamber. The rotation of the impeller causes air to be drawn into the volute chamber and discharged through the blower air discharge port. Cooling air is drawn through the cooling air pump compartment and directed across the engine and cylinder and ultimately discharged through an upper front portion of the engine compartment in a direction away from the operator.

Abstract: A stream of primary gas flowing through a bi-stable thrust vectoring nozzle becomes attached to a first or second surface extending downstream of the nozzle, each surface incorporating one or more control ports for controlling to which surface the stream is attached, wherein relative to the longitudinal axis of the nozzle, the angle of discharge from the first surface is substantially different from the angle of discharge from the second surface, preferably with the first surface substantially aligned with the longitudinal axis of the nozzle. In one embodiment, a plurality of nozzles are arranged with the respective first surfaces substantially aligned with the longitudinal axis of the nozzle combination and each of the respective second surfaces arranged to laterally deflect a respective portion of the stream of primary gas in a respective direction along each of two orthogonal lateral axes.

Abstract: A scroll compressor has a pair of scroll members which compress a fluid as the fluid moves through pockets created by the scroll members. The fluid moves from a suction pressure zone to a discharge pressure zone. A chamber is defined by one of the scroll members. The chamber is in communication with a pocket located between the suction and discharge pressure zone such that an intermediate pressurized fluid is supplied to the chamber through a fluid passageway. The fluid passageway is designed to allow a large flow from the pocket to the chamber and a small flow from the chamber to the pocket. This dual flow capability reduces the pressure pulsation in the chamber. In one embodiment, a capacity control mechanism is associated with the compressor to vary the capacity of the compressor.

Abstract: Plugs for protecting internal spaces of rocket combustion chambers against moisture, dust, and other environmental factors. Each plug includes a central rod with a bracket fastened to it. The plug also includes a sleeve with radially extending structural ribs. Spring-loaded cams with rollers are securely hinged at the ends of the ribs. In addition, a spring-loaded limiter and a valve are mounted on the central rod so that they can possibly move relative to the central rod. The limiter includes a sleeve and a conical shell that are connected by rod ties. The valve includes a metal stamped conical plate that forms a gas-tight fit with the rod. A sealing ring of elastic material is positioned on a peripheral part of the plate. The set of spring-loaded cams and the limiter secure the self-mounting plug in a working position and make the valve operation independent of the operation of other plug components.

Abstract: A foil bearing assembly for use in a gas turbine engine is provided. The assembly includes an annular bearing carrier mounted to the housing of the engine. An annular foil carrier disposed within the bearing carrier and carrying a plurality of overlapping foils that engage an outer surface of a journal. The journal is mounted to the rotating assembly of the engine to define a cavity. Disposed in the cavity is a showerhead having an inlet for receiving a flow of cooling air and a plurality of orifices for providing impingement cooling of the inner surface of the journal. The use of a showerhead in a thrust foil bearing is also disclosed.

Abstract: An axially symmetric turbojet-engine exhaust nozzle which is directable as a unit. The exhaust nozzle is situated downstream of an exhaust duct (1) fitted with a spherical wall (5). A single control ring (12) driven by linear actuators (30) allows regulation of the nozzle cross section and direction. Converging flaps (7) are guided on an upstream side by the spherical wall (5) and are supported at a downstream side by a control lever (13) which hinges on the control ring (12) and rests upstream on an external surface (16) of the spherical wall (5). Diverging flaps (10) hinge on the converging flaps (7) to form an inner ring of hot flaps. The diverging flaps (10) are situated downstream in an extension of the converging flaps (7) and further hinge on an outer ring of cold flaps (11), which in turn hinge on the control ring (12).

Abstract: A method for the separation of a feed gas mixture comprising oxygen and nitrogen in which an oxidant gas and fuel are combusted in a combustion engine to generate shaft work and a hot exhaust gas, the feed gas mixture comprising oxygen and nitrogen is compressed, and the resulting compressed feed gas mixture is separated into two or more product gas streams with differing compositions. The shaft work of the combustion engine is utilized to provide at least a portion of the work required for compressing the feed gas mixture, one of the product gas streams by is heated by indirect heat exchange with the hot exhaust gas from the combustion engine, and the resulting heated product gas is work expanded to generate shaft work and yield an expanded product gas stream. The combustion engine may be a gas turbine combustion engine.

Abstract: Liquid fuel purge device uses water, not compressed air as in the prior art, thereby prevented are rapid load change of gas turbine due to sudden discharge of liquid fuel and coking of remaining liquid fuel. Upon supply of liquid fuel to fuel nozzle (05) being stopped, water purge system (15) having stop valve (16) supplies water into fuel system including liquid fuel system (08) and fuel nozzle (05) and liquid fuel remaining therein is purged by water into combustion chamber (013) from the fuel nozzle (05).

Abstract: A burner arrangement (20) for a gas turbine comprises an interior space (22) enclosed by a casing (23), in which interior space (22) at least one burner (21) is arranged, and into which interior space (22) in each case a jet (26, 27) of a gaseous medium, in particular air, is sprayed through at least two nozzle openings (24, 25) against the direction of flow of the burner (21) and along the inner wall (23a) of the casing (23) which jets (26, 27), guided by the inner wall (23a), meet one another from opposite directions and combine to form a secondary flow (28) flowing off perpendicularly from the inner wall (23a). In such a burner arrangement, the flow is stabilized and evened out by virtue of the fact that, to establish the impingement point of the jets (26, 27), a dividing plate (29) arranged in the flow path of the jets (26, 27) and disposed essentially perpendicularly to the inner wall (23a) is provided.

Abstract: Three vectoring ring support and actuation apparatuses are disposed in an equi-angular manner circumferentially about the engine casing. Each of the vectoring ring support and actuation apparatuses includes a vectoring ring means to transfer side loads from the vectoring ring to the engine casing, a vectoring ring translation means for allowing the ring to be translated, and a support pivoting means and ring gimballing means to allow the vectoring ring attitude adjustments by a set of linear actuators. The vectoring ring support apparatus transfers side loads acting on a vectoring ring and generated by a gas turbine engine thrust vectoring nozzle to a relatively stationary portion of the engine and allows tilting of the vectoring ring to vector the thrust of the nozzle.