Abstract: Improved control over the production of motive gas applied by a nozzle (16) to a turbine wheel (10) may be achieved by a method of (a) supplying fuel to a combustor (20), (b) simultaneously with the performance of step (a), supply insufficient oxidant for the fuel through a path (90) to the combustor (20), and (c) simultaneously with steps (a) and (b), supplying additional oxidant sufficient to effect desired combusiton of the fuel to the combustor (20) via a path (92) and at a variable rate.

Abstract: In order to optimize ignition capabilities, while at the same time enhancing the life span of an igniter, a stored energy combustor (10) has an igniter (34) disposed within a fuel injector (26). The fuel injector (26) is disposed in a tubular extension (16) leading to a combustion chamber (20) and has a discharge end (28) communicating with a point of entry into the combustion chamber (20). An oxidant inlet port (24) is provided upstream of the combustion chamber (20) for directing oxidant into the combustion chamber (20). The oxidant inlet port (24) directs oxidant through the tubular extension (16) leading to the combustion chamber (20) in surrounding relation to the fuel injector (26). With this arrangement, the igniter (34) is disposed within the fuel injector (26) along a longitudinal axis (22) of the stored energy combustor (10).

Abstract: The high cost of a fuel injection system in a turbine engine may be substantially reduced by utilizing a combination manifold/fuel injector (80) that is formed of a flattened tube (82) of annular shape and disposed within the case (58) of the engine in substantially surrounding relation to an annular combustor (44). The flattened tube includes fuel injecting apertures (88, 100) which need not be precision formed but which are aligned with the flared ends (74) of inlet tubes (70) extending into the combustor (44) from the plenum defined by the space between the combustor (44) and the case (58).

Abstract: The weight of a start cartridge in a cruise missile (10) of the type having a booster rocket (60) for initiating flight and a thrust producing gas turbine (12) for sustaining flight may be eliminated by placing the gas outlet (62) for the rocket engine (60) in ducting (64, 82) downstream of the gas turbine engine exhaust (20) so that operation of the rocket (60) to initiate flight of the missile (10), through eduction, draws sufficient air through the engine (12) to accelerate the same to starting speed.

Abstract: Inexpensive cooling of a gas turbine nozzle and shroud assembly (62, 66, 76) is obtained by locating cooling air passages (84) in the vanes (76) forming part of the nozzle structure (62, 66, 76) so as to allow cooling air to flow between the shrouds (62 and 66).

Abstract: A first annular seal (46) is mounted on the housing (10) and extends into the space (32) between the compressor (26) and the turbine wheel (16). The seal (46) includes a main sealing and support section (54) adjacent the compressor (26) and an insulating section (86) adjacent the turbine wheel (16). The insulating section (86) is mounted on and generally spaced from the main support section (54). A peripheral groove (66) opens axially towards the turbine wheel (16) and is located at a radially outer extremity of the first seal (46). The groove (66) includes a first and second wall, with the first wall (70) located radially inward of the second wall (78). A mounting element (68) is attached to a radially inward side (69) of the first wall (70) to form a gap (75) between the first wall (70) and the mounting element (68). A second annular seal (74 ) includes an inner and outer edge.

Abstract: A method of starting a gas turbine engine eliminating the need for oversizing a starter motor or the like to attain a proper transition through the "pinch point" includes the steps of applying a torque from an external source to the gas turbine engine (10) to accelerate the same toward a self sustaining speed, igniting fuel in the engine (10) at a pre-determined speed less than the self-sustaining speed, and at or about the time of fuel ignition, momentarily increasing the torque applied to accelerate the engine (10). The acceleration torque and momentary increase can be achieved by applying torque from a gas turbine containing auxiliary power unit (20) to an engine (10) either mechanically or pneumatically and then overspeeding and/or increasing the turbine inlet temperature of the gas turbine within the APU (20) to achieve a momentary burst of torque.

Abstract: Processes using high temperature thermoplastic polymers in the in-situ fabrication in the formation of foamed composite sandwich or foam articles often result in weak unsound products which may be avoided by utilizing a high temperature thermoplastic in powder form (22), a blowing agent having a high decomposition temperature (24), and, if desired, reinforcers and/or fillers, (28), mixing the thermoplastic, blowing agent and reinforcer and fillers (30), placing the mixture in a mold and, if forming a composite structure, in abutment with at least one skin (34), and applying sufficient heat and/or pressure to the mold and its contents to melt the thermoplastic and generate gas within said mixture by decomposition of the blowing agent (38). Also, an activator may be included with the blowing agent which promotes the production of gas (26). The thermoplastic should be free from any material which will react with the blowing agent or the activator at temperatures below the melting point of the thermoplastic.

Abstract: Manifold head effects at low fuel flows in a fuel injected air breathing turbine are minimized by utilizing fuel injectors having fuel injecting tubes (66) with open ends (70) for fuel injection and provided with elongated capillary tubes (88) upstream thereof and connected to receive fuel from a fuel manifold (48) having an inlet (56) while uniform, relatively low velocity fuel exit flow from the ends (70) the injecting tubes (66) is achieved through the use of internal impingement surfaces (96, 102, 106, 110, 124). Pressure loss differences contributing to nonuniform fuel flow and resulting from some fuel injecting tubes (66) be more distant from the manifold inlet (56) are minimized by shortening the length of the capillary tubes (88) furthest from the manifold inlet (56).

Abstract: A column for removing a gas from a gas-containing liquid using a stripping gas has an enclosed shell having a side wall defining an inner periphery and a top and a bottom. A gas containing liquid inlet is provided proximate at the top of the shell for introducing a gas-containing liquid into the column. At least two adjacent parallel spaced apart substantially planar sieve plates, each sieve plate being oriented transverse the side wall of the shell and having an edge conforming substantially to the inner periphery of shell, are provided within the shell. The seive plates are perforated to facilitate the passing of the gas-containing liquid therethrough. A stripping gas inlet causes a stripping gas to flow between the adjacent sieve plates. Baffles are provided between adjacent sieve plates for directing the stripping gas to flow in a torturous path, the path being parallel to and between planes formed by the sieve plates.

Abstract: A release mechanism for facilitating launching a spin-stabilized self-propelled missile, which includes a rotary missile support and a launching support for supporting the rotary missile support for rotation about a spin axis and for movement axially of the spin axis. A nozzle assembly extends between the rotary missile support and the missile coaxial with the spin axis. A separable portion of the nozzle assembly moves axially in an aft direction under the influence of exhaust gases expelled by the missile. The separable portion strikes an abutment on the rotary missile support to effect rapid movement of the rotary missle support axially away from the missile on separation of the separable portion of the nozzle assembly. A low friction bearing is provided for engagement by the rotary missile support at its aft limit position of travel away from the missile to reduce spin momentum induced forces caused by the rotary missile support.

Abstract: In order to assist in starting a gas turbine engine (10), hot pressurized exhaust gases are supplied through relatively large hot gas supply tubes (22) for direct impingement on turbine blades (14) to drive a turbine rotor (12). The relatively large hot gas supply tubes (22) are located in immediate proximity to a flame zone (32) of a combustor (16). This proximate location of the relatively large hot gas supply tubes (22) facilitates diversion of a small amount of hot pressurized, exhaust gases to the flame zone (32) through a flow control orifice (28) for the purpose of initiating ignition in the combustor (16) wherein the BTU energy of the exhaust gases is transferred to the combustor (16) during the starting thereof. The relatively large hot gas supply tubes (22) ensure a high mass flow rate of hot pressurized exhaust gases with some being directed to the flame zone (32) in a manner minimizing heat loss which enhances ignition reliability.

Abstract: Electric motor cooling difficulties in a ducted axial flow electric fan construction are avoided through the use of a duct-like housing (10) having an interior wall (30) with axially spaced feet (34), (40) within the housing (10) and radially inward of the interior wall (30). A motor stator (88) is located within the housing (10) and is engaged by the feet (34) and (40) to be mounted in spaced relation to the interior wall (30) with its exterior surface (98) between the feet (34), (40) and facing and exposed to the interior wall (30). A rotor (84) is journalled within the stator (88) and mounts an impeller (52) which drives ambient gas through the housing (10) in contact with the exterior surface (98) of the stator to cool the same.

Abstract: In order to avoid plugging the air passageways (42a) of fuel injectors (42) with carbon particles or lumps in a gas turbine engine (10), the gas turbine engine (10) includes an annular combustor (18) having radial dilution air injection. The gas turbine engine (10) also includes a rotor (12) having turbine blades (14) and a nozzle (16) adjacent the turbine blades (14) which is adapted to direct hot gases of combustion at the turbine blades (14) to cause rotation of the rotor (12). The annular combustor (18) is disposed about the rotor (12) and has an outlet (20) to the nozzle (16), spaced inner and outer walls (22 and 24), and a generally radially extending wall (26) connecting the inner and outer walls (22 and 24). The gas turbine engine (10) further includes a housing (28) substantially surrounding the annular combustor (18) in spaced relation to the inner, outer, and radially extending walls (22, 24 and 26) to define a dilution air flow path (30).

Abstract: In order to reduce weight while also minimizing volume and pressure drop in a combustor assembly (18) for a turbine engine, the combustor assembly (18) includes an annular combustion chamber having a combustion space (20) defined entirely be an annular combustor case (22). The combustion chamber (18) is adapted to combust fuel and air in the combustion space (20) to generate gases of combustion. It has a combustor outlet (26) leading to a turbine nozzle (16). The outlet (26) is defined by a pair of turbine shrouds (28, 30). It also has a combustor inlet (32) leading to the combustion space (20). The combustor inlet (32) is defined by the combustor case (22) and one of the turbine shrouds (28). The combustion chamber (18) is adapted to receive injected air at the combustor inlet (32) in a manner creating a generally annular air flow in the combustion chamber (18) about the combustor case (22).

Abstract: In order to visually monitor all aspects of a breathing circuit, a visually monitored anesthesia breathing circuit is disclosed. The circuit includes a transparent absorber having a disposable single use cartridge with particulate carbon dioxide absorbent material therein. The disposable single use cartridge is also formed of a transparent material and is removably positioned within the absorber. The circuit also includes a visual indicator associated with the disposable single use cartridge for indicating the extent of depletion of carbon dioxide absorption potential of the carbon dioxide absorbent material. The absorber includes an expiratory valve in communication with the disposable single use cartridge and an inspiratory valve in communication with the absorber. The circuit further includes fittings for delivering an anesthetic and/or oxygen to a patient in a metered flow.

Abstract: A casting type fishing reel is disclosed and includes a spool having a transverse spool shaft and a frame about the area of the spool. The frame includes a plurality of spacer posts joining a pair of side frame plates and interengaged to maintain the frame plates in conjoint alignment and to provide easy separation and assembly of the frame plates. A clutch mechanism is provided for selective actuation to move a spool pinion gear out of engagement with the spool shaft, and automatically re-engages the pinion gear in response to rotation of the reel handle. A magnetic drag mechanism is provided and recessed within a side cover of the reel. The reel handle, the main gear train of the reel and an anti-reverse ratchet-pawl mechanism all are mounted as a unitary assembly on a side cover for the reel whereby the cover can be removed from the reel for access to the gear train and other interior reel components without removing the handle.

Abstract: A system comprising a high pressure gas reservoir, a turbine, a compressor, a low pressure reservoir, a heat exchanger and flow control structure such as valves, etc. The high pressure reservoir is in heat exchange relationship with ambient air and delivers fluid at ambient temperature to a turbine. Spent fluid from the turbine exhausts and is brought into heat exchange relationship with the compressor. The compressor exhaust is at a temperature above that of the turbine exhaust. The exhaust, which is heated by the compressor, is then delivered to a low pressure reservoir which is in heat exchange relationship with ambient air and from there the exhaust heated by the compressor is delivered to the compressor inlet.

Abstract: A security device for a garment display structure of the type having an elongate rail for supporting a garment/security hanger, with the elongate rail having a free end with a first cross-sectional area taken transversely of the length thereof. The security device has a blocking element removably attached in an operative position adjacent to the free end of an elongate rail on a garment display structure to thereby create an effective cross-sectional area, taken transversely of the length of the elongate rail, that is greater than the first cross-sectional area. With the inventive structure, the blocking element prohibits the passage of certain garments/security hangers, that encircle the elongate rail, over and past the free end of the elongate rail, that could otherwise occur in the absence of the blocking element on the elongate rail.