Abstract: A coolant pressure regulating appartus having a predetermined number of coolant pressure regulating valves which rotate against a spring bias to divert coolant flow and excess pressure from the coolant air fan duct into the engine core exhaust flow. The pressure regulator valve regulates the pressure within a closed cavity suppressor to the pressure level within the core without any affect upon the upstream fan duct pressure.

Abstract: A hose pump (1) consisting of a hose (2), at least one, preferably two pressure rollers (3,4), a support plate (9) and a drive source (26). The hose (2) is paced in a hose receiving track (6) in the support plate (9). The rollers (3,4) are rotatably journalled on a common rotary shaft (10), whose center (11) is firmly connected with a drive shaft (12), which is perpendicular to the support face (5) of the support plate (9) engaging the rollers (3,4). The rollers (3,4) act on the hose (2) in the flow direction of the pump (1) and alternately determine, in specific angle ranges, the liquid volume flow discharged. The succeeding roller (4) cooperates with the hose (2) in such a manner that the hose is completely closed when the forwardly disposed roller (3), as seen in the flow direction, initiates its disengaging movement away from the hose (2).

Abstract: A thrust reverser including a bypass duct and a plurality of light weight, circumferentially displaced blocker doors each movable between a normal position and a thrust reversal portion. The blocker doors include pits on the inner portion which faces the bypass duct during normal operation of the engine. Provision is made for automatically covering the pits during normal operation to provide smooth, non-turbulent flow of air through the bypass duct. In one embodiment of this invention a pit cover is pivotally mounted on the blocker door and is biased to engage the edge of a ramp fairing when the blocker door is in the position it occupies during normal operation of the engine. During thrust reversal, the pit cover moves outwardly along with the blocker door and away from the ramp fairing so as not to impede in any way flow of thrust reversal air through an opening in the outer wall.

Abstract: A trust reverser is disclosed for a turbofan-type turbojet engine having the capabilities of reversing the air passing through a cold flow air duct to provide a reverse thrust for the engine and also adjusting the cross-section of the cold flow air duct. This enables the cold flow air duct to be increased in cross section during periods of high thrust operation, a cowl defining the outer limits of the cold flow air duct has a stationary portion arranged generally, concentrically about the hot gas exhaust duct, and two movable portions, each of which are movable axially with respect to the stationary cowl. Locking systems are utilized to releasably lock a first movable cowl to the stationary cowl, and to releasably lock the second movable cowl to the first movable cowl.

Abstract: In the preferred configuration, the assembly is characterized in that the lateral and longitudinal thrust reserving loads exerted on the thrust reversing subassembly are transmitted into the fan duct structure which is arranged to in turn transmit these thrust reversing loads into outer structure to which the jet engine and thrust reversing assembly is mounted.In the preferred from, there are vane means which, with the thrust diverting structure in the thrust reversing position, is positioned in the thrust reversing opening to properly direct flow through the thrust reversing opening. Also in the preferred form, the thrust diverting structure is pivotally mounted to the fan duct structure at a lower location so that the thrust diverting structure rotates with a downward component of motion to the thrust reversing position, so that the thrust diverting opening is directed upwardly.

Abstract: Inside a ducted fan turbine engine, especially one with a high or very high bypass dilution ratio, access to the gas generator compartment of the engine is effected by means of two articulated caps (34) with a C-shaped section. The upper edge of each cap (34) is connected to the fixed structure of the jet engine by means of a series of articulated arms (36) and a telescopic link (54) is inserted between the housing of the engine and the bottom of each cap. In a first stage (arrow F1), this mechanism enables the caps (34) to be brought beyond the rear edge of the outer ring (12) of the jet engine, the links (54) being locked in a compressed position. In a second stage, the caps (34) uncoupled from the ring (12) are able to pivot from the desired angle (arrow F2) around an axis (y-y') parallel to the axis (x-x') of the ducted fan turbine engine.

Abstract: A gas flow diverter receives large volumes of hot gases from a gas turbine into a chamber in which is a pivotally mounted blade adapted to close either the outlet port to a heat recovery steam generator or the outlet port to the stack. Each port is surrounded by an open channel, the two side walls of each of which are provided with an exposed seal arranged one beyond the other. One or both surfaces of the blade is insulated, the insulated surface(s) being covered with steel cladding and the uncovered surface being a stainless steel membrane adapted to resist corrosion from the hot gases. The steel cladding is connected through insulation to the underlying structure in a manner permitting but confining the expansion of the cladding.

Abstract: Laminar flow tubes of uniform inner diameter and length are individually incorporated in each of plural fuel lines leading from a distributor to the various fuel injectors in a gas turbine combustor to provide generally uniform fuel distribution over a wide range of fuel flow rates, thus eliminating the need for a variable fuel metering valve in each fuel line.

Abstract: The present invention provides a method for the destruction of hazardous carbonaceous wastes comprising solids which comprises the steps of (a) gasifying said wastes and producing an intimate admixture of the gaseous products of said gasification with air, said admixture containing at least a stoichiometric amount of air, (b) passing said admixture to a plug flow combustion zone, and (c) effecting sustained and essentially complete combustion of said admixture under essentially adiabatic conditions to destroy said gaseous products and to form a combustion effluent of high thermal energy; said combustion being characterized by said admixture having an adiabatic flame temperature such that that actual flame temperature in the combustion zone is greater than about 1350 K.

Abstract: The present invention provides a high bypass turbofan engine configuration wherein a fan drive turbine is divided into first and second turbine sections mounted for independent rotation within the engine frame. The first, higher pressure, higher speed turbine section is coupled to the fan section drive shaft via a gear box which reduces the rotational speed of the power delivered by the higher pressure first turbine section to match the design rotational speed of the fan section. The second turbine section, having a larger diameter and lower rotational speed as compared to the first turbine section, is directly connected to the fan section and drives the fan section at the same rotational speed as that of the second turbine section. In this manner, the fan drive shaft horsepower is provided while reducing the weight and size of the necessary gearing between the fan drive turbine and the fan. The weight and size of the fan drive turbine and the booster compressor are also reduced.

Abstract: A compact, multimode propulsion system for aerial vehicles having multiple thermal cycles for selective independent or integrated operation in multiple modes to enable the propelled vehicle to operate in a full range of velocities under a variety of atmospheric conditions and efficiencies, the system including a turbo-jet unit with an air compressor, a gas turbine and an intermediate fuel injected combustor in association with an auxiliary combustor unit that includes a supplemental fuel and selective oxidizer supply, and a conversion system for selectively converting the auxiliary combustion unit into a secondary burner mode for the turbo-jet unit, an independent rocket mode operable with or without the turbo-jet unit or in independent ram-jet mode operable with or without the turbo-jet unit, the turbo-jet unit and auxiliary combustor system having separate exhaust systems for directional mobility of the vehicle to which the propulsion system is applied.

Abstract: A thrust reverser includes a thrust reversing door having maximum efficiency in both the closed, forward thrust position and the open, reverse thrust positions. An inner panel is pivotally attached to the thrust reverser door by a linkage mechanism such that, in the closed position, an interior surface of the inner panel is substantially flush with the interior surfaces of the housing defining the cold flow duct so as to minimize or eliminate any perturbations in the air flowing through the cold flow duct. When the door is moved to the opened position, the linkage mechanism interconnecting it to the inner panel causes the inner panel to pivot a greater amount so as to bring an upstream portion of the inner panel closer to an upstream portion of the door to expose the deflector and thereby increase the thurst reversing efficiency.

Abstract: In a gas turbine engine including first and second differentially rotating members coaxial with each other, a low pressure region disposed about the first and second differentially rotating members, and an annular gas flowpath disposed within the first and second differentially rotating members defining a high pressure region, a method and apparatus for preventing fluid leakage between the first and second rotating members. An annular carrier is coupled to the first rotating members such that the annular carrier is coaxial with the first rotating member. The annular carrier is sandwiched between a first race and a second race with the first and second races coupled to the second rotating member. The second race is urged toward the first race such that leakage of a fluid from the high pressure region to the low pressure region is not substantially increased by frictional wear of any of the annular carrier, first race and second race.

Abstract: A transporter includes at least one elongated transporting element (1) which is made of a material capable of changing its volume in response to the application of voltage or magnetic fields thereacross. The transporting element, optionally together with a further transporting element or some other part of the transporter, defines an elongated transporting channel (7). Means are provided for generating fields in predetermined regions along the transporting element (1) and in a given order of sequence, such as to impart substantially peristaltic motion to the element. These means include at least three mutually adjacent conductors (3, 4, 5) which extend substantially helically in relation to the transporting element (1) and to which different phases of a multi-phase alternating voltage or alternating current source are applied.

Abstract: The present invention provides a movable air deflector which, in a first position, deflects air passing through the cold flow air duct of a turbofan engine in a direction such that it approximates the theoretical air flow line and does not enter a cavity defined by the interior of the thrust reverser door when the door is in its closed position. A linkage mechanism connects the air deflector to the door actuator, such that, when the door is moved to its opened or thrust reversing position, the deflector is moved to a second position so as to minimize its interference with the thrust reversing air flow.

Abstract: A turbo fan gas turbine engine is disclosed which includes a central engine and a shroud-enclosed fan, the shroud being supported by a plurality of structural struts extending from the central engine to the shroud. A plurality of tubes internal to each strut are provided with fins to increase their effective internal surface areas. Means are provided for connecting the tubes to a source of heated hydrocarbon liquid and for providing a return from the tubes to the source of hydrocarbon liquid, whereby the tubes provide cooling for the liquid. In a preferred embodiment of the invention, the tubes are surrounded by a highly conductive cement to provide support and improved heat transfer between the tubes and the struts.

Abstract: An apparatus for applying lubricant to a railroad vehicle wheel flange utilizes a solid lubricant material. The block of lubricant is wedge-shaped and mounts to one side of the brake shoe. The lubricant wedges between the wheel flange and the brake shoe. The block of lubricant is secured to a plate that sandwiches between the brake shoe pads and the beam head of the braking system. A cantilevered, resilient loop urges the block into engagement with the flange.

Abstract: A cooling water system for a rotary internal combustion engine includes initial direct water cooling for the outer surface of the exhaust manifold with the cooling water directed therefrom to serially interconnected cooling water passages in the various housing elements comprising the engine block. The cooling water passage in each housing element is circumferentially disposed along the peripheral portion of the housing which is directly adjacent the high temperature exhaust and combustion areas of the engine rotor chamber. The cooling system thus supplies water directly to the portions of the engine subject to the highest operating temperatures. The system also includes protection against the formation of hot air or steam pockets and the cooling system is readily adaptable to both single and twin rotor engines.

Abstract: The invention relates to a motor-driven pump intended for the pumping of liquids and driven by a pressurized motive fluid. The motor-driven pump (1) has a rotary sleeve (12) mounted in line between two stationary connections (8, 10). Mounted on the periphery of this sleeve (12) are the blades of a turbine which surrounds the sleeve (12). Rotary pumping members (24) are fastened inside the sleeve (12). The motor-driven pump (1) of the invention is intended more particularly for use as a submerged pump, especially as a pump for dredging at great depth.

Abstract: A redundant rocket engine for high reliability that incorporates a single thrust chamber and its attendent hydrogen and oxygen injectors and provides a pair of independent but indentical engine systems that provide the fuel feed and cooling systems where one system remains in a standby condition until a malfunction occurs while the other system remains operative. The independent systems are comprised of all of the movable parts.