Abstract: A propulsion system for use primarily in V/STOL aircraft is provided with a variable cycle, double bypass gas turbofan engine and a remote augmenter to produce auxiliary lift. The fan is oversized in air-pumping capability with respect to the cruise flight requirements of the remainder of the engine and a variable area, low pressure turbine is capable of supplying varying amounts of rotational energy to the oversized fan, thereby modulating its speed and pumping capability. During powered lift flight, the variable cycle engine is operated in the single bypass mode with the oversized fan at its maximum pumping capability. In this mode, substantially all of the bypass flow is routed as an auxiliary airstream to the remote augmenter where it is mixed with fuel, burned and exhausted through a vectorable nozzle to produce thrust for lifting.

Abstract: Cascades and associated blocker doors are provided in the lower section of a turbofan engine nacelle such that when the blocker doors are closed the bypass flow is diverted through the open cascades to produce vertical thrust. Vanes are provided in the cascades to assist in directing the diverted airflow in the downward direction. The upper section of the bypass duct is isolated from the lower cascade section by way of horizontal struts extending across the bypass duct. A pair of outer doors may be provided over the cascades such that, when opened, they act to provide side skirts to guide the downward flow of air.

Abstract: A gas turbine engine comprises a casing defining a duct for a thrust producing gas, the casing is divided into an upstream and a downstream portion movable between a normal position form a continuous duct and a thrust reversal position in which the two portions are separated by a gap. A plurality of thrust reversal doors are pivotally connected at or towards one end thereof to the downstream portion and a number of struts and pivotally connected at or towards one end thereof to the upstream portion, the thrust reversal doors and the struts in the normal position and as the upstream and downstream portions move towards the thrust reversal position, extending downstream to leave the duct unobstructed thereby.

Abstract: A boat includes a longitudinal water channel along the bottom thereof. A motor driven propeller in the channel circulates water from a forward inlet end thereof to a rear outlet end thereof to advance the boat through the water. Passages are provided which communicate with the channel and which are adapted to discharge water through front and rear openings on the port and starboard sides. Gates are provided for opening these passages. A gate actuating mechanism is provided for opening the front port and rear starboard passages to rotate the boat in one direction about its own vertical axis. Another gate actuating mechanism is provided for opening the front starboard and rear port passages to rotate the boat in the opposite direction about its own vertical axis. Upon being opened, each set of gates serves to block travel of water to the outlet of the channel, and thereby divert all water through the passages.

Abstract: A two dimensional expansion nozzle having a rotating plug serves to block flow, meter flow and afford thrust vectoring. Adjustable walls cooperate to obtain these features and may be adjusted independently to vary nozzle throat area. Cooling means are disclosed. This invention has particular application for VTOL aircraft.

Abstract: A thrust reverser suitable for reversing the flow direction of the fan air of a fan jet engine is disclosed. The thrust reverser comprises a cascade section and a fan duct blocker section. The cascade section includes a series of cascade elements mounted in a side-by-side manner about a portion of the engine nacelle for rotation through an arc of 90.degree. about longitudinal axes lying generally parallel to the direction of fan air flow. Each cascade element includes an inner panel, an outer panel, and a series of vanes located between the inner and outer panels. Rotation is between a closed position whereat the inner panel forms a portion of the fan air duct and the outer panel forms a portion of the outer surface of the nacelle, and an open position whereat the vanes define passageways adapted to reverse fan air flow i.e., direct fan air flow back toward the front of the engine.

Abstract: A thrust reverser cascade section comprising a plurality of cascade windows mounted in an engine nacelle rearwardly of the fan air compressor, each cascade window including a plurality of cascade elements, is disclosed. The cascade elements are rotatable through an arc of 90.degree., more or less, between closed and open positions, along axes lying generally parallel to the longitudinal axis of the nacelle. The cascade elements include deflecting vanes and are generally S-shaped when viewed in cross-section. Adjacent cascade elements abut one another in both their open and closed positions. Seals are located in the regions of abutment. The vanes direct fan air flow from the fan air duct toward the front of the nacelle when the cascade elements are in their open position. Each cascade window also includes sealing end plates adapted to move into and out of sealing relationship with the cascade elements to seal the ends when the cascade elements are closed.

Abstract: A steerable rocket motor for towing a load or extracting an aircrew member rom a disabled aircraft, regardless of aircarft attitude or altitude. The rocket motor is formed from a hollow cylindrical thin walled casing containing a high burn rate propellant and having a plurality of rocket nozzles at one end. The rocket nozzles are positioned around the circumference of the rocket body and are angled to thrust outward and toward the load or aircrew member being towed. A thrust control proportions thrust among the plurality of nozzles for controlling the pitch and yaw of the rocket. Position and rate sensing apparatus informs the thrust control regarding rocket attitude to enable the rocket to steer a predefined desirable flight trafectory. One or more lines are attached to the rocket and are adapted to be fastened to the load or aircrew member being towed.

Abstract: A pure fluid interface device for proportional linear control of high temature, high pressure, hot gas flow from the exhaust of a rocket motor. The interface device receives the hot gas by direct bleeding from the rocket exhaust system and directs the gas to the control system of a missile airframe.The proportional linear control of the interface is achieved through a pair of positive displacement pistons which engage a jet pipe, charged with the hot gas, for pivotal movement of the jet pipe for alignment of the orifice of the jet pipe with one or both exit ports in the body of the interface device to direct the hot gas through the desired exit port.

Abstract: The present invention relates to vessels which are propelled by two or more groups of thrusters and particularly to ships or oil drilling rigs in which it is desired to keep on a particular station. In some circumstances one of the thrusters is found to interfere with the operation of another thruster or to be overloaded when another thruster is not overloaded. The invention provides a method and apparatus for alleviating these problems.

Abstract: A waterjet propulsion system having at least two pumps in series so that low from a hull or other intake is directed through a first waterjet propulsion pump; and then via a two-position diverter valve, either out to a thrust nozzle, or to and through a second waterjet propulsion pump having a thrust nozzle. Subsequent series-pump units and diverter valves may follow to provide as many propulsion stages as required for power requirements. Each pump unit is driven by its own power unit which may be shut down when flow is diverted to the preceding unit's thrust nozzle. Good efficiencies are thereby attained over a wide range of power and speed requirements.

Abstract: A valve for directing fluid under pressure in which a diverter vane when actuated causes the incoming fluid to move a sealing ball member from a first to a second position for opening or closing said valve.

Abstract: The engine exhaust flow diverter is formed as a duct, extending from the exhaust section of a gas turbine powerplant, having a closed end which is contoured externally as a nozzle plug. First exit means for the flow from the powerplant extends around the duct just forwardly of the contoured plug and second exit means for the flow extends around the duct midway between the first exit means and the end of the exhaust section of the powerplant. An annular door is axially movable around the duct between an open and closed position to control the flow through the second exit opening and an annular shroud is axially movable around the duct between an open and closed position to control the flow through the second exit means. The annular shroud cooperates with the contoured nozzle plug to form a conventional nozzle. An actuating system is connected to both the annular door and annular shroud to actuate them so that when one is open the other is closed.

Abstract: An axial flow gas turbine engine, for use in a V/STOL aircraft, of the type having a rotatable nozzle for vectoring the direction of exhausting gas and a tapping for bleeding high pressure compressor outlet gas for use in an aircraft stabilising system, has controllable means for supplying compressor outlet gas to the turbine blades. The same valve is used for controlling supply of gas to the turbine blades and to the stabilising system.

Abstract: An improved gas turbine engine exhaust nozzle diverter valve is provided to selectively direct the flow of motive fluid through one of two nozzle exhaust ports and to provide improved sealing to prevent the flow of fluid through the second nozzle exhaust port. Linkage and actuator means are provided to retract a blocker door having a deformable seal attached thereto from a first seated position over the second nozzle exhaust port, and to then rotate the blocker door to a position over the first nozzle exhaust port. The method of retracting the blocker door prior to rotating it eliminates sliding friction and minimizes the potential of damage to the seal between the blocker door and the nozzle exhaust port.