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: A composite cycle rocket engine having an inner engine disposed to discharge directly into the nozzle of an outer engine, is described herein.

Abstract: A turbofan-ramjet engine is provided with optional duct burning in the turbofan mode. A core engine is provided with a first annular passage therearound for directing airflow around the inlet of the core engine. A second annular passage having a fan directs air flow into the inlet of the core engine and said first annular passage. A third annular passage extends around the first and second annular passage with the first and third annular passage each directing their flow into a common annular combustion chamber. Variable vanes are provided in the first and third annular passages to provide for blocking off the passage or acting as swirl vanes depending on mode of operation. Blocking vanes are also provided in the annular exhaust passage of the core engine. Coannular nozzles are provided with one located at the exhaust of the core engine and an outer one located aft of the common annular combustion chamber.

Abstract: A jet propulsion engine assembly for aircraft embodying a longitudinal tubular pod or nacelle housing having an open air intake nose. This assembly includes an axial air flow impeller supported longitudinally in the interior of and by the housing, and it has an annular array of rotary blades supported therein upon a rotatably supported, longitudinal and generally central shaft to force air from the intake nose longitudinally back toward the tail end of said housing. A central jet engine within this housing has a longitudinal drivable shaft substantially aligned with the impeller shaft and drivably connected thereto by disengageable clutching means for effecting drive of the latter from the former when the engine shaft is power driven by the central engine.

Abstract: A missile is initially propelled through space by the burning of solid fuel in a combustor. The heat produced by the combustion of such fuel is used to vaporize a liquid, the pressurized vapor being used to pump liquid fuel to the combustor after the solid fuel has been depleted.

Abstract: A multi-stage gas generator in which selective sequential initiation of cartmental propellant charges is available as a pulsing gas generator. The generator has individual gas generating compartments mounted in tandem and separated from each other by a partitioning wall, each wall having an undirectional plug in a filtering passage, an ignition propellant and an associated electric squib with a pyro-electric switch responsive to generated propellant gas in an adjacent compartment.