United Technologies Corporation

The United States of America As Represented by the United States

Utc Fuel Cells, LLC

Torger J Anderson

Wendell V Twelves

John H Whiton

Jayant Sabnis

William M Proscia

Robin J Guthrie

Roy N Guile

Gary D Jones

Frank R Biancardi

Charles Edward Kepler

David R Sobel

David E Tew

Gorken Melikian

James W Sitler

Maurice D Meader

Abraham M Landerman

Fuel is provided to an inlet () of a cascade region () which has a plurality of stages (), each of which divides fuel flow evenly into a pair of corresponding slots (). The flow is then spread across a floor surface () of a cascade exit header (), the flow spreading into areas between the slots. The flow is then directed into an open cavity which is in fluid communication with the inlets of the fuel flow fields () of the fuel cells, reaching the fuel flow field inlets uniformly and simultaneously.

Cascade fuel inlet manifold for fuel cells

A pulse detonation engine ( ) is provided with an aerovalve ( ) for controlling the pressure of injected propellants (Ox, Fuel) in an open-ended detonation chamber ( ). The propellants are injected at such pressure and velocity, and in a direction generally toward a forward thrust wall end ( ) of the detonation chamber ( ), an aerovalve ( ) is formed which effectively inhibits or prevents egress of the propellant from the detonation chamber ( ). A shock wave ( ) formed by the injected propellant acts, after reflection by the thrust wall end ( ) and in combination with the aerovalve ( ), to compress and conserve, or increase, the pressure of the injected propellant. Carefully timed ignition ( ) effects a detonation pulse under desired conditions of maintained, or increased, pressure. Termination of the propellant injection serves to &ldquo;open&rdquo; the aerovalve ( ), and exhaust of the combusted propellants occurs to produce thrust. Alternate embodiments of propellant injection mechanisms ( ) provide pulse valves ( ) each having a fixed slotted disk ( ) and a rotating slotted disk ( ) to provide the desired high speed valving of discrete pulses of propellant for injection.

Pulse detonation engine having an aerodynamic valve

A valve assembly that is useful for controlling fuel delivery utilizes turbine power available from the steady state fuel flow within the valve assembly. A turbine element, which is moved by the steady state fuel flow, provides a motive force to a valve element that controls fuel delivery through selected outlet members of the valve arrangement. A rotating cage valve member preferably is coupled with the turbine element so that the valve member rotates responsive to movement of the turbine element. A controller determines the rate of rotation of the valve member and selectively controls a braking actuator to control the movement of the turbine element and the valve member.

Valve assembly for use in a gas fuel nozzle

The turbocompressor comprises a power turbine (14) and a compressor turbine (16) having respective rotors (18) and (20) on a common shaft (22), rotatably supported by bearings (26) and (28). A first working fluid is supplied by a power loop (32) and is expanded in the turbine (14). A second working fluid is compressed in the turbine (16) and is circulated in a heat pump loop (70). A lubricant is mixed with the second working fluid but is excluded from the first working fluid. Bearings (26) and (28) are cooled and lubricated by a system which circulates the second working fluid and the intermixed lubricant through the bearings (26) and (28). Such system includes a pump (126), a thermostatic expansion valve (150) for expanding the working fluid into the space (152) between the bearings (26) and (28), and a return conduit system (154, 156, 158) for withdrawing the expanded working fluid after it passes through the bearings and for returning the working fluid to the evaporator (82). A shaft seal (30) excludes the lubricant from the power turbine (14). The power loop (32) includes a float (208) operable by liquid working fluid in the condenser (46) for controlling a recirculation valve (206) so as to maintain a minimum liquid level in the condenser, while causing a feed pump (48) to pump most of the working fluid into the vapor generator (34). The heat pump compressor loop (70) includes a float (222) in the condenser (78) for operating an expansion valve (88) to maintain a minimum liquid working fluid level in the condenser (78) while causing most of the working fluid to be expanded into the evaporator (82).

Solar-powered turbocompressor heat pump system

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Manchester, CT, United States of America

Torger J Anderson