United Technologies Corporation

Other

Gary D Jones

Wendell V Twelves

Carlos G Figueroa

Gunther Eichhorn

Mark E Palusis

Daniel C Friedberg

Bradley C Sammann

James W Norris

Stephen Karl Kramer

Roy N Guile

Rudolph J Novotny

James E Jones

Douglas A Thonebe

Torger J Anderson

Sharon Jones

David E Wendt

David R Sobel

James Steven Johnson

Harvey L Klein

David E Tew

Heather Jones

A pulsed combustion device includes a support structure and a combustor carousel supported by the support structure and rotating relative thereto about an axis. The carousel has a number of combustion conduits in a circumferential array. Each conduit cyclically receives a charge and discharges combustion products of the charge.

Pulsed combustion engine

A turbine engine has a circumferential array of combustion chamber conduits downstream of the compressor and upstream of the turbine. Means are provided for directing oxygen-containing gas from the compressor to the conduits so as to cyclically feed a gas charge into each conduit through its first port and permit discharge of combustion products of the charge and fuel through both the first and second ports.

Pulsed combustion turbine engine

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 alarm device for warding off an imminent attack by generating loud warning sounds and generating attention. The alarm device includes a housing including a front wall, a back wall, a pair of side walls and a pair of end walls and designed for securely coupling to a user; a first sound generating device is coupled within the housing and is operationally coupled to a first such that the first sound generating device produces a first sound when the first switch is actuated; a second sound generating device is coupled within the housing operationally coupled to a second switch such that the second sound generating device produces a second sound when the second switch is actuated; and a power source is operationally coupled to the first switch and the second switch such that the power supply provides power to the first sound generating device and the second sound generating device when the first switch and the second switch are actuated.

Alarm device

Two composite parts, such as sheet and a hollow gas turbine liner tile, are fastened together using a fastening system that includes a journal bearing that fits in a bore in the sheet and springs to support a bolt fastener that is tightened to hold the parts together. Resilient spacers are placed between the sheet and the liner. The springs may comprise a stack of rings, each ring being a tightly wound helical spring, giving the ring a hollow cross section and resilient qualities.

Brittle composite structure for resiliently accomodating thermal

Attaching brittle composite structures in gas turbine engines for

Exit area control panels 18 are supported for movement at an angle with respect to the nozzle axis 12. A varying exit area is formed as actuator 26 axially positions the panels 18. In each exit area control panel 18, there is slidably supported a throat area control panel 28, driven by actuator 32. A sliding throat is achieved as the two panels 18,28 are moved in each quadrant. Yaw and pitch vectoring is accomplished with selective positioning of the two panels.

Sliding throat gas turbine engine nozzle

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Jensen Beach, FL, United States of America

Gary D Jones