Alliedsignal Inc.

Honeywell International Inc.

Charles Michael Royalty

Joseph L Schoepf

Yogendra Y Sheoran

Kellan P Geck

Louie Timothy Gaines

James Neil Quitmeyer

Marc Schmittenberg

Laurence D N Liston

David F Ross

Craig A Lyon

Joseph W Hough

Laurence D Liston

Thomas W Davis

Kurt T Kenzler

Jeff S Rayner

William Traxler

The present invention provides a tailcone and power assembly mountable to the body of an aircraft using a height adjustable dolly. The tailcone assembly comprises a longitudinal support member, a gas turbine engine mounted to the support member; a firewall; two curved rotatable casings hingeably connected to the support member; an inlet duct extending form an aperture in one of the rotatable casings to the engine inlet; an integral exhaust casing, and interface means for making necessary engine accessory connections to the aircraft. The tailcone is installed on the aircraft by mounting the tailcone in the adjustable dolly, rolling the dolly up to the aircraft, adjusting the dolly until the auxiliary power assembly is properly aligned for attachment to the aircraft, connecting the engine accessories to the aircraft, and bolting the assembly to the aircraft.

Detachable integral aircraft tailcone and power assembly

A relatively small, lightweight valve actuator assembly that can withstand relatively high levels of vibration and shock includes a motor, a position sensor, and a drive belt mounted on an actuator housing assembly. The position sensor is preferably disposed within a sensor housing that is mounted on a side of the actuator housing assembly. As a result, the overall center-of-gravity (CG) and weight of the actuator assembly is significantly reduced, as is the overall size envelope.

Reduced profile electromechanical valve actuator

The present invention provides a tailcone and power assembly mountable to the body of an aircraft using a height adjustable dolly. The tailcone assembly comprises a longitudinal support member, a gas turbine engine mounted to the support member; a firewall; two curved rotatable casings hingeably connected to the support member; an inlet duct extending from an aperture in one of the rotatable casings to the engine inlet; an integral exhaust casing, and interface means for making necessary engine accessory connections to the aircraft. The tailcone is installed on the aircraft by mounting the tailcone in the adjustable dolly, rolling the dolly up to the aircraft, adjusting the dolly until the auxiliary power assembly is properly aligned for attachment to the aircraft, connecting the engine accessories to the aircraft, and bolting the assembly to the aircraft.

A butterfly valve plate is provided for use in a pneumatic surge valve or the like, wherein the valve plate is designed for reduced noise with increased mass flow capacity. The valve plate is of the type having an offset stem hub for supporting the valve plate on a pivot stem or shaft for movement between closed and open positions within a flow conduit. A pair of part-circular and generally axially extending acoustic fences are carried respectively at opposite sides of the valve plate in peripheral positions for flow-through passage of air when the valve plate is opened. An enlarged and smoothly contoured noise reduction collar is formed on the stem hub at the downstream side of the valve plate, generally at the periphery thereof to substantially fill and occupy the space between the stem hub and the adjacent end of the downstream-side acoustic fence.

Butterfly valve plate for a pneumatic surge valve

A method and apparatus for cooling the heat generated by a gas turbine engine mounted in a compartment is provided. The apparatus comprises a novel eductor that incorporates a mixer nozzle to entrain sufficient air flow through the compartment to provide all the necessary cooling. The engine's oil cooler is mounted to the eductor so that the entrained air flow passes through it and cools the engine's oil. The novel eductor also has means for receiving a flow of high velocity air from the engine and injecting this air downstream of the mixer nozzle to enhance the entraining of the cooling flow.

Exhaust eductor cooling system

An elongate exhaust gas muffler for a turbine engine includes a foraminous central exhaust duct which is circumscribed along its length by a plurality of tuned dissipative and reactive noise attenuation chambers. At an inlet end of the muffler an annular secondary flow inlet is defined about the central exhaust duct and opens to the first sound attenuation chamber. A secondary flow of pressurized bleed air is receivable into the first attentuation treatment in the muffler.

Growing community of inventors

Tempe, AZ, United States of America

Charles Michael Royalty