Avco Corporation

Alliedsignal Inc.

George T Milo

Clive Waddington

Avi Ben-Porat

Walter Smith

Normand L Lagasse

Theodore Westerman

John G Van Kamerik

An integral structure comprised of inner and outer coaxial shells mutually supported so as to define an annular passageway between the shells. The integral structure may be an air inlet housing for a gas turbine engine and the inner shell may be a hub member having a generally cylindrical passage extending therethrough for rotatably receiving a drive shaft. The inner shell has an outer surface of revolution. A plurality of duct preforms each include an inner duct surface shaped to congruently mate with said outer surface of said inner member, an outer duct surface spaced from said inner duct surface, and first and second lateral walls having opposed lateral surfaces. The duct member preforms are mounted onto the outer surface of the inner member in side-by-side relationship such that the first and second lateral walls on adjacent pairs of duct member preforms are coextensive and engaged. A coaxial outer shell preform is spaced from the inner member. Resin on the duct member preforms and the outer shell preform is cured to form an integral structure comprised of the inner member and outer shell member and a plurality of circumferentially spaced strut members defined by the first and second lateral walls.

Ducted support housing assembly

A method is disclosed of making an integral structure comprised of inner and outer coaxial shells mutually supported so as to define an annular passageway between the shells. The integral structure may be an air inlet housing for a gas turbine engine and the inner shell may be a hub member having a generally cylindrical passage extending therethrough for rotatably receiving a drive shaft. The inner shell is formed by braiding on a shaped mandrel a plurality of fibers such as fiberglass, boron, carbon, or the like, to form an inner shell preform having an outer surface of revolution. A plurality of duct preforms are similarly formed on a conical mandrel, then removed, and administered onto an outer peripheral surface of a duct mold so as to define a modified shape. The modified duct preforms are then positioned onto the outer surface of the inner shell preform in side-by-side relationship such that the first and second lateral surfaces on adjacent modified duct preforms are coextensive and engaged, the plurality of modified duct preforms completely circumscribing the inner shell preform. Then, a plurality of fibers are braided across the plurality of outer modified duct surfaces of the duct preforms to form an outer shell preform spaced from and coaxial with the inner shell preform. Thereafter, resin is applied to the structure to encapsulate the braided inner shell preform, the braided modified duct preforms, and the braided outer shell preform. The resin is then cured to thereby complete fabrication of the integral structure.

An integrated emergency lubrication system for lubricating the bearings of a gas turbine engine in the event that the normal lubrication system for the engine fails for any reason. The emergency system includes an accumulator for storing oil, derived from the normal lubrication system, that is released in a controlled manner, mixed with air and supplied, as a mist to lubricate the engine's bearings for several minutes after the normal lubrication system fails. Energy for operating the emergency lubrication system is derived from high pressure compressed air admitted from the compressor section of the engine when the oil pressure of the normal lubrication falls, a portion of the compressed air being pressure-regulated and combined with oil from the accumulator to form an air/oil mist that is sprayed over the bearings to be lubricated. A flow control valve is provided to control the flow of the oil from the accumulator under the influence of high pressure compressed air, for admixture with the regulated air to form the mist. Thus the oil flow rate remains substantially constant independently of the upstream and downstream air pressures and the oil temperatures.

Integrated emergency lubrication system having single feed line to

An integrated emergency lubrication system is provided to lubricate the bearings of a gas turbine engine in the event that the normal lubrication system for the engine fails for any reason. The emergency system includes an accumulator for storing oil, derived from the normal lubrication system, that is released in a controlled manner to lubricate the engine's bearings for several minutes after the normal lubrication system fails. During that time, the operator of the engine has an opportunity to cope with the situation. Energy for operating the emergency lubrication system is derived from compressed air bled form the compressor section of the engine, the compressed air also being combined with oil from the accumulator to form an air/oil mist that is sprayed over the bearings to be lubricated. A plurality of valves provided to control the flow of the oil and the air and to regulate the pressure of the air, all valves and associated elements being integrated in an assembly that is relatively inexpensive to manufacture, highly reliable, and easily maintained. The configuration also minimizes vulnerability to extraneous forces and has the further benefit of not being attitude sensitive, rendering it particularly useful in aircraft employing gas turbine engines.

Integrated emergency lubrication system

A lubrication system including a regulating valve and a bellows is provided for controlling the flow of lubricant from a source of lubricant under pressure to the gearbox and sump of an aircraft gas turbine engine as a function of the altitude at which the engine is operating. An override valve by-passes the regulating valve and cuts off flow of lubricant to the sump while assuming control of lubricant flowing from the source to the gearbox when a detent valve, operatively associated with the bellows, detects that either the regulating valve or the bellows is inoperative and permits the override valve to become operative.

Lubrication system

A lubrication supply system for providing lubricant to the bearings and the gear box assemblies of a gas turbine engine includes a three stage poppet control valve means interposed between the source of pressurized lubricant and the bearings. The control valve is responsive to the engine speed which determines the level of pressurization of the pressurized lubricant. The control valve by-passes all lubricant to a sump below a selected speed, opens a first passage to the bearings, etc. during idling speed and, modulates the opening of a second passage to the bearings, etc., at speeds above idling.

Gas turbine engine lubrication system including three stage flow control

An oil supply system for pumping oil to the main shaft bearings seals, accessory gears and splines of a gas turbine engine is provided with a bypass duct controlled by a valve programmed to dump excessive oil flow at engine idle. The valve diverts oil flow from the bearings to prevent a build-up therein. A check valve is placed in the main supply line to the bearings and is designed to stop oil flow after engine shutdown.

Growing community of inventors

Bridgeport, CT, United States of America

George T Milo