Abstract: A multi-spool turbofan engine has a plurality of circumferentially spaced poppet valves with diverters secured thereto for precisely controlling bleed of combustion gas aft of the high pressure turbine whereby the high pressure spool operates at high idle RPM so as to power accessories and the low pressure spool operates at low RPM so as to minimize noise and fuel consumption.

Abstract: A fuel lubricated anti-friction bearing comprises an inner race for an anti-friction bearing having a plurality of radially opening apertures communicating with a fuel supply, a rotatable outer race, and a plurality of anti-friction rollers between the inner and outer races, rotation of the outer race effecting rotation of the rollers and pumping of fuel radially outwardly through the apertures in the inner race of the rollers.

Abstract: A multi-spool turbofan engine has a high pressure spool that operates at high idle RPM so as to power accessories and minimize acceleration time from idle to full rated RPM without producing high idle thrust which compromises the landing maneuver and ground operation.

Abstract: An electromagnetically shielded self-molding package for an electronic component comprises a pair of bags having an electrically conductive coating therebetween and disposed about the component and having a polymerizable resin completely filling the space between the bags and the component.

Abstract: A slurry polishing apparatus (100) comprises an assembly of an upper slurry input/output section (108), a polishing section (110), and a lower slurry input/output section (112). Each of the apparatus sections are individually detachable from the assembly to facilitate insertion and removal of a hydrodynamic or aerodynamic machine part having a complex surface shape such as a turbine fan (102). A plurality of upper slurry deflector blades (124) and lower slurry deflector blades (126) are removably attached to the polishing section (110), and positioned in the slurry flow path so as to direct the slurry mixture evenly over the entire surface of each respective fan blade (104), and corresponding exposed intermediary rotor surface (106). Because the high pressure slurry mixture flows evenly over the exposed fan surfaces, a consistent removal of metal stock is achieved across the entire polished surface.

Abstract: A composite wing for an aircraft comprises a plurality of elongated hollow one-piece composite spars arranged in juxtaposed generally parallel relation in an array defining an airfoil with a composite skin disposed about said assembled spars.

Abstract: An annular combustor for a gas turbine engine having a rotatable fuel slinger has a first plurality of effusion cooling holes for directing air flow radially inwardly toward said fuel slinger and circumferentially in the direction of rotation of the fuel slinger and a second plurality of effusion cooling holes on the opposite side of the fuel slinger for directing air radially inwardly and circumferentially in the direction of rotation of the fuel slinger, thereby to produce a pair of annular axially spaced helical air flow patterns having a confluence in the direction of fuel flow radially outwardly from the fuel slinger.

Abstract: A conical microlith catalyst reaction system for use in automotive catalytic converters or gas turbine catalytic combustors advantageously utilizes a microlith catalyst bed formed from a wire cloth (10) woven into a spiral wound flat helix (or coil). The spiral windings of the wire cloth helix are wound to form a uniform angle less than 90.degree. relative to a ceramic housing formed from an inner ceramic hub (102) and an outer ceramic shroud (104). Warp wires (12) further carry electrical current via bus bars (106, 108) for electrically heating the catalyst bed. Lightoff time for the bed is significantly reduced due to the heating. The angled spiral windings create the conical shape to prevent buckling of the spiral windings due to thermal stress caused by the microlith catalyst bed becoming hot.

Abstract: A method of protecting an electronic component from the environment comprising the steps of providing a bag made from thermoplastic heat shrink material, inserting said electronic component into said bag, injecting a liquid polymerizable resin into said bag, heating said bag to shrink it about said electronic component and said resin, and curing said resin.

Abstract: A microlith catalyst bed for use in automotive catalytic converters or gas turbine catalytic combustors. The microlith catalyst bed of the present invention advantageously utilizes a wire cloth (10) woven to form a spiral wound flat helix (or coil). Woof wires (14) are woven into warp wires (12) in a polar weave pattern. There is no leftover scrap when forming the microlith catalyst bed. Warp wires (12) further carry electrical current via bus bars (106, 108) for electrically heating the catalyst bed. Lightoff time for the bed is significantly reduced due to the heating.

Abstract: A composite fan blade comprises a blade portion (12) formed from a first set of unidirectional layers of fibers (110) wrapped around a wedge shape bushing (16). A blade platform (14) comprising a second set of unidirectional fiber layers (114) filled with a resin filler (116) is pressure molded with the blade (12) and bushing (16) to form a desired blade shape. The blade is then hinge mounted to a metallic blade support disk (18). The blade of the present invention provides a strong, lightweight fan blade for small, high speed propfan turbine engines.

Abstract: A compliant hydrodynamic gas bearing comprises a nonlinear spring arrangement for supporting a plurality of tilting arcuate pads which hydrodynamically carry radial journal loads. The nonlinear spring support arrangement enables the bearing to provide increasing load-deflection capacity under extreme loads to limit deflection to a predetermined clearance. The spring arrangement provides nonlinear load-deflection capabilities while operating with a designed constant bending stress.

Abstract: A drum compressor rotor (10) for use in a gas turbine engine comprises a plurality of high strength, low density filaments (18a-d) which are covered with a high temperature adhesive resin and tightly wound around the hub (12) between rows of fan blades (14). The filaments allow an increase in the maximum compressor rotor operating speed thereby increasing the potential performance of the turbine engine. The filament windings (18a-d) are significantly lighter and less expensive than conventional welded metal support disks (106a-c).

Abstract: A reflexive fuel heating system for fuel entering the fuel filter of an engine comprises a heat exchanger disposed between a fuel tank and the fuel filter for transferring heat generated in a gear type fuel pump to the fuel.

Abstract: An aft fan gas turbine engine comprises a coaxially related compressor, compressor turbine, fan turbine, and aft fan. An annular fuel tank is disposed about the compressor and an annular combustion chamber is disposed between the compressor and turbine.

Abstract: A subatmospheric pressure swing filter is integrated with a vapor cycle refrigeration system so as to provide both air filtration and air conditioning.

Abstract: A propulsion system comprises a gas turbine engine having sructurally integrated support systems that maximize structural efficiency and minimize cost.

Abstract: A near supersonic aircraft comprising an airframe that maintains subsonic air flow thereover within the flight envelope of the aircraft. The airframe comprises a right circular conical forward fuselage section, a right circular cylindrical intermediate fuselage section defining a passenger compartment, and an aft fuselage section having a generally circular frontal cross section and a generally rectangular aft cross section.A submerged semi circular air inlet is disposed between the intermediate and aft fuselage sections at the top thereof. A pair of forwardly swept wings are joined to the fuselage adjacent the circumferentially spaced ends of the air inlet whereby air flow over the fuselage and along the leading edges of the wings is directed into the air inlets at subsonic speeds and at all attitudes of the aircraft within its flight envelope.

Abstract: A fuel control system for providing steady state fuel flow to a gas-turbine engine comprises a pulse-width modulated, solenoid-operated fuel metering valve, an engine speed transducer, and a remote microprocessor communicating with the valve and the speed transducer through an optical fiber. The valve is operated by a direct current signal which is pulsed at a frequency substantially higher than the natural frequency of the valve spring/plunger system, whereby the plunger remains axially displaced from the valve seat to provide continuous flow through the valve. The amount of axial plunger displacement and, hence, the fuel flow are prescribed by the pulse width of the signal directed through the valve.

Abstract: A refrigeration system utilizes a small high speed centrifugal compressor driven by a directly coupled, high frequency, electric motor. The motor has a double-ended shaft which supports the rotors of low pressure and high pressure centrifugal compressor stages. The motor operates in the refrigerant atmosphere so as to eliminate the requirement for rotating shaft seals. High frequency power (3750 Hz) is supplied to the motor, which runs at 75,000 RPM. The system utilizes a novel flash intercooler between the compressor stages.