The Boeing Company

Olin Corporation

Primex Technologies, Inc.

George W Butler

Frank T Cianciotto

David H Reed

Frederick Theodore Calkins

James Henry Mabe

Eric H Nesbitt

Christopher L Davis

Steven C Knowles

Mark A Simon

Mehmet Bahadir Alkislar

David O King

Alan E Kull

Mehmet B Alkislar

Jet engine nozzles with projections (e.g., chevrons) and injected flow, and associated systems and methods are disclosed. A method in accordance with one embodiment includes generating a first flow of gas with a jet engine, delivering the first flow through a nozzle having a trailing edge perimeter that includes multiple projections extending in an aft direction, and injecting a pressurized second flow of fluid into the first flow proximate to the projections. In other embodiments, other mixing enhancement devices (e.g., vortex generators) are carried by the projections. It is expected that the combination of the projections and the mixing enhancement devices will reduce engine exhaust noise levels below the levels achievable with either projections or injected flow individually.

Systems and methods for reducing noise from jet engine exhaust

A right angle light diverter includes a hexagonal tube that is bent at a right angle that is coated with a highly reflective coating on the inside surface. An incoming light beam may be homogenized upon entering an input port of the hexagonal tube and may be evenly diverted at a right angle at a reflection section while the homogenized profile may be maintained. A right angle optical splitter may include at least one additional output section. An incoming light beam may be homogenized and may be split into at least two outgoing beams that may be diverted at right angles at reflection sections. The right angle light diverter and the right angle optical splitter may be suitable for, but not limited to, applications in aircraft industry, both military and commercial. They may be used, for example, in connection with airborne laser programs, in commercial airplanes, and in military jets.

Hex tube light homogenizer splitter

An optical wave guide. The guide includes a body with a cross section that defines a polygon, preferably a hexagon. The proximal end of the body optically couples to an optical source (e.g. an optical fiber or light source) with an initial distribution. The wave travels through the body to the distal end whereby the distribution becomes a top hat distribution. In another preferred embodiment a bundle of optical fibers is coupled to the distal end. Additionally, the guide may include a coupler to align the source and the bundle with the body. In yet another preferred embodiment, the length of the body is at least about 6 times the width of the cross section. In another preferred embodiment, a method of splitting a wave is provided. The method includes passing an electromagnetic wave through a wave guide with a hexagonal cross section.

High efficiency multi-spectral optical splitter

A noise reduction system for use with an exhaust nozzle associated with a jet engine of an aircraft. The noise reduction system employs a plurality of flow-altering components disposed circumferentially about a lip portion of an exhaust nozzle. In one preferred form the flow-altering components each comprise piezoelectric transduction layers. The flow-altering components are caused to move in an oscillating manner by an AC signal applied thereto such that they move into and out of the exhaust gas emitted from the exhaust nozzle to achieve a desired degree of intermixing of the exhaust flow with the flow adjacent the exhaust nozzle. This produces a reduction in the noise generated by the jet engine. The noise reduction can be utilized during takeoff conditions of an aircraft. The flow-altering components are maintained out of the exhaust gas flowpath during cruise conditions of the aircraft so as not to cause a reduction of thrust, that would in turn result in an increase in the fuel burn during cruise conditions.

High frequency jet nozzle actuators for jet noise reduction

An exhaust flow nozzle for a jet engine having a plurality of flow altering components extending from a lip portion of a secondary exhaust nozzle that are movable between first and second positions. In the first position the flow altering components are disposed substantially parallel to an exhaust gas flow path and thereby do not produce drag or a reduction of thrust from the engine. In the second position the flow altering components bend or are deformed to project into the exhaust gas flow path exiting from the secondary exhaust nozzle. The flow altering components are comprised of a shape-memory alloy material which deforms in response to heat. One or more additional layers of material are bonded or otherwise coupled to the shape-memory alloy layer of each flow altering component to assist in returning the shape-memory alloy layer to its unheated shape.

Deployable segmented exhaust nozzle for a jet engine

There is provided an anode for an electrothermal arcjet thruster. A conduit running through the anode body has a converging upstream portion and a diverging downstream portion connected by a constrictor portion having a greater diameter at the interface with the upstream portion than at the interface with the downstream portion. As the result, the cross-sectional area available to a propellant gas passing through the constrictor constantly decreases and the propellent gas velocity continually increases. This constrictor geometry allows the arcjet thruster to be operated at a lower mass flow rate increasing the obtainable specific energy.

Converging constrictor for an electrothermal arcjet thruster

There is provided a system for the manufacture of a diamond film. A plasma generator generates a hydrogen atom containing plasma stream into which a hydrocarbon containing gas is fed. The plasma dissociates the hydrocarbon to carbon radicals and carbon which are deposited on a substrate where the carbon crystallizes to a diamond film. The efficiency of the system is increased by heating the hydrogen source gas prior to generation of the plasma. Other means to increase the effectiveness of the system include using a plurality of plasma streams and shaping the plasma stream, A low internal strain, high quality optical film is generated by depositing the carbon on a substrate supported by a heat sink having nonuniform thermal conductivity such that the thermal gradient across the surface of the heat sink is less than about 8.degree. C./centimeter.

Apparatus for synthesizing diamond films utilizing an arc plasma

There is disclosed an anode for an electrothermal arcjet thruster. The anode includes a divergent nozzle having, in tandem, a recombination portion and an expansion portion. The expansion portion has a greater rate of divergence than the recombination portion. A regeneration channel containing flowing propellent gas extends internally within the anode adjacent the recombination portion. The combination of the biangle nozzle and the regeneration channel produces an arcjet thruster having a markedly increased thrust efficiency.

Increased efficiency arcjet thruster

An arcjet thruster is disclosed which has an electrically conductive anode body having an anode cavity therein which defines a nozzle symmetrical about a central axis. The anode cavity has a tandemly arranged divergent recombination portion and a divergent expansion portion. The expansion portion has a greater rate of divergence than the recombination portion. The anode body further preferably comprises a cylindrical constrictor portion upstream and in tandem with the recombination portion. An electrically conductive cylindrical cathode body is coaxially arranged and spaced from the anode body by a gap. An electrical current source connected to the cathode and the anode produces an electrical arc across the gap. A vortex flow of propellant gas is fed through the gap and through the nozzle to produce thrust. The vortex flow of propellant gas pushes the arc through the constrictor into one of the divergent portions of the nozzle. The recombination and expansion portions merge at a transition being between a divergence of 5 and 15 degrees and within a diameter ratio range of the transition to the constrictor of about 1.5 to 4.0. The divergent recombination portion causes a portion of the ionized and disassociated propellant gas passing therethrough to recombine, recovering frozen flow losses prior to entering the expansion portion and increasing the overall energy conversion efficiency of the thruster.

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Seattle, WA, United States of America

George W Butler