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Ballistic resistant body covering
A ballistic resistant body covering for protecting the torso, groin and neck area from ballistic missiles.
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| Number | Title | Issue Date |
| 7775460 | Combustion nozzle fluidic injection assembly A fluid flow system for use with a gas turbine engine includes an exhaust nozzle, a primary air supply valve, a distribution manifold connected to the primary fluid supply valve and in fluid communication therewith, and a plurality of fluid injector assemblies posit... | 08/17/2010 |
| 7658337 | Fluid vectoring nozzle A fluid vectoring nozzle comprises flow vectoring means suitable for selectively producing a fluid dynamic throat in the nozzle in a plane oblique to the axis of the nozzle, such that in operation fluid flow passing through the throat is rotated about an axis parall... | 02/09/2010 |
| 7401682 | Architecture for an acoustic liner An acoustic liner 20 includes a remote panel 26, a perforated proximate panel 22 transversely spaced from the remote panel and one or more partitions 32 spanning across the space between the panels. At least one baffle 44 cooperate... | 07/22/2008 |
| 7392651 | Turbomachine nozzle cover for reducing jet noise A cowl for a turbomachine nozzle, the cowl having a plurality of repeated patterns disposed circumferentially at a trailing edge, each pattern being asymmetrical about a midplane of the pattern containing a longitudinal axis of the cowl, and each pattern having a fi... | 07/01/2008 |
| 7377099 | System and method for cooling lateral edge regions of a divergent seal of an axisymmetric nozzle An axisymmetric nozzle for a gas turbine engine has divergent flaps and seals disposed about a central longitudinal axis thereof. The divergent flaps and seals each have an inner surface defining cooling air inlet holes at an upstream portion, cooling air exit holes... | 05/27/2008 |
| 7353656 | Method and apparatus for achieving power augmentation in gas turbines using wet compression A gas turbine unit and method of operation thereof are disclosed. A very quick and easily controllable augmentation or reduction of shaft power produced by the gas turbine unit, in particular of large gas turbine units exhibiting a pressure ratio larger than 15 bar,... | 04/08/2008 |
| 7353654 | Method and apparatus for achieving power augmentation in gas turbines using wet compression A gas turbine unit and method of operation thereof are disclosed. A very quick and easily controllable augmentation or reduction of shaft power produced by the gas turbine unit, in particular of large gas turbine units exhibiting a pressure ratio larger than 15 bar,... | 04/08/2008 |
| 7354029 | Apparatus and method for treating process fluids A process fluid treating apparatus includes an ejector assembly fluidically connected to a process fluid supply assembly. A Coanda airfoil is located in the ejector assembly. Primary fluid is injected into the ejector duct to form a Coanda layer. A process fluid, or... | 04/08/2008 |
| 7353655 | Method and apparatus for achieving power augmentation in gas turbine using wet compression A gas turbine unit as well as a method for operating a gas turbine with high-pressure turbine and a low-pressure turbine unit are disclosed. A very quick and at the same time easily controllable augmentation or reduction of the shaft power of the gas turbine unit ca... | 04/08/2008 |
| 7310939 | Device for reducing the jet noise of a turbomachine A device for reducing the jet noise of a turbomachine, the turbomachine having a longitudinal axis and a substantially cylindrical nozzle extending along the longitudinal axis of the turbomachine, having a downstream end for mixing the flows of gas inside and outsid... | 12/25/2007 |
| 7311175 | Acoustic liner with bypass cooling An acoustic liner 20 includes a remote panel 26, a proximate panel 28 transversely spaced from the remote panel and a resonator chamber 34b residing between the panels. Perforations 38 penetrate the proximate panel in regist... | 12/25/2007 |
| 7299635 | Device for mixing two flows of fluid which are initially guided separate from one another in a bypass jet engine The invention relates to a device for mixing two fluid flows, initially guided separately from one another, in a two-circuit reaction engine, a mixing tube which encloses a hot core stream being provided, along the outer shaped lateral surface of which a cold bypass... | 11/27/2007 |
| 7296397 | Ventilation system for a convergent divergent exhaust nozzle The invention relates to a ventilation system for a convergent divergent exhaust nozzle in a bypass turbojet comprising an afterburn chamber surrounded by an annular passage through which circulates a stream of cooling air, a convergent divergent axisymmetric nozzle... | 11/20/2007 |
| 7293401 | Jet engine noise suppressor An embodiment of the invention is a technique to suppress noise in a jet engine. A noise suppressor includes an exhaust duct to exhaust a first stream from an air stream taken from an inlet. The exhaust duct has an exit end. The air stream is divided into the first ... | 11/13/2007 |
| 7264203 | Spider actuated thrust reverser A thrust reverser includes reverser doors circumferentially spaced around a nacelle. An arcuate yoke is disposed coaxially around the nacelle. An actuator is mounted tangentially to the yoke for rotary movement thereof. Actuator rods join the doors to the yoke for s... | 09/04/2007 |
| 7251927 | Jet nozzle mixer A second stage external jet nozzle mixer (20) includes identically formed lobes which equal in number the lobes of the first stage internal mixer. The external mixer works with the internal mixer, and furthers the mixing of the jet engine internal bypass flow... | 08/07/2007 |
| 7250130 | Method and inspection device used for the cyclic production of injection molded parts The invention relates to a manufacturing inspection method for the cyclic production of injection-molded parts in multi-cavity casting molds involving a row-by-row monitoring of the injection-molded parts after they are removed from the casting molds, said monitorin... | 07/31/2007 |
| 7246481 | Methods and apparatus for operating gas turbine engines A method for operating a gas turbine engine includes channeling compressed air from the gas turbine engine to a noise suppression system, and selectively operating the noise suppression system such that air discharged from the noise suppression system generates a st... | 07/24/2007 |
| 7174718 | Device for controlling propulsive jet mixing for aircraft jet engines A device for controlling propulsive gas mixing at an outlet of an aircraft jet engine, wherein propulsive jets are composed of a hot primary jet exiting from a nozzle of the jet engine and a secondary flux flowing between an external wall of the nozzle and an intern... | 02/13/2007 |
| 7152410 | System and method for dumping surge flow into eductor primary nozzle for free turbine A method and apparatus for dumping surge bleed air into a primary nozzle of a free gas turbine engine. The surge bleed air is introduced into gas turbine exhaust flow within the primary nozzle to create a mixed flow which may be used as a combined driver flow to com... | 12/26/2006 |
| 7111448 | Jet nozzle mixer An external jet nozzle mixer includes identically formed lobes. The external mixer works with the internal mixer further to mix the engine internal bypass flow with the internal jet engine core flow to level the disparate flow velocities, to reduce the peak velociti... | 09/26/2006 |
| 7096662 | Variable area throat exhaust nozzle with vectorable sideways shifting of exhaust flow A nozzle includes a sideways split and aftwardly swept nozzle ramp extends between a fixed lower nozzle wall and a pivotal upper nozzle wall pivotally connected to an aft end of the nozzle and operable to vary a throat area of a throat of the nozzle. The upper and l... | 08/29/2006 |
| 7055329 | Method and apparatus for noise attenuation for gas turbine engines using at least one synthetic jet actuator for injecting air A method enables a gas turbine engine to be operated. The method comprises channeling exhaust gases from a core engine through an exhaust assembly and past at least one flow boundary surface, and selectively operating a noise suppression system extending from the at... | 06/06/2006 |
| 7055307 | Vectorable nozzle with sideways pivotable ramp A vectorable nozzle includes a longitudinally extending upper fixed wall spaced upwardly and aftwardly of a longitudinally extending lower fixed wall and an aftwardly swept fixed ramp extending between the upper and lower fixed walls. The upper and lower fixed walls... | 06/06/2006 |
| 7048276 | Flying device for IR flying target representation A flying device for IR flying target representation with at least one infrared radiator (2). An infrared radiator (2) is arranged inside the exhaust gas flow of a convected heat-generating unit so that the exhaust gas stream completely encloses the sur... | 05/23/2006 |
| 7043898 | Combined exhaust duct and mixer for a gas turbine engine A gas turbine engine including a gas exhaust duct assembly which comprises an annular shroud forming at least a section of an inner wall of a gas exhaust duct, a plurality of strut members radially projecting from the shroud, and a plurality of insert members. The s... | 05/16/2006 |
| 7032835 | Convergent/divergent nozzle with modulated cooling A nozzle system includes a multiple of circumferentially distributed convergent flaps, divergent flaps and inter-flap seals which circumscribe an engine centerline and define the radial outer boundary of a gas path. Each divergent flap includes a multiple of cooling... | 04/25/2006 |
| 7017332 | Lobe mixer for jet flow There is disclosed a lobe mixer comprising: a cylindrical partition wall 22 which partitions a high-speed inner flow from a low-speed outer flow; a lobe portion 24 which is disposed on a downstream side of the partition wall and whose transverse sectio... | 03/28/2006 |
| 7010905 | Ventilated confluent exhaust nozzle An exhaust nozzle includes an outer duct surrounding an inner duct. The inner duct includes a main outlet, and a row of apertures spaced upstream therefrom. The outer duct includes a row of intakes at a forward end, an auxiliary outlet at an aft end, and surrounds t... | 03/14/2006 |
| 6996973 | Method of achieving jet separation of an un-separated flow in a divergent nozzle body of a rocket engine The invention relates to a rocket engine nozzle comprising a system for controlling jet separation of the flow in the nozzle, wherein said control system exhibits a plurality of separation triggering elements (5, 10) arranged in such a way as to generate, fro... | 02/14/2006 |
| 6962044 | Method and apparatus of asymmetric injection into subsonic flow of a high aspect ratio/complex geometry nozzle The present invention reveals a method and apparatus for controlling the effective area and thrust vector angle of a fluid flow. In one embodiment, the fluid flow is controlled in an advanced, high aspect ratio, complex aperture geometry nozzle using asymmetric inje... | 11/08/2005 |
| 6935098 | Turbomachine nozzle with noise reduction A nozzle comprising an inner barrel, a centerbody disposed inside the inner barrel so as to define a first channel for a primary flow, and an outer barrel surrounding the inner barrel so as to define a second annular channel for a secondary flow, the free end of the... | 08/30/2005 |
| 6937181 | Device for reducing the signature of hot exhausting gases The invention relates to a device for exhausting hot gases with a reduced signature, for instance exhaust gases from an exhaust (7, 8) of a tank. The device is of the type comprising a means for mixing (9, 33) of the hot gases with fresh air from the e... | 08/30/2005 |
| 6854260 | Jet nozzle mixer An external jet nozzle mixer (20) includes identically formed lobes (48), equal in number those of the internal mixer (42). External mixer (20) works with internal mixer (42), further to mix the engine internal bypass flow with the... | 02/15/2005 |
| 6837038 | Variable cycle boost propulsor The present invention relates to a variable cycle boost propulsor system for use on an aircraft. The variable cycle boost propulsor system includes an engine, a turbine, a fan connected to the turbine, and a valve system for delivering the fluid output from the engi... | 01/04/2005 |
| 6804947 | Device for cooling the common nozzle of a turbojet pod The invention relates to a dual flow turbojet comprising an engine of axis X housed completely inside a tubular pod whose inside wall co-operates with the case of said engine to define an annular passage for a secondary flow delivered by a fan, said pod having an ai... | 10/19/2004 |
| 6804948 | Lobe mixer for jet engine A lobe mixer (22) used in jet engines, is provided with diameter expansion portions (22a) in which the diameters gradually increase in the downstream direction, in which adjacent diameter expansion portions have different diameters from each oth... | 10/19/2004 |
| 6792748 | Cooling system for a gas turbine engine post-combustion jet nozzle The invention concerns a cooling system for a post combustion jet nozzle, The jet nozzle includes a primary gas duct allowing a primary flow of gas, and a secondary air duct allowing a secondary flow of air. The secondary air duct surrounds the primary gas duct and ... | 09/21/2004 |
| 6742721 | Shock wave aerosolization method and apparatus A pneumatic inhaler that is able to deliver a controlled burst or dose of aerosol from a reservoir of liquid medication. The inhaler is suitable for the aerosolization of liquid medication that is in solution or suspension form. The inhaler is also ideal for the del... | 06/01/2004 |
| 6640537 | Aero-engine exhaust jet noise reduction assembly A gas turbine engine of a fan bypass type includes an exhaust shroud having a perforated tubular wall extending between a forward end and an aft end. The exhaust shroud is adapted to be affixed to a gas turbine engine exhaust for discharging engine exhaus... | 11/04/2003 |
