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| Number | Title | Issue Date |
| 7434762 | Retractable thrust vector control vane system and method A retractable thrust vector control system (10) for a rocket motor (26) that can generate an exhaust plume comprises at least one control vane (12) connectable to an attitude control assembly (20) that rotates the vane (12) about a... | 10/14/2008 |
| 7434384 | Fluid mixer with an integral fluid capture ducts forming auxiliary secondary chutes at the discharge end of said ducts A fluid mixer for mixing two fluid streams 40, 42 includes a set of main lobes 26 defining alternating primary and secondary main chutes 30, 32, one or more auxiliary lobes 28 intermediate two of the main lobes, and an auxiliary fluid cap... | 10/14/2008 |
| 7347041 | Rocket engine combustion chamber An improved engine construction, such as a rocket engine construction is provided. The engine construction comprises a combustion chamber, a smooth wall nozzle, and a transition zone between the chamber and the smooth wall nozzle. The transition zone has a coolant s... | 03/25/2008 |
| 7347425 | Rope seal for gas turbine engines A sealing arrangement in a gas turbine engine comprises a rope seal held against a sealing surface by a resilient seal carrier in which the rope seal lies. ... | 03/25/2008 |
| 7313910 | Jet vane thrust vector control system Disclosed is a jet vane thrust vector control (JV-TVC) system. A general system has many problems in design techniques considering actual operation environments, and does not have reliability in component assembly design. The JV-TVC system improves thrust vector con... | 01/01/2008 |
| 7308966 | Device for reducing jet engine exhaust noise using oscillating jets A device for reducing engine exhaust noise in an aircraft engine includes a number of oscillating jets which direct an oscillating flow into the engine exhaust. The oscillating jets are connected via channels to a turbomachinery source of high pressure gas, where th... | 12/18/2007 |
| 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 |
| 7296411 | Method and system for regulating internal fluid flow within an enclosed or semi-enclosed environment The present invention features a fluid flow regulator that functions to significantly influence fluid flow across the surface of an object, as well as to significantly effect the performance of the object subjected to the fluid. The fluid flow regulator comprises a ... | 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 |
| 7284487 | Single-piece stereolithographically-produced missile igniter Stereolithography is used to fabricate directly a single-piece, missile-usable, accurate, flightweight igniter without the use of intermediate, non-operational molds or prototypes in the fabrication process. The same prototype-less, direct stereolithography can be u... | 10/23/2007 |
| 7255353 | Flexible graphite sealing joint with metal jacket for high temperature The seal can be used at high temperature. It is composed of a central flexible graphite core (10) maintained in its shape by two metal cups (12) that do not touch. It is all surrounded by a tight sheath (15) enabling the flexible core (10... | 08/14/2007 |
| 7240493 | Method and device for reducing engine noise A method and device to reduce the noise produced by jet aircraft engines and/or other supersonic nozzles involves the use of corrugated engine seals (30) for the secondary internal divergent flaps (14) of the nozzle (10). Such corrugated seals (... | 07/10/2007 |
| 7229029 | Propulsion system A propulsion system for a jet- or rocket-propelled vehicle in which the resulting jet exhaust nozzle profile is a 3D spiral. The propulsion system can be applied to any jet- or rocket-propelled vehicle, including aircraft and watercraft. The propulsion system also c... | 06/12/2007 |
| 7188477 | High temperature dynamic seal for scramjet variable geometry A seal assembly for use in an engine, such as a scramjet engine, having a movable element, such as inlet cowl flap, is provided. The movable element has an outboard structural member which requires thermal protection. The seal assembly includes a sealing element and... | 03/13/2007 |
| 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 |
| 7090459 | Hybrid seal and system and method incorporating the same A seal having a first seal mechanism adapted for insertion between a first structure and a second structure, wherein the first structure is in communication with a first medium and the second structure is in communication with a second medium. The seal also includes... | 08/15/2006 |
| 7065957 | Segmented mixing device for jet engines and aircraft Disclosed is a means for reducing jet engine exhaust noise wherein mixing is enhanced between adjacent exhaust flows and between exhaust flow and free-stream flow. Also disclosed is a means for improving the thrust of jet engines and for reducing the noise and drag ... | 06/27/2006 |
| 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 |
| 7051511 | Method and arrangement for preventing encased explosives being caused to explode by an external fire This disclosure relates to a method and an arrangement for preventing explosives such as rocket engines from exploding while subjected to an external fire in an ammunition bunker. The basic principle underlying the invention is that the casing surrounding the explos... | 05/30/2006 |
| 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 |
| 7000853 | System and method for control of fluid dispense pump In a fluid pump and cartridge assembly, a cartridge includes a material inlet port, a material outlet port, and a feed screw. The feed screw delivers fluid to be dispensed from the fluid inlet to the outlet port. The fluid inlet is preferably elongated in a directio... | 02/21/2006 |
| 7000378 | Gas turbine engine exhaust nozzle having a noise attenuation device driven by shape memory material actuators A gas turbine engine exhaust nozzle arrangement for the flow of exhaust gases therethrough between an upstream end and a downstream end thereof comprising a nozzle and a plurality of tabs which extend in a generally axial direction from a downstream portion of the n... | 02/21/2006 |
| 6971229 | Confluent exhaust nozzle A gas turbine engine exhaust nozzle includes a nacelle having an inlet and main outlet at opposite ends, and a main duct extending therebetween. A secondary bypass duct extends radially through the nacelle upstream of the main outlet and includes an unobstructed sec... | 12/06/2005 |
| 6945031 | Recessed engine nacelle A gas turbine engine nacelle includes an inner skin surrounded by a radially outer skin. The inner skin terminates at an exhaust outlet. The outer skin terminates at a recess in the inner skin extending into a closed cavity under the outer skin. ... | 09/20/2005 |
| 6892959 | System and method for control of fluid dispense pump In a fluid pump and cartridge assembly, a cartridge includes a material inlet port, a material outlet port, and a feed screw. The feed screw delivers fluid to be dispensed from the fluid inlet to the outlet port. The fluid inlet is preferably elongated in a directio... | 05/17/2005 |
| 6820410 | Bifurcated turbofan nozzle A turbofan exhaust nozzle includes a fan duct defined between a fan nacelle and a core engine cowling. The fan duct includes a longitudinal endwall and a partition spaced therefrom to define a secondary flow duct. The fan duct also includes a primary outlet, and the... | 11/23/2004 |
| 6817184 | Nozzle extension A nozzle extension including flange elements of C/SiC is able to be manufactured relatively simply and provides sufficient physical properties. The carbon-fiber structure of the nozzle extension is wound, and a flange for fastening the nozzle extension to the nozzle... | 11/16/2004 |
| 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 |
| 6742335 | EGR control system and method for an internal combustion engine EGR mass fraction or a value indicative thereof can be calculated based on temperature measurements rather than mass flow and/or pressure measurements, hence negating the need for expensive and relatively unreliable measurement devices in an active EGR system for an... | 06/01/2004 |
| 6711901 | Rocket motor nozzle assemblies having vacuum plasma-sprayed refractory metal shell throat inserts, methods of making, and rocket motors including same The rocket motor nozzle assembly of this invention includes a throat insert and a carbon or silica protective eyelid. The throat insert has a carbon throat support and a refractory metal shell. The shell is positioned radially inside the throat support to cover the ... | 03/30/2004 |
| 6705076 | Rocket thrust chamber Thrust chamber housing for a driving mechanism for space travel applications which is fastened to an injection head with its first end and which includes a combustion chamber housing of a highly heat-resistant steel, a nozzle element of a platinum-iridium alloy, and... | 03/16/2004 |
| 6702300 | High temperature seal for large structural movements A high temperature sealing system is operative to seal an interface between adjacent hot structures and to minimize parasitic flow between such structures that move relative to one another in-plane or out-of-plane. The sealing system may be used to seal t... | 03/09/2004 |
| 6691505 | Fiber-reinforced rocket motor insulation Insulation for a rocket motor is provided, as is a method for insulating a rocket motor. The insulation includes a cured elastomer and vapor-grown carbon fibers dispersed in the cured elastomer. The cured elastomer is preferably formed from a precursor co... | 02/17/2004 |
| 6675571 | Apparatus for controlling the heat transfer to the nozzle wall of expander cycle rocket engines The invention relates to an apparatus for increasing the heat transfer to the coolant at the inside of a nozzle wall provided with coolant channels of expander cycle rocket engines. To achieve this the invention proposes that, to disturb the boundary laye... | 01/13/2004 |
| 6574952 | Apparatus for controlling the flow separation line of rocket nozzles The invention refers to an apparatus for controlling the flow separation line of rocket nozzles for reducing side loads. For obtaining this control it is suggested according to the invention that the inside of the nozzle (1) has circumferentially regular ... | 06/10/2003 |
| 6574964 | Rocket nozzle contour for flow separation control and side load reduction The invention refers to a full-flow rocket nozzle having a longitudinal contour essentially corresponding to a parabola. For obtaining a flow separation control and also a side load reduction the invention suggests that the parabola contour shape from the... | 06/10/2003 |
| 6572030 | Device for displacing to nozzle outlet or eliminating jet separation in rocket engine nozzles, and a nozzle including the device To control the separation of a hot gas ejection jet within a rocket engine nozzle, the device includes a jettisonable annular structure for placing around the outside wall of the nozzle at the gas cutlet section thereof, which structure defines a radial e... | 06/03/2003 |
| 6516606 | Aeroengine nacelle afterbodies The invention discloses an aeroengine nacelle afterbody of the type comprising a common nozzle for exhausting the mixed hot and cold gases originating respectively from the fan duct and from the aeroengine combustion chamber, the said nozzle having a long... | 02/11/2003 |
| 6479148 | Rocket assembly ablative materials formed from solvent-spun cellulosic precursors, and method of insulating or thermally protecting a rocket assembly with the same A rocket motor assembly is insulated or thermally protected with a rocket motor ablative material formed from a prepreg. The prepreg contains at least an impregnating resin matrix and, as a precursor prior to carbonization, either carded and yarn-spun sol... | 11/12/2002 |
