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| Number | Title | Issue Date |
| 7854395 | Rocket combustion chamber with jacket The present invention relates to rocket engine combustion chambers, and more particularly to an improved rocket engine combustion chamber having a jacket. In some embodiments, a combustion system for a rocket engine includes an injector, a cylindrical combustion cha... | 12/21/2010 |
| 7406827 | Apparatus for injecting a fuel-air mixture into a combustion chamber In a fuel lance by means of which fuels can be injected, via at least two separate passages, into a combustion chamber alternately or simultaneously at an injection location arranged substantially at the lance tip, reliable operation is achieved, without the risk of... | 08/05/2008 |
| 7370469 | Rocket chamber heat exchanger A rocket engine chamber has a back structure and a heat exchanger structure located radially inwardly of the back structure. The heat exchanger structure has a plurality of integrally formed cooling passageways with adjacent ones of the passageways having a common s... | 05/13/2008 |
| 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 |
| 7343732 | Rocket engine chamber with layered internal wall channels A combustion chamber/supersonic nozzle assembly is cooled by an array of coolant channels in the wall of the assembly with coolant being fed to the assembly at the throat plane between the subsonic (convergent) and supersonic (divergent) sections. A minor portion of... | 03/18/2008 |
| 7302794 | Rocket engine member and a method for manufacturing a rocket engine member Method and arrangement for providing a liquid fuel rocket engine member having a load bearing wall structure (11,14) including a plurality of cooling channels (11) for handling a coolant flow. Each cooling channel (11) is provided with a flow gu... | 12/04/2007 |
| 7299551 | Method of assembling a rocket engine with a transition zone between the combustion chamber and the coolant system 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... | 11/27/2007 |
| 7299622 | Component for being subjected to high thermal load during operation and a method for manufacturing such a component Method and arrangement for providing a component (1) for being subjected to high thermal load during operation. The component includes a wall structure, which defines an inner space for gas flow. The component is formed by at least a first part (5) tha... | 11/27/2007 |
| 7269951 | Throat retention apparatus for hot gas applications A nozzle for use in a hot gas valve is provided that includes a housing, an insert, and a throat retainer. The housing is constructed of an insulating material and has a flow path formed therein. The flow path has a throat section. The insert is made of material cap... | 09/18/2007 |
| 7234294 | Outlet nozzle and a method for manufacturing an outlet nozzle Method and arrangement for providing an outlet nozzle (10) for use in a liquid fuel rocket engine. The nozzle forms a body of revolution having an axis (11) of revolution and a cross section that varies in diameter along said axis. The nozzle has a wal... | 06/26/2007 |
| 7213392 | 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... | 05/08/2007 |
| 7188417 | Advanced L-channel welded nozzle design A fluid flow nozzle is formed by a plurality of adjacent L-shaped channels forming successive channel pairs. Each channel has a linking member joined to a radial member. Each linking member is welded to an adjacent linking member forming a contiguous surface of link... | 03/13/2007 |
| 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 |
| 7117682 | Turbojet axisymmetric nozzle controlled hot flap shutter A controlled hot flap shutter for a turbojet nozzle includes a friction surface made of metal, and including straight lateral flanks to reduce the gap between each controlled hot flap shutter and the tracking flap shutters adjacent thereto. ... | 10/10/2006 |
| 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 |
| 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 |
| 7017333 | Wall structure A wall structure (2) configured to be exposed to a thermal load. The wall structure having at least two layers including a first layer (5) and a second layer (6). The second layer (6) is located closer to a source of the thermal load than... | 03/28/2006 |
| 6997346 | Apparatus and method for reducing buildup of particulate matter in particulate-matter-delivery systems The present disclosure provides approaches for reducing buildup of particulate-matter in particulate-matter-delivery systems. In some embodiments, a trough-shaped feeder is provided in which a rectangular-to-elliptical conduit extends from the trough-shaped feeder. ... | 02/14/2006 |
| 6966176 | System and fabrication method for actively cooling high performance components The present invention is directed toward a coolant system and method for fabricating a coolant system for actively cooling high performance components utilizing a plurality of feed channels that receive coolant from a manifold through coolant feed tubes and supply c... | 11/22/2005 |
| 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 |
| 6948317 | Methods and apparatus for flade engine nozzle A method for adjusting a throat area of a jet aircraft exhaust nozzle assembly includes positioning a lower structure within a substantially rectangular nozzle assembly, coupling a ramp flap to the lower structure, and coupling an outer flap to the nozzle assembly s... | 09/27/2005 |
| 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 |
| 6920750 | Rocket engine member and a method for manufacturing a rocket engine member Method and arrangement for providing liquid fuel rocket engine member (10). The member forms a body of revolution having an axis of revolution and a cross section that varies in diameter along said axis. The wall structure includes a plurality of cooling chan... | 07/26/2005 |
| 6912782 | Forming and assembly method for multi-axial pivoting combustor liner in gas turbine engine A multi-axial pivoting liner within the combustion system of a turbine engine allows the system to work with minimum thermal interference, especially during system operation at transient conditions, by allowing the liner to pivot and slide about its centerline and r... | 07/05/2005 |
| 6907920 | Heat exchanger panel The present invention relates to a heat exchanger panel which has broad utility in high temperature environments. The heat exchanger panel has a first panel, a second panel, and at least one fluid containment device positioned intermediate the first and second panel... | 06/21/2005 |
| 6883220 | Method for forming a tube-walled article A method for forming an article having a wall that is at least partially fabricated from tubing. The methodology employs a pressurized fluid to deform the tubing such that an outer surface of the tubing substantially conforms to a predetermined first wall configurat... | 04/26/2005 |
| 6829884 | Rocket engine combustion chamber having multiple conformal throat supports In a first assembly step a coolant liner is formed having an outside surface. A plurality of coolant channels are formed on the outside surface. At least two inner conformal throat support sections and at least two outer conformal throat support sections are formed.... | 12/14/2004 |
| 6802179 | Nozzle with spiral internal cooling channels A convergent-divergent rocket nozzle is formed by joining two coaxially aligned conical sections at a throat plane, each diverging outward from the throat plane. Coolant channels formed in the wall of the nozzle are arranged in spirals around the nozzle axis. Prefer... | 10/12/2004 |
| 6799418 | Rocket engine member and method for manufacturing a rocket engine member Method and arrangement for providing a liquid fuel rocket engine member (10). The member has a load bearing wall structure (14) having a plurality of cooling channels (11). For improving the heat transfer, a material with a higher thermal conduc... | 10/05/2004 |
| 6799417 | Diversion of combustion gas within a rocket engine to preheat fuel Heat is extracted from the combustion gas in a rocket engine combustion chamber by diverting portions of the gas through channels in the nozzle wall. The channels are layered between channels of coolant, which in expander cycle rocket engines is uncombusted fuel, to... | 10/05/2004 |
| 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 |
| 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 |
| 6640538 | Combustion chamber cooling structure for a rocket engine A combustion chamber structure (1) comprising a plurality of cooling ducts (31, 41) extending in the longitudinal direction of the combustion chamber structure (1), whereby the combustion chamber structure (1) is rotationally symmetrical in relation to an... | 11/04/2003 |
| 6637188 | Rocket engine combustion chamber with enhanced heat transfer to cooling jacket A combustion chamber for a rocket engine expels a hot stream of gas and has a cooling device. The inner wall of the combustion chamber adjoins the cooling device and contains depressions formed in such a way that the stable outer layer of the stream of ga... | 10/28/2003 |
| 6584766 | Methods and apparatus for minimizing thermal stresses in a centerbody A centerbody for a gas turbine engine includes a thermal control system which minimizes the thermal stresses between the centerbody and at least one stiffener. The centerbody stiffener extends radially inward from a centerbody shell. A cavity is defined w... | 07/01/2003 |
| 6470671 | Coolable nozzle and method for producing such a nozzle for a rocket engine A regeneratively coolable nozzle for a rocket engine is formed by winding a tubular material (6) onto a winding mandrel to produce a helical composite structure (5), through which a coolant can flow during operation of the nozzle. The spiral composite str... | 10/29/2002 |
| 6467253 | Nozzle structure for rocket nozzles having cooled nozzle wall The invention relates to a nozzle structure for rocket nozzles having a cooled nozzle wall comprising a large member of closely spaced cooling channels (2) extending from the inlet end of the nozzle to its outlet end. To facilitate the production of the c... | 10/22/2002 |
| 6389801 | Jet propulsion power unit with non-metal components A rocket engine has a combustion chamber and an expansion chamber interconnected by a nozzle. Both chambers and the nozzle are made of carbon fiber reinforced silicon carbide formed as a monolithic rocket engine body or formed in sections bonded to each o... | 05/21/2002 |
| 6308914 | Apparatus for the suppression of infra red emissions from an engine An apparatus for the suppression of infra red emissions from an engine includes a suppressor body through which pass exhaust gases from the engine, the suppressor body having an inlet means for air which is mixed within the suppressor body with the hot ex... | 10/30/2001 |
| 6182440 | Infrared radiation coanda suppressor An infrared radiation Coanda suppressor of an exhaust system encloses a Coanda surface for guiding exhaust gases into the atmosphere. The infrared radiation suppressor further uses cooling films for reducing the temperature of the Coanda surface and other... | 02/06/2001 |
