Did You Know...
...that a workman who left the soap mixing machine on too long was responsible for making Ivory Soap? He was so embarrassed by his mistake that he threw the mess in a stream. Imagine his dismay when the evidence of his error floated to the surface! Result: Ivory soap, the soap that floats.
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| Number | Title | Issue Date |
| 7963100 | Cooling system for high-speed vehicles and method of cooling high-speed vehicles A cooling system for a high-speed vehicle may comprise a combustor wall at least partially enclosing a combustor and which is cooled using a coolant circulating in a Brayton cycle. The heated coolant may be expanded in a turbine, transfer heat to a fuel within a hea... | 06/21/2011 |
| 7900438 | Heat transfer system and method for turbine engine using heat pipes A heat transfer system is provided for a turbine engine of the type including an annular casing with an array of generally radially-extending strut members disposed therein. The heat transfer system includes at least one primary heat pipe disposed at least partially... | 03/08/2011 |
| 7900437 | Heat transfer system and method for turbine engine using heat pipes A heat transfer system is provided for a turbine engine of the type including an annular casing with an array of thermally conductive, generally radially-extending strut members disposed therein. The heat transfer system includes at least one arcuate heat pipe dispo... | 03/08/2011 |
| 7845159 | Heat pipe-based cooling apparatus and method for turbine engine A cooling apparatus is provided for a turbine engine of the type including an cowling with an outer surface defined by a skin exposed to an external air flow. The cooling apparatus includes at least one heat pipe disposed in the cowling. The heat pipe has a first en... | 12/07/2010 |
| 7481784 | Wall structure A wall structure (2) and components incorporating such a wall structure that are intended to be exposed to high thermal loads. The wall structure (2) includes at least two layers; a first layer (5) and a second layer (6), the second layer... | 01/27/2009 |
| 7464537 | Heat transfer enhancement features for a tubular wall combustion chamber A combustion chamber for use in an engine, such as a rocket engine, has an inner wall with a corrugated configuration. The inner wall is formed with a plurality of tubes for carrying a coolant. As a result of the tubular construction, the inner wall has a plurality ... | 12/16/2008 |
| 7389636 | Booster rocket engine using gaseous hydrocarbon in catalytically enhanced gas generator cycle A process and a system for delivering a propellant combination to a rocket engine is described. The process comprises the steps of providing a flow of a hydrocarbon propellant fuel, raising the pressure of the hydrocarbon propellant fuel, cracking the hydrocarbon pr... | 06/24/2008 |
| 7377100 | Bypass duct fluid cooler A method and apparatus for cooling a fluid in a bypass gas turbine engine involves directing the fluid to the bypass duct of the engine to allow for heat exchange from the fluid to bypass air passing through the bypass air duct. ... | 05/27/2008 |
| 7373774 | Enhanced performance torroidal coolant-collection manifold A system for cooling a combustion chamber of an engine, such as a rocket engine, is provided. The system has a plurality of coolant tubes or passages surrounding the combustion chamber, a torroidal coolant-collection manifold for receiving coolant from the coolant t... | 05/20/2008 |
| 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 |
| 7305816 | Rocket augmentation for combined cycle turboaccelerator jet engine An engine for creating a propulsive force includes turbomachinery for generating a flow of hot exhaust gases and an initial thrust force, an augmentor positioned aft of the turbomachinery, and a system for injecting an oxidizer, which preferably undergoes thermal de... | 12/11/2007 |
| 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 |
| 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 |
| 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 |
| 7293403 | Combustion chamber with internal jacket made of a ceramic composite material and process for manufacture A combustion chamber, in particular for a rocket drive, includes at least one jacket madeof a composite material with a ceramic matrix. The composite material contains a fibrous structure made of carbon-containing fibers, and the fibrous structure comprises layers o... | 11/13/2007 |
| 7260926 | Thermal management system for an aircraft A fuel based thermal management system includes a fuel stabilization system which permits the fuel to exceed the traditional coking temperatures. High temperature components are arranged along the fuel flow path such that even at the higher operating temperatures th... | 08/28/2007 |
| 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 |
| 7188478 | Power generation system and method of operating same A power generation system comprising a liquid-cooled electrolyzer operable to produce a supply of hydrogen from water is provided. The power generation system may also comprise a steam turbine and a steam production device operable to produce a supply of steam to th... | 03/13/2007 |
| 7178339 | Closed-loop cooling system for a hydrogen/oxygen based combustor A closed-loop cooling system is provided for a hydrogen/oxygen based combustor. A combustion reaction between hydrogen and oxygen in the combustor produces steam. The steam is used to generate work from a turbine shaft, which is used to drive a propulsion system for... | 02/20/2007 |
| 7171813 | Fuel injection nozzle for gas turbine combustor, gas turbine combustor, and gas turbine A fuel injection nozzle has a cylindrical nozzle body having a cavity where fuel passes through. A plurality of hollow spokes, each having an aerofoil cross section, are provided around the nozzle body. Each hollow spoke has four fuel injection holes in total on bot... | 02/06/2007 |
| 7131612 | Nacelle inlet lip anti-icing with engine oil A nacelle for housing a gas turbine engine having a pressurized oil system for lubricating components thereof comprises an inlet lip defining a leading edge of the nacelle, the inlet lip having a conduit therein in fluid flow communication with the pressurized oil s... | 11/07/2006 |
| 7117675 | Cooling of liquid fuel components to eliminate coking A system for cooling at least one gas turbine liquid fuel component located in a high temperature environment to eliminate coking in the component is disclosed. The system includes a sleeve surrounding the liquid fuel component, a device for providing a current of c... | 10/10/2006 |
| 7117680 | Cooling scheme for scramjet variable geometry hardware A cooling system for use in an engine having an element to be cooled includes at least one cooling channel on a first side of the element, at least one cooling channel on a second side of the element, and the at least one cooling channel on the first side communicat... | 10/10/2006 |
| 7051513 | Rocket engine tubular chamber with single piece jacket A method for forming a coolant system for a rocket engine combustion chamber is provided. The method comprises the steps of providing a plurality of tubes formed and shaped into the profile of a nozzle with each of the tubes having a constantly expanding cross secti... | 05/30/2006 |
| 7013964 | High temperature heat exchanger structure To provide a thermal connection that can withstand mechanical stress in a high temperature structure comprising a panel having one face carrying a circuit made up of tubes in which a fluid flows, the outside walls of the tubes are covered in respective high thermal ... | 03/21/2006 |
| 7013636 | System and method for controlling the temperature and infrared signature of an engine A system and method for cooling at least a portion of an engine are provided. The engine is cooled using a fuel, such as a high heat sink fuel, that is subsequently used for combustion in the engine. The fuel can be used to cool one or more of the gases and/or compo... | 03/21/2006 |
| 6996991 | Fuel injection system for a turbine engine A fuel system for a turbine engine for reducing CO emissions caused during fuel staging processes while the turbine engine operates at reduced loads. The fuel system may include a first premix injector assembly and a second premix injector assembly, each formed from... | 02/14/2006 |
| 6990797 | Methods and apparatus for operating gas turbine engines A method facilitates assembling a turbine engine to facilitate preventing ice accumulation on the turbine engine during engine operation. The method comprises coupling at least one heat pipe to the engine such that a first end of the at least one heat pipe is couple... | 01/31/2006 |
| 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 |
| 6951317 | Vehicle, lightweight pneumatic pilot valve and related systems therefor A vehicle, such as a missile, with a pilot valve system controls the vehicle's thrust valves despite a hostile propellant gas environment. The pilot valve system can have one or more pilot valves. Using refractory elements, the pilot valve ball reciprocates between ... | 10/04/2005 |
| 6945032 | Method for manufacturing outlet nozzles for rocket engines A wall structure capable of withstanding high thermal load, including a wall structure with an inner wall, an outer wall positioned about the inner wall, and distancing elements located between the inner and outer walls. The distancing elements are joined to at leas... | 09/20/2005 |
| 6939392 | System and method for thermal management A system for the management of thermal transfer in a gas turbine engine includes a heat generating sub-system in operable communication with the engine, a fuel source to supply a fuel, a fuel stabilization unit to receive the fuel from the fuel source and to provide... | 09/06/2005 |
| 6925812 | Rotary injector A radially-extending arm is adapted to rotate within a stream of first fluid flowing thereacross. In one embodiment, the arm comprises a plurality of lands located at different radial distances from the axis of rotation, and a port located on each land is operativel... | 08/09/2005 |
| 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 |
| 6918255 | Cooling of liquid fuel components to eliminate coking A system for cooling at least one gas turbine liquid fuel component located in a high temperature environment to eliminate coking in the component is disclosed. The system includes a sleeve surrounding the liquid fuel component, a device for providing a current of c... | 07/19/2005 |
| 6913068 | Engine exhaust heat recovering apparatus A circulating path 12 is provided for circulating a heat transfer medium across the cooling section 6A and an exhaust heat exchanger 9. The circulating path 12 is communicated to an output heat exchanger which is mounted on a hot water st... | 07/05/2005 |
