Did You Know...
...that one person who claimed to be the inventor of the television is Russian emigre Vladimir Zworykin? In 1929 David Sarnoff, founder of RCA, asked Zworykin what it would take to develop TV for commercial use. He said: a year and a half and $100,000. In reality, it took 20 years and $50 million! Before his death in 1982 at the age of 92, Zworykin said of his invention: "The technique is wonderful. It is beyond my expectations. But the programs! I would never let my children even come close to this thing."
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| Number | Title | Issue Date |
| 7997062 | Dual channel regulated fuel-oil heat exchanger A gas turbine engine includes a fuel-oil heat exchange system in which the fuel is continuously heated by a primary hot oil flow in a primary fuel-oil heat exchanger and the fuel is selectively heated in a secondary fuel-oil heat exchanger by a secondary hot oil flo... | 08/16/2011 |
| 7997061 | Turbojet engine for aircraft, propulsion unit comprising such a turbojet engine and aircraft comprising such a propulsion unit A propulsion unit comprises a turbojet engine and a thermal exchanger, situated above the turbojet engine. The turbojet engine comprises a regulation device to regulate an air flow-rate in a cooling air lead-in conduit conveying a stream of cooling air into a therma... | 08/16/2011 |
| 7984606 | Systems and methods for thermal management in a gas turbine powerplant A thermal management system for a gas turbine powerplant with an engine oil line and an engine fuel line incorporates a heat transfer control module that includes a reversible heat pump with a heat pump compressor for circulating working fluid in forward and reverse... | 07/26/2011 |
| 7954311 | Ammonia vapor management system and method A method is described for managing vapors generated from an ammonia-containing reductant delivery system. The method may include generating ammonia vapors in a first storage device and storing said generated ammonia vapors in a second storage device. Further, the me... | 06/07/2011 |
| 7926261 | Turbofan provided with a pre-cooler The invention is a turbofan provided with a pre-cooler. In order to evacuate the heated cool air stream, at least one discharge pipe is arranged in a chamber and connects the pre-cooler to at least one discharge orifice provided in the inner fairing, in output of an... | 04/19/2011 |
| 7895823 | Heat exchanger for a rocket engine A cylindrical rocket engine exhaust duct has a liner that fits inside an outer jacket. The outer periphery of the liner has circumferentially spaced ribs defining a sinuous path for a fluid to be heated. The liner has a least one, preferably several, transverse fins... | 03/01/2011 |
| 7886520 | Gas turbine engine Within a turbine engine a heat exchanger may be provided to cool compressor air flows to be utilized for cabin ventilation or other functions. A fluid flow acting as a coolant for the heat exchanger is generally drawn from the by-pass duct of the engine and a dedica... | 02/15/2011 |
| 7810311 | Cooling exchanger ducts A heat exchange system for use in operating equipment in which a working fluid is utilized in providing selected operations thereof, including for use in lubricating systems for aircraft turbofan engine equipment, the heat exchange system for providing air and worki... | 10/12/2010 |
| 7810312 | Heat exchanger arrangement In certain circumstances recovery of a fluid flow presented through a heat exchanger into another flow can create problems with respect to drag and loss of thrust. In gas turbine engines heat exchangers are utilized for providing cooling of other flows such as in re... | 10/12/2010 |
| 7765788 | Cooling exchanger duct A heat exchange system for use in operating equipment in which a working fluid is utilized in providing selected operations thereof, including for use in lubricating systems for aircraft turbofan engine equipment, the heat exchange system for providing air and worki... | 08/03/2010 |
| 7757477 | Convergent divergent nozzle with slot cooled nozzle liner A nozzle system includes a multitude of circumferentially distributed convergent flaps and seals that circumscribe an engine centerline. A cooling liner body cooperates with a cooling liner panel attached to respective convergent flaps and convergent seals to define... | 07/20/2010 |
| 7716913 | Engine An engine (110, 210) for moving a conveyance (132) through a fluid includes first and second pressure creating means (13, 14) for pressurising an engine airflow, and intercooling means (116, 290, 292) for cooling the engine airflow betwee... | 05/18/2010 |
| 7581385 | Metering sheet and iso-grid arrangement for a non axi-symmetric shaped cooling liner within a gas turbine engine exhaust duct A cooling liner having a liner hot sheet formed as a relatively thick iso-grid structure having iso-grid ribs, which extend from a surface between the ribs. A multitude of metering sheets are mounted directly to the liner hot sheet surface. Each metering sheet is mo... | 09/01/2009 |
| 7398641 | Aeroengine intake having a heat exchanger within an annular closed chamber A gas turbine engine comprising a nacelle having an intake, the intake defining a generally annular chamber, an engine accessory and a heat exchanger for cooling a fluid of the accessory. The chamber is closed and the heat exchanger is disposed within the chamber op... | 07/15/2008 |
| 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 |
| 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 |
| 7373773 | Gas turbine installation, cooling air supplying method and method of modifying a gas turbine installation The invention provides a gas turbine installation, a cooling air supplying method, a method of modifying a gas turbine installation, which can reduce the amount of compressed air extracted for cooling of an exhaust plenum and which can increase energy efficiency. Th... | 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 |
| 7350360 | Annular combustor for a gas turbine The invention relates to an annular combustor (13) for a gas turbine (10), into which combustor (13) burners (14, 15) open on an inlet side, and which combustor (13) extends in the axial direction from the inlet side to an outlet s... | 04/01/2008 |
| 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 |
| 7334396 | Method and apparatus for a rocket engine power cycle A system for providing an oxidizer and a fuel to a rocket engine is provided. The system includes a fuel supply system. The fuel supply system includes a fuel pump that pumps fuel to the rocket engine. The system includes a coolant supply system that supplies a cool... | 02/26/2008 |
| 7334411 | Gas turbine heat exchanger assembly and method for fabricating same A method for assembling a gas turbine engine includes fabricating a heat exchanger that includes a first manifold including an inlet and an outlet, a first quantity of heat exchanger elements coupled in flow communication with the manifold inlet, a second quantity o... | 02/26/2008 |
| 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 |
| 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 |
| 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 |
| 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 |
| 7291853 | Discharge produced plasma EUV light source An DPP EUV source is disclosed which may comprise a debris mitigation apparatus employing a metal halogen gas producing a metal halide from debris exiting the plasma. The EUV source may have a debris shield that may comprise a plurality of curvilinear shield members... | 11/06/2007 |
| 7278256 | Pulsed combustion engine A pulsed combustion apparatus includes a conduit having an outer wall and an inner wall. The inner wall has a number of apertures. An interior space is separated from the outer wall by the inner wall. An induction system is positioned to cyclicly admit charges to th... | 10/09/2007 |
| 7270175 | Extended impingement cooling device and method An extended impingement cooling structure to cool outside an air supply plenum comprises an inner wall; an impingement sheet; a series of supports to maintain the inner wall in spaced relation to the impingement sheet, and a baffle supported between the inner wall a... | 09/18/2007 |
| 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 |
| 7254937 | Gas turbine heat exchanger assembly and method for fabricating same A method for assembling a gas turbine engine including a compressor and a combustor includes providing a heat exchanger assembly that includes at least one heat exchanger, and coupling the heat exchanger assembly to the gas turbine engine such that the heat exchange... | 08/14/2007 |
| 7231767 | Forced air cooling system A forced air cooling system for an APU comprising at least an oil cooler, a plenum in fluid communication with the oil cooler, and a compressor rotated by a rotating shaft of the APU such that the compressor and rotating shaft rotate at a same speed, the rotating co... | 06/19/2007 |
| 7216477 | Method and apparatus for a rocket engine power cycle A system for cooling a portion of a rocket engine with an inert compound and transferring the thermal energy from the inert compound to the propellants. The energy absorbed by the coolant is used also to power the turbines which powers the pumps that pump the fuel, ... | 05/15/2007 |
| 7213393 | Device for supplying cooling air to exhaust nozzle flaps A device for supplying cooling air to a hollow flap of an exhaust nozzle in a turbojet engine. The device includes a tube connecting the hollow flap to a cooling air source. The tube comprises at least one telescopic portion and at least one ball-joint connection. | 05/08/2007 |
| 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 |
| 7199318 | Air guidance device for cooling a switch part of an electrical switch An air guidance device is for cooling a switch part of an electrical switch. It includes at least one air guidance element arranged at a distance from the switch part to be cooled, forming at least one air duct which runs vertically when the switch is in the install... | 04/03/2007 |
| 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 |
| 7100360 | Pulsed combustion engine A pulsed combustion device includes a support structure and a combustor carousel supported by the support structure and rotating relative thereto about an axis. The carousel has a number of combustion conduits in a circumferential array. Each conduit cyclically rece... | 09/05/2006 |
