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7603843 |
Combustion chamber comprising a cooling unit and method for producing said combustion chamber
A combustion chamber for expelling a hot gas stream from a rocket engine includes a combustion chamber wall and a plurality of cooling channels arranged inside the combustion chamber wall and...
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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...
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7478525 |
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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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....
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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7037430 |
System and method for desalination of brackish water from an underground water supply
A system and method of desalinating brackish water from an inland, underground water supply is disclosed. The system includes a source of underground water, at least one distillation and/or...
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7017334 |
Compact fastening collar and stud for connecting walls of a nozzle liner and method associated therewith
A combination for connecting a hot sheet and a cold sheet of a nozzle liner in spaced relationship apart includes a stud having a main body wherein the stud is attached to the hot sheet and a...
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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...
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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...
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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...
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6779336 |
Cooled variable geometry exhaust nozzle
A variable geometry exhaust nozzle 10 for a turbine engine includes convergent and divergent flaps 12, 18 that circumscribe a gaspath 26 and define convergent and divergent nozzle sections ...
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6769242 |
Rocket engine
The invention is a coolant system for a rocket engine. The rocket engine includes an injector, a fuel supply, an oxidizer supply, a pump for feeding fuel from the fuel supply to the injector, a...
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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...
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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...
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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...
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6418709 |
Gas turbine engine liner
A liner for a gas turbine engine is provided that includes a first liner section and a second liner section. The first liner section includes a first flange having a first contact surface. The...
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6415595 |
Integrated thermal management and coolant system for an aircraft
A thermal management system avoids problems associated with the recirculation of fuel through a fuel tank on an aircraft in a system that includes a fuel reservoir ( 70 ), a pump ( 72 ) for pumping...
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6301877 |
Ejector extension cooling for exhaust nozzle
The cooling of the exhaust nozzle of a fan jet engine powering aircraft is enhanced by providing an extension cooling concept that includes an extension piece extending axially downstream of the...
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6295805 |
Exhaust induced ejector nozzle system and method
An exhaust induced ejector nozzle (20) includes a convergent portion (30) and a divergent portion (34) disposed downstream from the convergent portion (30). The ejector nozzle (20) also includes an...
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6282887 |
Bellows units for a chamber of a liquid-propellant rocket engine with afterburning
A device comprises a bellows with protective rings arranged between corrugations of the bellows. Support rings are connected in a sealed manner to a gas line and a combustion chamber. A gimbal ring...
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6182435 |
Thermal and energy management method and apparatus for an aircraft
The cooling of components (26) of a vehicle (10) carrying a turbine engine (12) and a fuel supply (24) for the engine (12) without the excessive consumption of bleed air is achieved in an apparatus...
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6164059 |
Multi-expansion ejector nozzle with diverging walls
The wall downstream of the slot of an ejector forms a divergent angle relative to the upstream wall adjacent to the slot so that the flow discharging from the slot expands and avoids having the...
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6149074 |
Device for cooling or heating a circular housing
The housing is heated or cooled to adjust its diameter and, in particular, the play between the tips of the rotor blades and the housing. The apparatus consists of networks of tubes (1) covering...
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6134880 |
Turbine engine with intercooler in bypass air passage
A turbine engine (20) having bypass and core passages (30 and 40), a high pressure compressor (80) for compressing air in the core passage and an intercooler (120, 220) for cooling core air (42) in...
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6122907 |
IR suppressor
An IR Suppressor (20) operative to suppress the infrared signature radiated from the high-temperature exhaust of an engine (12) and comprising a primary exhaust manifold (22), first and second...
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6102329 |
Flow diverter system for multiple streams for gas turbine engine
A flow diverting mechanism for the twin duct offtakes or coannular offtake for a turbo fan engine powering aircraft with either thrust reversing or short takeoff and vertical landing or both...
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6058696 |
Inlet and outlet module for a heat exchanger for a flowpath for working medium gases
An inlet-outlet module 108 having both an inlet 58 and an outlet 62 for a heat exchanger system 52 is disclosed. Various construction details which improve the stiffness to weight ratio and the...
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5832719 |
Rocket thrust chamber
A thrust chamber for an expander cycle rocket engine having a predetermined quantity of tubes concentric about an axis and radially inward of a structural jacket, each tube having first and second...
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5813221 |
Augmenter with integrated fueling and cooling
A turbofan engine augmenter includes an exhaust casing and a combustion liner therein which define therebetween a cooling duct for receiving bypass air. A diffusion liner adjoins the combustion...
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5778658 |
Recoup turbojet engine
A turbojet engine includes a compressor and turbine, with a combustor disposed therebetween for generating exhaust gas. An afterburner includes an annular casing and liner spaced radially inwardly...
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5775098 |
Bypass air valve for a gas turbine
A bypass air valve is provided comprising a liner, a strap, and apparatus for selectively actuating the valve. The liner includes an inner surface, an outer surface, a plurality of first regions,...
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5755093 |
Forced air cooled gas turbine exhaust liner
The exhaust in a gas turbine engine is lined with stacks of hollow cooling blocks made of a composite material. Air is pumped into each stack and escapes into the exhaust flow from a slot between...
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5680767 |
Regenerative combustor cooling in a gas turbine engine
A combustor, for a gas turbine engine, employing regenerative combustor cooling. The combustion gas flow direction extends generally longitudinally aft of the combustor fuel nozzle. A coolant...
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5680755 |
Convertible ejector selectively cooled thrust vectoring exhaust nozzle
A nozzle cooling system for selectively cooling longitudinally extending and circumferentially adjacent divergent exhaust flow confining elements bounding a hot exhaust gas flowpath in a divergent...
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5673551 |
Premixing chamber for operating an internal combustion engine, a combustion chamber of a gas turbine group or a firing system
In a premixing burner for the operation of an internal combustion engine, a combustion chamber of a gas turbine group or a firing system, which burner can be used for the combustion of fuels with...
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