Matches 1 - 50 out of 118 1 2 3 >
Match Document Document Title
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...
7481248 Flexible heat shields and method  
A heat shield comprises a flexible inner jacket configured and disposed to be fitted around at least a portion of a component, and a flexible outer jacket configured and disposed to be fitted...
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...
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...
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...
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....
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
6098402 Infra-red stealth masking device (IRSMD)  
An Infra-Red suppression device composed of systems designed to alter the infra-red spectrum bands produced by the exhaust plume and airframe friction in order to render infra-red seekers, both...
5802842 Dimensionally stable throat insert for rocket thrusters  
In accordance with the teachings of the present invention, there is disclosed a thruster rocket engine throat insert (12) having a thin walled shell (54) made from a high strength, oxidation...
5799874 Aerodynamically controlled ejector  
The supersonic ejector utilized for cooling includes a cooling extension axially extending the discharge slot from the throat of the primary stream and is contoured to accelerate primary stream, to...
5794850 Enclosed pressure balanced sync ring nozzle  
The C/D axisymmetrical exhaust nozzle for a gas turbine engine is designed to fit on the engine and STOVL aircraft and includes an hydraulic actuator and a combined load balancing piston/sync ring...
5775589 Cooling apparatus for aircraft gas turbine engine exhaust nozzles  
The present invention provides coolable exhaust nozzle flap and seal assemblies having liners that are spaced inward and apart from their respective flap and seal cool walls, to form a cooling...
5593112 Nacelle air pump for vector nozzles for aircraft  
The nacelle of the aircraft is purged and the sidewall of the vector nozzles of the gas turbine engine in the nacelle is cooled by utilizing the engine fan air to drive ejector pumps mounted in...
5348252 Vectorable nozzle mounting  
A vectorable nozzle mounting for an engine installation in a VSTOL aircraft in which hot gas nozzles are mounted on the airframe is described. A swivelable nozzle is mounted by means of a bearing...
5269132 Method and apparatus for controlling infrared emissions  
There is described a method and apparatus for reducing the infrared emissions from a tail-pipe section of a jet engine. The apparatus consists of a plurality of overlapping hollow panels each...
5226598 Nozzle wall  
A nozzle wall for two-dimensional (2D) hot gas nozzles of rocket or jet engines has a multilayer structure, in which a thermally conductive layer is flexibly connected to a support structure and a...
5221045 Bulge formed cooling channels with a variable lead helix on a hollow body of revolution  
A method of constructing a nozzle having cooling channels comprises a shell and a liner which are formed into a body of revolution having an axis of revolution. Helical welds are formed to hold the...
5209059 Active cooling apparatus for afterburners  
The present invention comprises at least one active cooling apparatus incorporated into the nozzle liner of sidewall of an afterburner. The liner has a plurality of cooling air holes located under...
5188292 Thermal shields for rotating members in a gas flow path  
In a gas turbine engine, in a wall aperture of a 2-D variable area gas turbine exhaust nozzle, at least two members are rotatably and concentrically mounted in such aperture, substantially flush...
5165227 Propelling nozzle for a hypersonic engine  
A nozzle for a hypersonic engine includes an axially displaceable mushroom-shaped central body. Two mutually opposing expansion flaps are provided which, when the flying Mach number is low, can be...
5154352 Propelling nozzle for an aircraft engine  
A propelling nozzle for an aircraft engine has an interior shroud of high thermal conductivity which is penetrated by a number of cooling ducts and is surrounded from the outside by a solid support...
5101624 Exhaust nozzle hinge  
A hinge for pivotably connecting upstream and downstream wall sections of an exhaust nozzle of a gas turbine engine. Each wall section includes a liner spaced from the interior surface of the wall...
5079912 Convergent side disk cooling system for a two-dimensional nozzle  
Disclosed is an apparatus and a method for cooling a rotatable convergent side disk in a two-dimensional nozzle for a gas turbine engine, in which coolant is supplied and exhausted through...
5078412 Separately loaded strip seal  
Disclosed is a continuous fluid pressure seal for use between two members that move relative to each other, that can withstand high temperatures, and that is separately loaded so as not to rely...
5076590 High temperature, flexible pressure-actuated, brush seal  
A high temperature, flexible brush seal comprises a bundle of fibers or bristles held tightly together and secured at one end with a backing plate. The assembly includes a secondary spring-clip...
5048289 Extendible nozzle  
A thrust nozzle assembly for selective deployment and retraction of an extendible nozzle for a rocket engine.
5016818 Integral transition and convergent section exhaust nozzle  
A lightweight multifunction exhaust nozzle is designed with a specially contoured short length transition casing and a correspondingly contoured pair of convergent flaps. The change in flowpath...
4955541 Two dimensional nozzle for a turbojet engine  
The two-dimensional adjustable nozzle according to the invention is a generally rectangularly shaped nozzle having a pair of opposite, fixed sidewalls defining the lateral boundaries of the nozzle...
4934600 Exhaust nozzle thermal distortion control device  
A variable area, two-dimensional nozzle for exhausting a hot stream of combustion gases from a jet engine comprising upper and lower movable exhaust flaps disposed between stationary sidewalls for...
4909032 Combustor of high pressure burner for rocket engine and method of fabrication thereof  
An inner tube tube an outer surface of which is machined to define regerative coolant grooves for flowing a coolant to cool a combustor is split at a throat into upper and lower portions which in...
Matches 1 - 50 out of 118 1 2 3 >