Matches 101 - 150 out of 317 < 1 2 3 4 5 6 7 >
Match Document Document Title
6055804 Turning vane arrangement for IR suppressors  
A turning vane arrangement (30) for an IR suppressor having a duct (32) adapted for receiving a primary flow PF of engine exhaust. The turning vane arrangement (30) is operative to direct a...
6016651 Multi-stage mixer/ejector for suppressing infrared radiation  
A multi-stage mixer/ejector (20) having at least one exhaust nozzle (24 or 28) which includes inlet conduit adapted for receiving a primary flow PF of engine exhaust and a plurality of adjoined...
6003301 Exhaust nozzle for multi-tube detonative engines  
A nozzle for a detonative combustion engine, the engine having multiple combustor tubes, comprises a common plenum communicating with the combustor tubes. The common plenum combines separate...
5951246 Exhaust system for marine gas turbine  
An exhaust system for a marine gas turbine may suppress a reduction of an efficiency even if a space therefor is small. In the exhaust system for a marine gas turbine, in which an end portion of an...
5935459 Test device for impinging a sample with a high-energy gas jet  
A test device (1) serves for impinging a sample (2) with a high-energy gas jet (3). A plasma torch (4, 5) provides the gas jet (3) heated by a plasma and directed towards the sample (2). A massive...
5934564 Variable geometry turbojet engine exhaust nozzle  
A variable geometry exhaust nozzle is disclosed for a turbojet engine having a rear portion, the nozzle having an outer flap ring with a plurality of driven outer flaps and a plurality of outer...
5894723 Rocket engine nozzle with ejectable inserts  
The diverging part of the nozzle comprises an outer diverging part and at least one inner diverging part of outlet section that is smaller than that of the outer diverging part and designed to be...
5884472 Alternating lobed mixer/ejector concept suppressor  
A mixer/ejector suppressor is disclosed for reducing the noise level created by the exhaust flows in gas turbines. In the preferred embodiment, the suppressor comprises a mixing ring of alternating...
5853904 High temperature articles  
A high temperature article, for example a rocket nozzle suitable for liquid-fuelled rocket motors for satellites, is formed from an alloy which is a binary or tertiary alloy from the Pt-Ir-Rh...
5826794 Aircraft scoop ejector nozzle  
An engine exhaust nozzle (36) is provided for reducing exhaust noise in an intermediate bypass ratio turbofan engine. The nozzle (36) includes a plurality of scoop ejectors (38) placed equal...
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...
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...
5746047 Infrared suppressor  
An infrared suppressor system for a gas turbine engine is provided for suppressing infrared radiation associated with the hot metal parts of the engine and with the hot exhaust gases exhausted from...
5722233 Turbofan engine exhaust mixing area modification for improved engine efficiency and noise reduction  
A modified exhaust tailpipe especially for use with an aircraft turbofan engine utilizing a noise suppressor. The modified tailpipe is connected to the exhaust duct of the engine. The forward end...
5699662 Infrared suppression exhaust duct system for a turboprop propulsion system for an aircraft  
The invention is an exhaust duct system for an aircraft, the aircraft having at least one turboprop propulsion system mounted on the wing within a nacelle, the propulsion system having a circular...
5690279 Thermal relief slot in sheet metal  
A thermal relief slot is formed by including a lateral slot in each of three overlying sheet metal sheets with the upper and lower slots being in overlying position and the middle slot being...
5664415 After-burning turbo-fan engine with a fixed geometry exhaust nozzle having a variable flow coefficient  
An after-burning turbo-fan engine system (10) includes turbo-fan engine (14) for producing exhaust gas (20), and jet thrust therefrom. After-burning chamber (16) receives turbo-fan exhaust and...
5592814 Attaching brittle composite structures in gas turbine engines for resiliently accommodating thermal expansion  
Two composite parts, such as sheet and a hollow gas turbine liner tile, are fastened together using a fastening system that includes a journal bearing that fits in a bore in the sheet and springs...
5584173 Nozzle seal assembly with removable baseplate  
A thermal shield and support structure assembly for a gas turbine engine is disclosed wherein the thermal shield can be removed while the support structure is still mounted in the engine. The...
5579635 Distributed erosion region rocket motor nozzle  
A rocket motor nozzle has a nozzle core that defines a nozzle passage through which combustion products travel during flight. The erosive forces created by the combustion products are...
5579999 Shock-free supersonic elliptic nozzles and method of forming same  
A method of forming a shock-free supersonic elliptic nozzle, in which the nozzle to be designed is divided into three sections, a circular-to-elliptic section which begins at a circular nozzle...
5571262 Supersonic nozzle for a turbojet engine  
Disclosed is a variable supersonic nozzle for a turbojet engine having an improved control system for varying the convergent and divergent nozzle flaps. All of the flaps are supported on several...
5524827 Method and nozzle for producing thrust  
A method and apparatus for producing a thrust force from an annular axial stream of gaseous products fed to a nozzle with a supercritical pressure drop and acceleration to subsonic speed. In the...
5484105 Cooling system for a divergent section of a nozzle  
A nozzle cooling system having apparatus to overexpand the exhaust flow in a divergent section of an aircraft gas turbine engine nozzle, relative to the air in the engine nozzle's bay and a valve...
5461856 Divergent slave petal for sealing in variable geometry exhaust nozzles for gas turbine propulsion units  
A divergent slave petal for sealing in variable geometry exhaust nozzles for gas turbine propulsion units includes a base plate for bearing axial forces but having minimum capacity for transmitting...
5450720 Rocket engine nozzle having a notched diverging portion  
In a rocket engine nozzle comprising: a converging portion that receives the gases produced in a combustion chamber; a throat of small section; and a diverging portion connected to the nozzle...
5437412 Variable geometry jet engine exhaust nozzle  
A variable cross-section nozzle for a jet engine is disclosed having main inner (hot) flaps defining an inner nozzle and main outer (cold) flaps defining an outer nozzle with adjacent main flaps...
5419120 Device for purging combustion residues  
The present invention relates to a device for purging combustion residues from a thruster that comprises firstly a combustion chamber designed to receive a solid propellent and secondly a nozzle...
5402964 Interference with vortex formation and control of fluid flow to reduce noise and change flow stability  
Apparatus for the interference and manipulation of vortex formation and control of fluid flow to reduce noise and increase flow stability is provided. A specific embodiment is directed to a...
5398500 Convergent divergent jet engine nozzle  
A thrusting nozzle (24) comprises an annular shell (34) and an inner body (30). The contours of the inner wall (42) of the shell (34) and the outer wall (44) of the inner body (30) form a...
5394690 Constant pressure, variable thrust bipropellant engine  
A pressure controlled pintle is employed in combination with a throttling quid, gel, or hybrid engine to provide a constant pressure and variable thrust from a single operating engine. As the...
5388765 Gas turbine nozzle construction  
A planar top plate (32) has film cooling slots (34) therein. A rigid honeycomb structure (38) sealingly joins this top plate with bottom plate (36). Cooling air distributed by openings (50)...
5363645 Enclosure containing hot gases cooled by transpiration, in particular the thrust chamber of a rocket engine  
An enclosure containing hot gases cooled by transpiration includes means for applying a cooling fluid, said means comprising a hydraulic calibration sheath applied on the outside face of a porous...
5359850 Self venting carbon or graphite phenolic ablatives  
Self venting ablative carbon or graphite composite materials are prepared by interspersing low temperature degradable thread within the woven carbon or graphite cloth prior to impregnation with a...
5343698 Hexagonal cluster nozzle for a rocket engine  
A rocket engine thrust nozzle assembly is disclosed wherein combustion products from a plurality of rocket engines having hexagonally-shaped exhaust areas flow to the inlet of a main nozzle that...
5339626 Inflatable engine protection system for recoverable rocket booster  
A rocket engine protection system for a recoverable rocket booster which is arranged to land in a salt water body for recovery. The system includes an inflatable water impermeable elastomeric...
5329762 Method for assembling rocket propulsion motor  
A method for assembling a rocket propulsion motor including a motor case and a nozzle assembly, wherein the assembling is carried out under vacuum so that air can not be presented between a silicon...
5309712 Solid fuel rocket motor seals  
A rocket motor has a reloadable, reusable hollow casing which contains solid fuel, a nozzle and preferably a delay ignition cartridge and ejection charge. A nozzle gasket holds the nozzle in place...
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...
5269139 Jet engine with noise suppressing mixing and exhaust sections  
The present invention relates to a jet engine, where there is an outer housing, an engine, a mixing section, and an exhaust section. Ambient air is drawn into the mixing section. The gaseous...
5251436 Thrust-reducing, chaotic-flow nozzle  
A nozzle assembly for a rocket type decoy used to protect aircraft from missile attack. The nozzle assembly includes an annular chamber and a mixing chamber which is spaced radially inward from the...
5239823 Multiple layer cooled nozzle liner  
The present invention is a multiple layered nozzle liner for two-dimensional nozzles which provides both convective and film cooling, and incorporates a highly maintainable thermal barrier coating.
5233827 Radiation supression  
An arrangement to mask direct view of the discharge end of a turbine through an exhaust duct extending downstream from the turbine. The turbine has an annular outlet. Two annular rows of fixed...
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...
5167118 Jet engine fixed plug noise suppressor  
A noise suppressor for use with a turbofan engine, the suppressor being formed of a tubular exhaust shroud affixed to the engine exhaust end, the shroud providing an internal circumferential...
5165229 Thruster sealing system and apparatus  
A thruster nozzle sealing system and apparatus is provided for protection of spacecraft thruster motors. The system includes a sealing plug, a sealing plug insertion tool, an outer cover, an outer...
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...
5080284 Cooling system for the trailing edge of a liner  
Disclosed is a device for cooling the trailing edge segment of a liner on a convergent flap of a nozzle on a gas turbine engine. The trailing edge cooling device enhances the cooling of the liner...
5067324 Engine nozzle liner retainer  
A nozzle liner (14) is secured to a nozzle support structure (10) with interlocking clips (24, 26). After moving the liner axially into engagement cantilever spring (32) abuts a clip (24) which...
5060550 Rocket nozzle snubber  
Stress from the ignition of a rocket is transferred from the rocket nozzle o the actuators and flexible joint seal which move the nozzle causing potential failure of the actuators. This stress can...
Matches 101 - 150 out of 317 < 1 2 3 4 5 6 7 >