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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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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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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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6935098 |
Turbomachine nozzle with noise reduction
A nozzle comprising an inner barrel, a centerbody disposed inside the inner barrel so as to define a first channel for a primary flow, and an outer barrel surrounding the inner barrel so as to...
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6804947 |
Device for cooling the common nozzle of a turbojet pod
The invention relates to a dual flow turbojet comprising an engine of axis X housed completely inside a tubular pod whose inside wall co-operates with the case of said engine to define an annular...
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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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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...
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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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6606854 |
Exhaust mixer and apparatus using same
Disclosed is an exhaust mixer ( 50 ) including a passage ( 54 ) extending from an inlet ( 56 ) to an outlet ( 58 ) that is coincident with a centerline axis of mixer ( 50 ). Several ridges ( 68 )...
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6606851 |
Transpiration cooling of rocket engines
A rocket engine having a combustion chamber with a chamber inner wall, a throat with a throat inner wall, and a nozzle with a nozzle inner wall is provided. The chamber inner wall is a vacuum...
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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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6347510 |
Axi-nozzle ejector seal
A nozzle for a gas turbine engine is provided which includes an outer casing, a convergent section, a divergent section, an external fairing, and a collapsible seal member. The divergent section...
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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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6182442 |
Combustion chamber wall construction for high power engines and thrust nozzles
A wall construction for a combustion chamber or thrust nozzle of a high power engine of a flying body includes an inner wall body that is subjected to the hot gases within the combustion chamber,...
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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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6134879 |
Suppression system for a gas turbine engine
A suppression system for a gas turbine engine uses a tapered exhaust manifold with a plurality of exhaust nozzles acting in conjunction with a plurality of mixing cells to produce cooling of an...
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5813609 |
Hinged lined exhaust nozzle
An exhaust nozzle includes circumferentially adjoining primary flaps and seals hinged at forward ends to an annular casing. The primary flaps and seals are actuated between open and closed...
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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...
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5794851 |
Nozzle sealing apparatus
A nozzle for a gas turbine engine is provided which includes an outer casing, a convergent section, a divergent section, an external fairing, and apparatus for sealing between the external fairing...
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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...
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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...
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5732883 |
Combustion enclosure with cooling by transpiration
The invention relates to an enclosure containing hot gases cooled by transpiration, the enclosure comprising a porous wall and means for applying a cooling fluid to the outside face of said porous...
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5699965 |
Infrared suppressor for a gas turbine engine
An IR suppressor produces a thin "ribbon" exhaust plume using a tapered exhaust manifold which has a plurality of discrete exhaust nozzles that are longitudinally aligned with the exhaust manifold....
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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...
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5655361 |
Sound absorbing apparatus for a supersonic jet propelling engine
To reduce a noise and to cool a nozzle in a supersonic jet propelling engine, a sound absorbing member made of a porous plate (4) and a honeycomb structure (2) or a porous plate (4) and a torus...
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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...
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5586431 |
Aircraft nacelle ventilation and engine exhaust nozzle cooling
This disclosure relates to a system for purging of the nacelle of an aircraft and for cooling the edge pieces of the divergent flap of a gas turbine engine's two-dimensional exhaust system by use...
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5577381 |
Exhaust nozzle cooling scheme for gas turbine engine
Cooling of the hot surfaces of the exhaust nozzle of a fan jet engine and purging of the nacelle is attained by a booster pump mounted in exhaust nozzle structure and the booster pump having an...
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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...
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5407133 |
Cooled thin metal liner
A first metal sheet (34) has openings (46) in registration with depressions (40) in a second contacting metal sheet (36). Each depression has a downstream wall (42) at an angle of 24° from the...
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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)...
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5364029 |
Axisymmetric convergent/divergent nozzle with external flaps
The gas turbine engine nozzle has fifteen divergent flaps (18) secured to fifteen convergent flaps (14). Five external flaps (30), are each of a "V" shape, and surround the divergent flaps. The...
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5351888 |
Multi-axis vectorable exhaust nozzle
A convergent-divergent exhaust nozzle is mounted to an exhaust duct of a jet aircraft engine by a circumferentially-spaced set of hydraulic cylinders. The cylinders are interconnected in captured...
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5292069 |
Convertible plug nozzle
A plug nozzle is convertible to and from an open nozzle by moving several components. The convergent flap moves between an outboard convergent flap position and a central plug position. Divergent...
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5288020 |
Seal arrangement for adjoining walls of a propulsion nozzle of an engine
Apparatus for sealing the side edges of flaps of a propulsion nozzle of an engine and the walls of a casing of the nozzle by sealing elements carried by the flaps and extending across a clearance...
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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...
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5255849 |
Cooling air transfer apparatus for aircraft gas turbine engine exhaust nozzles
A cooling air transferring apparatus is provided particularly for transferring cooling air from hollow convergent flaps and seals to hollow divergent flaps and seals respectively in aircraft gas...
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5249419 |
Nozzle liner for gas turbine engines
The improved liner comprises a base plate that mounts to the wall of the nozzle, at least one inner tube having a plurality of leg supports thereon for mounting to the base plate, a cylindrical...
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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...
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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...
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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...
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5144795 |
Fluid cooled hot duct liner structure
Liner structure for a duct carrying a heated fluid is described which comprises a substantially cylindrically shaped wall member having a corrugated inner surface contour defining a first plurality...
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5143292 |
Cooled leaf seal
A seal assembly includes a housing having a plenum, a leaf seal rotatably joined to the housing to define a hinge. The leaf seal includes flow channels which receive a cooling fluid from the plenum...
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5141154 |
Variable throat convergent/divergent nozzle
Each convergent flap and seal has a cantilevered extension deflector. This deflector reduces the throat area at minimum throat area, and seals against a divergent flap or seal in the maximum throat...
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5115979 |
Conforming plunger seal assembly
A seal assembly is provided between an exhaust flap and a nozzle sidewall of a gas turbine engine exhaust nozzle. The assembly includes a housing fixedly joined to the exhaust flap and a plurality...
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