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4351150 |
Auxiliary air system for gas turbine engine
An auxiliary air system contained within the nacelle of a gas turbine engine having the functions of cooling engine components and measuring air inlet temperature. The system comprises an air...
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4312480 |
Radiation shielding and gas diffusion apparatus
A device for shielding a heated surface from infra-red detection through an opening adjacent to the heated surface. The device includes a gas-conducting member, which is adapted to receive heated...
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4279123 |
External gas turbine engine cooling for clearance control
An active clearance control (ACC) for a turbofan engine is disclosed herein where the cross section of the external spray bars are fabricated in square or substantially square configurations.
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4271666 |
Integral infrared radiation suppressor for a turbofan engine
Apparatus is disclosed for minimizing the infrared radiation emitted at the aft end of a bypass fan type turbine engine. Minimization is accomplished by ducting cool air from the secondary bypass...
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4226084 |
Ducted fan engine exhaust mixer
A turbofan engine has an exhaust arrangement for the bypassed air and turbine exhaust gases providing for mixing of the two before a common propulsion nozzle. The turbine exhaust gas is directed to...
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4203286 |
Cooling apparatus for an exhaust nozzle of a gas turbine engine
A cooling control system for a convergent-divergent gas turbine exhaust nozzle which permits automatic ducting of cooling air during the augmented mode of engine operation. The convergent flaps of...
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4187675 |
Compact air-to-air heat exchanger for jet engine application
A structurally compact air-to-air heat exchanger, for a gas turbine engine of the fan bypass type, that permits a lower percentage of cooling air, than is presently needed in the art, to cool...
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4161231 |
Metal cavitated sandwich structures
A jet pipe wall is made from a honeycomb sandwich structure in which the skin forming one side of the sandwich is cut into many small square sheet pieces so that when differential longitudinal...
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4136518 |
Infrared radiation suppressor for a gas turbine engine
An infrared radiation suppressor secured to the discharge end of a gas turbine engine has a series of movable vanes maintained in an open trailing edge configuration in which they form converging...
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4118930 |
Filter-cooler
A filter-cooler is provided for use with a rocket motor to cool and filter ighly aluminized hot gases from around 5800° F. to around 2000° F. The cooled and filtered gases are then usable, for...
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4110972 |
Seal means for a movable centerbody in a two dimensional nozzle
This invention relates to sealing means for a movable centerbody having collapsible panels located in the two-dimensional exhaust nozzle of a jet engine so that movement of the centerbody and...
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4098076 |
Cooling air management system for a two-dimensional aircraft engine exhaust nozzle
This invention relates to a cooling air management system for a movable centerbody having articulating panels located in the two-dimensional exhaust nozzle of a jet engine so that movement of the...
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4093157 |
Seal for variable plug two dimensional nozzle
This invention relates to a seal adapted to prevent leakage at the interface of a movable plug with articulated panels and the side wall of a two-dimensional nozzle for a gas turbine engine. The...
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4074523 |
Pressure actuated collapsible curtain liners for a gas turbine engine nozzle
A cooling control system for a convergent-divergent gas turbine exhaust nozzle which permits ducting of cooling air during the non-augmented mode of engine operation. A Curtain Liner is hinged at...
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4072008 |
Variable area bypass injector system
An augmented mixed flow gas turbine engine is provided with a variable area bypass injector system which varies the area through which the bypass stream is injected into the core stream and which...
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4071194 |
Means for cooling exhaust nozzle sidewalls
A cooling arrangement for a gas turbine exhaust nozzle is provided which ludes a plurality of heat shield panels slidably positioned on tracks mounted on the nozzle casing. The panels are spaced...
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4069663 |
Thrust reverser for by-pass gas turbine engine
A by-pass gas turbine engine capable of producing an unmixed exhaust stream which comprises a core of hot turbine exhaust gases surrounded by an annular layer of by-pass air, is combined with a...
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4064691 |
Cooling of fastener means for a removable flameholder
A flameholder apparatus for use in a gas turbine engine exhaust nozzle comprises at least one V-shaped gutter for holding a flame, with fasteners to mount the gutter to a nozzle support structure,...
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4019320 |
External gas turbine engine cooling for clearance control
A reduction of the opening of the clearance between the outer air seal secured to the case of a turbo-fan engine and the tip of the turbine buckets is obtained by selectively turning on and off or...
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4000612 |
Cooling system for a thrust vectoring gas turbine engine exhaust system
A thrust vectoring gas turbine engine exhaust nozzle is provided with a variable area flow path wherein cooling of the stationary flow path side walls is partially obtained by the film cooling...
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3981143 |
Infrared suppressor
Successful flight of high altitude military aircraft is dependant, in part, pon the ability of the aircraft to remain undetected during flight. However, the hot gas plume is a prime source of...
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3972475 |
Nozzle construction providing for thermal growth
An exhaust nozzle has main flaps with seals therebetween. Each flap and seal is constructed having inner and outer members which cooperate to form a liner for passing cooling air therethrough which...
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3970252 |
Cooled exhaust duct
An exhaust duct for a turbofan aircraft engine includes a bulbous inner cone which blocks direct sight of the turbine through the duct. Ram air from the fan is caught by scoops and conveyed from a...
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3913666 |
Heat resistant wall construction
A technique of constructing a heat resistive wall with uni-directional quills, such as fibers, wherein a heat resistant surface is formed by the ends of the quills. The structure is formed of a...
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3866417 |
GAS TURBINE ENGINE AUGMENTER LINER COOLANT FLOW CONTROL SYSTEM
A stabilizing and support system for an augmenter cooling liner of a gas turbine engine is shown to include flange means which divide a cooling plenum formed between the cooling liner and an...
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3842597 |
GAS TURBINE ENGINE WITH MEANS FOR REDUCING THE FORMATION AND EMISSION OF NITROGEN OXIDES
Means for reducing the formation and emission of nitrogen oxides in a gas turbine engine provide for bleeding and cooling a portion of the airflow pressurized by the compressor. The cooled...
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3793832 |
NUCLEAR ENGINE REACTOR ROCKET CORES
A nuclear rocket engine reactor core equipped with a series of coolant channels having hydraulic diameters that decrease in programmed proportion with increasing radial position from the core...
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3712062 |
COOLED AUGMENTOR LINER
A liner for a combustion zone, particularly the thrust augmentor of a jet engine which has longitudinally spaced circumferential corrugations and slot film cooling means at the radially inward...
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3710572 |
THRUST CHAMBER
A rocket engine thrust chamber comprising a combustion chamber having its fuel inlet-mixing section and thrust nozzle section formed of integrally interconnecting pyrolyzed graphite filaments so...
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3698185 |
METHOD FOR DISPERSING DISCRETE PARTICLES
A slurry of metal flakes and freon is carried in a pressure tank connected o a supply tank of pressurized gas and to a distribution manifold attached near the exhaust pipe of a vehicle. When the...
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3685294 |
HOT GAS PUMPS AND THRUSTERS
This is a hot gas dredger or pump in which compressed air is mixed with fuel and ignited in a combustor near the end of a tube into which hot gases from the ignited fuel and air are directed in a...
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3682100 |
NOSE-CONE COOLING OF SPACE VEHICLES
This invention relates to the nose-cone cooling of space vehicles including missiles and more particularly to missiles whose nose structures incorporate means for dissipating heat therefrom.
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3648461 |
SOLID PROPELLENT ROCKET MOTOR NOZZLE
A solid propellent motor comprised of a metal casing for containing the solid propellent charge, a thin wall nozzle formed of carbon or graphite fibers or filaments, disposed in a carbon or...
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3643429 |
GAS GENERATOR CONSTRUCTION
A gas generator construction particularly an auxiliary combustion chamber for a rocket engine of the main current type for the production of oxygen-rich propellant gases of relatively low...
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3534908 |
VARIABLE GEOMETRY NOZZLE
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3533467 |
TUBULAR HEAT EXCHANGE ASSEMBLY
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3533232 |
ORGANIC FUSIBLE SOLID FUEL BINDERS AND STABILIZERS
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3528250 |
BYPASS ENGINE WITH AFTERBURNING AND COMPRESSOR BLEED AIR HEAT EXCHANGER IN BYPASS DUCT
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3475906 |
HEAT EXCHANGER FOR AIRCRAFT AIR CONDITIONING SYSTEMS
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3440820 |
THERMAL PROTECTION SYSTEM FOR MISSILE COMPONENTS SUBJECTED TO EXCESSIVE PERIODS OF AERODYNAMIC HEATING
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3422623 |
JET ENGINES WITH COOLING MEANS
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3418810 |
Cooling means for rotatable jet nozzle, bearing and turbine blades
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3386243 |
Bypass valve for recuperative gas turbines
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3383862 |
Rocket thrust chamber
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3384346 |
Aerofoil shaped blade for a fluid flow machine such as a gas turbine engine
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3359724 |
Cooling means in combustors for gas turbine engines
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3358457 |
Engine cooling system
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3309026 |
Gas cooled rocket structures
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3300975 |
Protective apparatus for a rocket motor
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3299639 |
Turbofan engine
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