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5996336 |
Jet engine having radial turbine blades and flow-directing turbine manifolds
A jet aircraft engine having an improved turbine section with curved intake manifolds to direct combustion gasses from the engine's combustion chamber into the turbine housing on a chordal flow...
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5947412 |
Jet engine noise suppressor assembly
The present invention relates to a noise supressor assembly for a jet engine comprised of a plurality of conduit assemblies proximate the trailing edges of the wall members which capture a portion...
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5941061 |
Aircraft propulsive power unit assembly having a leading edge lipskin and intake barrel
An aircraft propulsive power unit comprises an engine, a nacelle structure which houses the engine and which includes displaceable nacelle portions which form a forward part of the nacelle...
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5924632 |
Jet nozzle having centerbody for enhanced exit area mixing
A nozzle arrangement includes a nozzle and a centerbody. The longitudinal axis of the centerbody is coaxially aligned with the nozzle. The centerbody has a free end portion shaped to create...
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5906097 |
Engine flow control device
A fencing assembly (66) for prohibiting circulation of primary and/or fan airflows (52), (54) into a bounded low pressure region of a jet engine installation. The fencing assembly includes one or...
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5894721 |
Noise reducing stator assembly for a gas turbine engine
A stator assembly for reducing noise in the outermost portion of the working medium flow path is disclosed. Various construction details are developed which relate to the reduction in noise within...
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5887822 |
Segmented engine flow control device
In a turbofan jet engine installation including a low pressure area (48) located between a primary exhaust nozzle (20) and strut fairings (30), an improvement including a fencing assembly (66) for...
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5867979 |
Gas turbine engine system
An aircraft mounted gas turbine engine system comprises a three shaft propulsive gas turbine engine having three electrical generators; each one respectively associated with one shaft of the...
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5867980 |
Turbofan engine with a low pressure turbine driven supercharger in a bypass duct operated by a fuel rich combustor and an afterburner
A multiple bypass turbofan engine includes a core Brayton Cycle gas generator with a fuel rich burning combustor and is provided with a variable supercharged bypass duct around the gas generator...
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5860275 |
Method of combining ducted fan gas turbine engine modules and aircraft structure
In a ducted fan gas turbine engine the fan module is connected rigidly to aircraft structure and flexibly to the core gas generator via flanged annular diaphragms (62,66) thus obviating the...
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5822975 |
Bypass engine with means for limiting gas leakage
A bypass engine including a fan which has its blades disposed in both the imary gas flow path and the secondary gas flow path of the engine is provided with an annular intermediate gas flow path in...
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5809772 |
Turbofan engine with a core driven supercharged bypass duct
A multiple bypass turbofan engine including a core engine assembly has a fan bypass duct radially outward of the core engine assembly and has first and second inlets disposed between forward and...
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5806303 |
Turbofan engine with a core driven supercharged bypass duct and fixed geometry nozzle
A multiple bypass turbofan engine including a core engine assembly has a fan bypass duct radially outward of the core engine assembly and has first and second inlets disposed between forward and...
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5806302 |
Variable fan exhaust area nozzle for aircraft gas turbine engine with thrust reverser
A structure to provide a variable nozzle for the fan air flow of a turbofan aircraft gas turbine engine with the nozzle being defined by the exit throat area defined by the aft edge of a trailing...
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5794432 |
Variable pressure and variable air flow turbofan engines
A variable cycle gas turbine engine has, in axial flow serial relationship, a fan assembly, a core engine, and an exhaust assembly. The core engine includes a compressor, a combustor, a high...
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5782077 |
Device for bleeding off and cooling hot air in an aircraft engine
The present invention relates to a device for bleeding off and cooling hot air in an aircraft engine, including: at least one hot air take-off at the outlet of the compressors of the engine, ...
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5782082 |
Aircraft engine acoustic liner
A middle layer (22) having partitioned cavities (28) is sandwiched between an imperforate sheet (24) and an optional perforate sheet (26) to form a low resistance acoustic liner (22). A preferred...
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5778659 |
Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems
A gas turbine engine (10) includes a translating sleeve (38) disposed within a downstream portion of an outer nacelle (20). A variable area fan exhaust nozzle (30) is defined between the trailing...
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5771681 |
Aircraft turbofan engine mixing apparatus
A fluid mixing apparatus for mixing primary exhaust and secondary airflow in a turbofan engine with provision for changing the ratio of secondary airflow to primary exhaust cross-sectional areas in...
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5771680 |
Stiffened composite structures and method of making thereof
A stiffened composite is provided exhibiting multi-directional reinforcement with continuous long fibers. The composite has a substrate and serpentine stiffeners adhered thereto. The stiffeners...
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5758488 |
Core flow expansion chamber device system for reduction of jet turbine engine noise
A noise reduction system is provided for installation on a bypass turbine having a core engine, an outer casing and a thrust reverser. The system is comprised of an acoustically treated nose cowl...
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5740674 |
Arrangement of gas turbine engine comprising aerodynamic vanes and struts located in the same plane and an intermediate casing
The arrangement of a gas turbine engine suitable for high bypass ratio aircraft engines in which gases circulate in a primary air channel (7) and a secondary channel (8) concentric to said primary...
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5737914 |
Device for fixing an air intake to a jet engine and jet engine incorporating such a device
Device for fixing an air intake to a jet engine and jet engine incorporating such a device. This device for fixing an air intake (24) to a jet engine (10) installed on a support strut (12) and...
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5732547 |
Jet engine fan noise reduction system utilizing electro pneumatic transducers
A jet engine fan noise reduction system. The noise reduction system includes active noise control to suppress fan tone noise of an airplane flyover noise signature. The active noise control...
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5706648 |
Sealing device between an air inlet and a fan frame of a turbofan engine
In a turbofan engine, particularly of the type in which the front end of the fan frame (26) is separate from the air inlet (24), the seal between the said two structures is provided by an elastic...
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5706649 |
Multi axis thrust vectoring for turbo fan engines
The present invention is a thrust reversing apparatus for diverting purely rearwardly directed air flowing through an engine nacelle to combined rearward-and-radially-outward flow, and then to a...
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5702231 |
Apparatus and method for reducing noise emissions from a gas turbine engine inlet
Noise attenuating linings for a turbofan engine inlet are installed around the upper crown area and/or around the lower lip. The acoustical lining at the upper crown area attenuates those fan noise...
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5692372 |
Aircraft compound cycle propulsion engine
A ducted fan aircraft compound cycle engine comprises a core engine which includes a compressor, three rotary internal combustion engines fed by the compressor and a power turbine to receive the...
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5680754 |
Compressor splitter for use with a forward variable area bypass injector
The present invention is a unique splitter of a core engine compressor in a double bypass, variable cycle engine. The splitter is extended forward to a second fan section. The extended splitter may...
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5649419 |
Rotating acoustically lined inlet splitter for a turbo-fan engine
A noise controlling device (12) is used for controlling noise in a turbo-fan engine (10). The engine includes an entrance (22) for ingesting air, and a fan rotor (18) connected to a spinner (20) in...
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5642615 |
Turbofan engine with a floating pod
In a turbofan engine, the mechanical connection between the pod (12) and the fan stator case (10) is limited to a centering system (22) in the immediate vicinity of the arms (20) by which the fan...
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5603471 |
Ducted fan turbine engine nozzle assembly
A ducted fan turbine engine includes a nacelle and an outer discharge nozzle mounted on an aircraft wing by a pylon. The nacelle includes to parts which are hinged to the pylon for pivoting...
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5592813 |
Hush kit for jet engine
A hush kit for jet aircraft engine includes a respaced inlet guide vane to provide an increased space between the fixed guide vanes of the inlet and the rotating fan blades of the fan connected to...
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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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5485717 |
Multi-spool by-pass turbofan engine
A multi-spool turbofan engine has a high pressure spool that operates at high idle RPM so as to power accessories and minimize acceleration time from idle to full rated RPM without producing high...
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5485723 |
Variable thickness isogrid case
A light weight isogrid containment structure has minor concessions to weight in order to achieve efficient manufacture oversize flanges are permitted in skin thickness interface zones so that...
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5440875 |
Fixed geometry mixer/ejector suppression system for turbofan aircraft engines
An internal flow mixer is attached to the rearward end of a turbofan engine for inverting the engine fan and core streams. Rearwardly of the internal flow mixer is a multi-lobed exhaust nozzle...
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5408826 |
Gas turbine engine casing construction
A casing assembly for a ducted fan gas turbine engine comprises a casing around which extend two annular, axially spaced apart, frangible rails. Pieces of cloth woven from an aromatic polyamide...
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5402963 |
Acoustically shielded exhaust system for high thrust jet engines
A flade exhaust nozzle for a high thrust jet engine is configured to form an acoustic shield around the core engine exhaust flowstream while supplementing engine thrust during all flight...
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5388964 |
Hybrid rotor blade
A hybrid gas turbine engine rotor blade includes an airfoil and a dovetail integrally joined thereto. The airfoil includes an inner portion disposed adjacent to the dovetail to provide a structural...
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5369954 |
Turbofan engine bypass and exhaust system
A turbofan engine bypass and exhaust system has a double-hoop configuration in which a fan exhaust passageway comprises shells of a constant circular contour to resolve air pressure induced...
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5363641 |
Integrated auxiliary power system
A method for providing both starting power and thermal management requirements of a vehicle incorporating a gas turbine engine by using the same unit to alternately provide both starting power and...
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5361580 |
Gas turbine engine rotor support system
A gas turbine engine rotor support system includes outer and inner rotors having respective outer and inner blades interdigitated in respective blade row stages. A stationary rear frame includes a...
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5349814 |
Air-start assembly and method
A method and assembly are effective for air-starting an aircraft gas turbine engine having a fan powered by a low pressure turbine through a first shaft, and a compressor powered by a high pressure...
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5345760 |
Turboprop booster
A booster-compressor for a high flow coefficient turboprop aircraft engine increases engine thrust by supercharging the air into the inlet of the gas generating core engine. The flow of...
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5320305 |
Propulsion system for an aircraft providing V/STOL capability
The invention is a propulsion system for powering an aircraft in both vertical and horizontal flight modes. In detail, the invention includes a pair of ducted lift fans mounted in the aircraft for...
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5319927 |
Ducted fan gas turbine engine
A ducted fan gas turbine engine has a fan duct across which extends an aerodynamically configured fairing. The fairing has a leading edge region which is defined by a pair of doors. The doors pivot...
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5315821 |
Aircraft bypass turbofan engine thrust reverser
An aircraft bypass turbofan engine subassembly for ground deceleration (e.g., thrust reversal). A fan nacelle has a through passageway connecting its inner exterior surface and outer exterior...
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5315820 |
Composite structural component
Fatigue, the phenomenon of structural or system failure, caused by repeated excitations from high frequency noise or vibration levels, can occur without warning in inlet cowls, fan ducts and thrust...
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