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6786037 |
Segmented mixing device having chevrons for exhaust noise reduction in jet engines
Disclosed is a segmented mixing device for reducing jet engine exhaust noise wherein mixing is enhanced between adjacent exhaust flows and between exhaust flow and free-stream flow. The device does...
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6766638 |
Hydrogen peroxide based propulsion system
A micro air vehicle is propelled by a bipropellant micro engine supplied with hydrogen peroxide and a hydrocarbon fuel. The hydrogen peroxide is decomposed to produce steam and oxygen at high...
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6766639 |
Acoustic-structural LPC splitter
An acoustic-structural LPC splitter assembly which comprises a structural acoustic splitter through which are arranged a plurality of bleed exhaust ports, the acoustic splitter having a first and...
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6718752 |
Deployable segmented exhaust nozzle for a jet engine
An exhaust flow nozzle for a jet engine having a plurality of flow altering components extending from a lip portion of a secondary exhaust nozzle that are movable between first and second...
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6705547 |
Active noise reducing nozzle
A nozzle where the sector into which noise reduction is sought (the direction of populated areas) has a moving lip, driven by actuators in an oscillatory, periodic or sinusoidal motion, around the...
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6640537 |
Aero-engine exhaust jet noise reduction assembly
A gas turbine engine of a fan bypass type includes an exhaust shroud having a perforated tubular wall extending between a forward end and an aft end. The exhaust shroud is adapted to be affixed to...
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6615576 |
Tortuous path quiet exhaust eductor system
A tortuous path quiet exhaust eductor system may be mounted to a gas turbine engine, such as commercial aircraft APU. The system includes an oil cooler, eductor primary nozzle, oil cooler air...
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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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6578355 |
Bloom mixer for a turbofan engine
The invention relates to lobe-type mixer tube for a bypass jet engine in which a bypass flow delivered by a fan is mixed with a hot gas stream issuing from the core engine, said lobe-type mixer...
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6574965 |
Rotor tip bleed in gas turbine engines
A gas turbine engine includes a compressor, a combustor, and turbine enclosed in an engine case with the compressor having a plurality of alternating rows of rotating blades and stationary vanes....
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6571549 |
Jet noise suppressor
A jet noise suppressor is disclosed. The jet noise suppressor includes first and second high frequency pulse injection units located exteriorly of the turbine engine exhaust nozzle. The pulse...
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6532731 |
Turbofan engine having central bypass duct and peripheral core engine
A turbofan engine has a fan bypass duct which is at the center of the engine surrounding the fan and compressor drive shafts and an annular drive engine which is located at the outer periphery of...
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6516606 |
Aeroengine nacelle afterbodies
The invention discloses an aeroengine nacelle afterbody of the type comprising a common nozzle for exhausting the mixed hot and cold gases originating respectively from the fan duct and from the...
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6487848 |
Gas turbine engine jet noise suppressor
The present invention relates to a gas turbine engine jet noise suppressor which does not appreciably adversely impact engine thrust and performance. The jet noise suppressor includes a nozzle,...
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6415598 |
Exhaust nozzle for by-pass gas turbine engines
A by-pass gas turbine engine including a primary and a secondary nozzle which are substantially convergent, wherein the primary nozzle is situated radially within, but axially protruding from, the...
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6360528 |
Chevron exhaust nozzle for a gas turbine engine
A gas turbine engine exhaust nozzle includes an exhaust duct for channeling a gas jet. A plurality of adjoining chevrons are disposed at an aft end of the duct to define an exhaust outlet. Each of...
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6351940 |
Inverter ducting for dual fan concept
Accordingly, the present invention provides a ducting system for use on a gas turbine engine having two fans connected to a common shaft, and includes a primary inlet duct that is integral with a...
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6308740 |
Method and system of pulsed or unsteady ejector
The present invention reveals a method and apparatus for more efficiently injecting a primary fluid flow in a fluid ejector used to pump lower velocity fluid from a secondary source. In one...
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6276127 |
Noise suppressing mixer for jet engines
The mixer has a circular forward end which is attached to the exit of a jet engine, or the core of a bypass engine. The mixer has radial lobes which increase in their radial dimension with...
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6260800 |
Aircraft power plant with two air intake fans
An aircraft power plant for vertical take-off and landing comprises a jet propulsion unit having an air inlet and an exhaust outlet and incorporating a combustion chamber, a high pressure...
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6260352 |
Turbofan aircraft engine
A turbofan aircraft engine has a core engine, which is arranged in a gondola, and a fan which delivers a cold air current through a bypass flow duct to a mixer within which a low-pressure turbine...
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6253540 |
Removable baffle 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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6227800 |
Bay cooled turbine casing
A turbine casing supports a row of nozzle vanes through which are flowable hot combustion gases. A baffle surrounds the casing to define a cooling duct. A nacelle surrounds the turbine casing to...
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6178742 |
Rear mixer ejector for a turbomachine
A rear mixer ejector of a turbomachine for a supersonic aircraft has an ejector casing of rectangular cross-section fitted with movable flaps defining a variable geometry exhaust nozzle, and cold...
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6151882 |
Turbofan engine construction
A turbofan engine construction has a stator portion coupled to and centra disposed within a rigid casing. A rotor portion is disposed between the rigid casing and the stator portion for rotation...
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6058696 |
Inlet and outlet module for a heat exchanger for a flowpath for working medium gases
An inlet-outlet module 108 having both an inlet 58 and an outlet 62 for a heat exchanger system 52 is disclosed. Various construction details which improve the stiffness to weight ratio and the...
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6041589 |
Asymmetric turboprop booster
A booster-compressor assembly for supercharging air into a core engine that powers propellers of a turboprop aircraft engine includes an asymmetric annular booster duct aft of the propellers and...
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6032459 |
Turbine exhaust cooling in a microturbine power generating system
A microturbine power generation system includes a turbine having a diffuser. A plurality of openings are located in the diffuser. When an exhaust stream is leaving the turbine, ambient air is drawn...
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6021637 |
Integrated fluidic CD nozzle for gas turbine engine
An exhaust nozzle for a gas turbine engine includes converging and diverging nozzles joined together at a throat and attached to a frame. An injection slot is disposed at the throat in flow...
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6012281 |
Noise suppressing fluid mixing system for a turbine engine
The invention is a method and apparatus for combining two fluid streams, for example concentric inner (42) and outer (44) fluid streams in a turbine engine, thereby reducing noise emissions of the...
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5992140 |
Exhaust nozzle for suppressing infrared radiation
An exhaust nozzle (24 or 28) operative to suppress the InfraRed (IR) signature radiated from the high-temperature exhaust of an engine (12) which exhaust nozzle (24 or 28) includes an inlet conduit...
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5943856 |
Turbofan engine with reduced noise
A noise reduction kit for modifying a two (2) spool axial flow turbofan engine with multi-stage compressors and fan driven by multi-stage reaction turbines, and a thrust of at least about 18,000...
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5941065 |
Stowable mixer ejection nozzle
An ejector nozzle (10) including an first cowling (12), a second cowling (14), and opposed upright sidewalls (16) that together form an internal nozzle exhaust path is provided. A reconfigurable...
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5908159 |
Aircraft chute ejector nozzle
An aircraft axisymmetric exhaust nozzle (36) is provided for reducing noise in an intermediate bypass ratio turbofan engine. The nozzle (36) includes a plurality of chute ejectors (38) placed equal...
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5899058 |
Bypass air valve for a gas turbine engine
A bypass air valve for a gas turbine engine is provided which includes a liner, a strap, and means for selectively actuating the valve. The liner includes an inner radial surface, an outer radial...
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5894722 |
Variable geometry ramjet for aircraft
A ramjet for supersonic and/or hypersonic aircraft, designed to operate over a wide range of speeds, includes an inlet for a combustion supporting gas; a fuel injection device; and a ramjet body....
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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...
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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...
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5826424 |
Turbine bypass engines
A supersonic aircraft engine, either turbojet or turbofan, having a compressor, a diffuser, a combustion chamber, a turbine, and a nozzle passageway, and a turbine bypass passageway for bypassing...
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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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5775095 |
Method of noise suppression for a turbine engine
A method for suppressing noise in a turbofan engine includes segmenting coaxial inner and outer flow streams into circumferentially interleaved inner and outer segments beginning at a common...
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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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5761900 |
Two-stage mixer ejector suppressor
A two-stage mixer ejector concept ("TSMEC") is disclosed for suppressing the noise emanated by jet aircraft. This TSMEC was designed to help older engines meet the stringent new federal noise...
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5761899 |
Supersonic engine apparatus and method with ejector/suppressor
A supersonic engine having an ejector/suppressor. The engine has a rear discharge portion with an ambient air inlet section, a mixing section, and a rear discharge section. For noise suppression,...
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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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5755092 |
Exhaust nozzle mixer for a turbofan engine
An exhaust nozzle mixer for a turbojet engine is disclosed having a multi-lobed shroud extending from the exhaust nozzle of the turbojet engine, the shroud having a plurality of radially oriented...
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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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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...
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