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7617685 |
Quick change fastener system for attaching liner bracket to convergent flap and seal in turbine nozzle
A quick change connection is provided for attaching a bracket and liner subassembly to convergent flaps and seals in an adjustable nozzle for a gas turbine engine. A threaded attachment member has...
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7607306 |
Infrared suppressor apparatus and method
A method for suppressing infrared radiation from an engine of an aircraft operating in an environment includes directing hot exhaust from the aircraft engine into a lobed mixer of a single baffle...
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7607305 |
One-piece baffle infrared suppressor apparatus and method
A method for suppressing infrared radiation from an aircraft engine includes directing hot exhaust from the aircraft engine into a lobed mixer of a single baffle infrared suppressor having a single...
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7600384 |
Gas exhaust nozzle for a bypass turbomachine having an exhaust or throat section that can be varied by moving the secondary cowl
The invention relates to an exhaust nozzle for a bypass turbomachine, the nozzle comprising a central body, a primary cowl surrounding the central body to define a primary channel, and a secondary...
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7596951 |
Exhaust nozzle for a gas turbine engine
An exhaust nozzle for a gas turbine engine includes a nozzle casing having top and bottom walls and side walls. A liner is provided within the nozzle casing to define a cooling passage. The top and...
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7587899 |
Shape memory alloy actuated adaptive exhaust nozzle for jet engine
The proposed adaptive exhaust nozzle features an innovative use of the shape memory alloy (SMA) actuators for actively control of the opening area of the exhaust nozzle for jet engines. The SMA...
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7581400 |
Elbow-shaped propulsion gas exhaust assembly in an aircraft
A propulsion gas exhaust assembly is presented for use in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator. The assembly may include a first cylindrical...
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7581399 |
Damped coil pin for attachment hanger hinge
The present invention is directed toward a suspension system for mounting an exhaust duct liner within an exhaust duct of a gas turbine engine. An exhaust liner suspension system comprises a...
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7581384 |
Turbomachine nozzle cover provided with triangular patterns having a point of inflexion for reducing jet noise
The invention relates to an annular cover for a turbomachine nozzle, the cover having a plurality of patterns extending a trailing edge of said cover and spaced apart circumferentially from one...
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7581382 |
Gas turbine engine air valve assembly
A gas turbine engine air valve assembly has first and second valving elements. The second element is rotatable about a first axis relative to the first element. The rotation controls a flow of air...
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7578133 |
Reduced radar cross section exhaust nozzle assembly
An exhaust nozzle assembly includes a plurality of interfitting flap assemblies that are moveable between a maximum area ratio and a minimum area ratio. Each of the pluralities of flap assemblies...
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7578132 |
Gas turbine engine exhaust nozzle
A gas turbine engine exhaust nozzle arrangement for the flow of exhaust gases therethrough between an upstream end and a downstream end thereof comprising a nozzle and a plurality of tabs which...
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7568348 |
Nozzle assembly for rocket and ramjet applications
A nozzle assembly for thrust or thrust vector control of a rocket or ramjet, comprising an elongated nozzle housing and a pair of vane members mounted for pivotal movement within a central portion...
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7555905 |
Self-actuating bleed valve for gas turbine engine
A bleed valve for bleeding air from a compressed air chamber at start-up of a gas turbine engine is self-actuated. The bleed valve moves between open and closed positions based on the pressure...
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7555904 |
Thermally compliant rivet connection for connecting turbine engine liner to convergent flap and seal for turbine nozzle
A bracket for attaching a liner to the divergent flaps and seals in a gas turbine engine convergent/divergent nozzle includes a rivet connection. There is clearance between a rivet and an opening...
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7543452 |
Serrated nozzle trailing edge for exhaust noise suppression
A nozzle for a gas turbine engine is provided with undulations on a core and/or fan exhaust flow nozzle. An annular wall defines a fluid flow passage and includes a base portion and an adjoining...
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7543451 |
Aircraft engine exhaust shroud
A shroud for an aircraft engine exhaust plume, the shroud being formed of a flexible material secured at one end to the exhaust nozzle and selectively extendable downstream with the exhaust plume...
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7533533 |
Jet engine with a variable section nozzle of which at least one flap pivots about a pin, pins for flaps
The jet engine of the invention comprises an exhaust nozzle of variable section, comprising at least one flap pivot mounted about a pin, the pin being joined to the fixed structure of the jet...
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7520124 |
Asymmetric serrated nozzle for exhaust noise reduction
An exhaust nozzle for use in a gas turbine engine comprises a flow body for receiving exhaust gas from the turbine engine and includes a leading edge and a trailing edge. The leading edge connects...
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7500353 |
Eductor swirl buster
A system is provided in an aircraft that includes a power unit and an eductor. The power unit has a nozzle, and is configured to exhaust gas, a portion of which flows in a swirling motion, through...
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7464554 |
Gas turbine combustor heat shield panel or exhaust panel including a cooling device
A combustor heat shield panel has interior and exterior surfaces with a number of circuitous non-interconnected cooling gas passageways having inlets on the exterior surface and outlets on the...
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7464536 |
Methods and apparatus for assembling gas turbine engines
A method is provided for operating a gas turbine engine including a core engine having a core stream duct, an inner bypass duct, an outer bypass duct, and a nozzle assembly downstream of the core...
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7430867 |
Gas turbine multiple sectioned exhaust duct
A duct comprising an inner casing spaced apart from an outer casing and which also comprises a number of interfaced duct sections must be assembled in such a way to prevent relative redial movement...
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7430852 |
Turbojet having a large bypass ratio
A turbojet comprises at least a fan, a compressor, a combustion chamber, a turbine, and a rigid substantially-cylindrical jacket fastened at its upstream end to an intermediate casing and at its...
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7418813 |
Gas turbine engine exhaust nozzle including an infrared suppression system having a plurality of U-shaped blocking fins and method of assembling said exhaut nozzle
A method for assembling a gas turbine engine includes mounting a core engine to a vehicle, coupling a fuselage radially outward and around the core engine, coupling an exhaust nozzle to the core...
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7412832 |
Method and apparatus for operating gas turbine engines
A method for operating a gas turbine engine includes channeling compressed air from the gas turbine engine to a noise suppression system, and selectively operating the noise suppression system such...
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7406821 |
Adapter device for a rocket engine nozzle having a movable diverging portion
An adapter device for controlling a rocket engine nozzle under conditions of external pressure that can lead to the jet separating inside the nozzle, the nozzle being fitted with a diverging...
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7377109 |
Apparatus and method for reduction of jet noise from turbofan engines having separate bypass and core flows
An exhaust flow system for use with a turbofan jet engine that provides separate fan flow and core flow streams that are not mixed. The system includes a fan nozzle and a primary flow nozzle. The...
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7334394 |
Localized arc filament plasma actuators for noise mitigation and mixing enhancement
A device for controlling fluid flow. The device includes an arc generator coupled to electrodes. The electrodes are placed adjacent a fluid flowpath such that upon being energized by the arc...
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7299635 |
Device for mixing two flows of fluid which are initially guided separate from one another in a bypass jet engine
The invention relates to a device for mixing two fluid flows, initially guided separately from one another, in a two-circuit reaction engine, a mixing tube which encloses a hot core stream being...
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7296411 |
Method and system for regulating internal fluid flow within an enclosed or semi-enclosed environment
The present invention features a fluid flow regulator that functions to significantly influence fluid flow across the surface of an object, as well as to significantly effect the performance of the...
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7272930 |
Exhaust diffuser assembly with tunable velocity profile
A turbine engine exhaust diffuser assembly having a tuneable exhaust velocity profile is disclosed. The assembly includes structure that generates a desired, tunable velocity profile within working...
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7269951 |
Throat retention apparatus for hot gas applications
A nozzle for use in a hot gas valve is provided that includes a housing, an insert, and a throat retainer. The housing is constructed of an insulating material and has a flow path formed therein....
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7229029 |
Propulsion system
A propulsion system for a jet- or rocket-propelled vehicle in which the resulting jet exhaust nozzle profile is a 3D spiral. The propulsion system can be applied to any jet- or rocket-propelled...
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7200538 |
Methods and apparatus for modeling gas turbine engines
A method enables modeling of a gas turbine engine that includes a pulse detonation system. The method includes providing a pulse detonation modeling system, predicting characteristics of the engine...
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7188417 |
Advanced L-channel welded nozzle design
A fluid flow nozzle is formed by a plurality of adjacent L-shaped channels forming successive channel pairs. Each channel has a linking member joined to a radial member. Each linking member is...
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7181915 |
High temperature centerbody for temperature reduction by optical reflection and process for manufacturing
A high temperature gas turbine component for use in the gas flow path that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the gas flow path of the...
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7174718 |
Device for controlling propulsive jet mixing for aircraft jet engines
A device for controlling propulsive gas mixing at an outlet of an aircraft jet engine, wherein propulsive jets are composed of a hot primary jet exiting from a nozzle of the jet engine and a...
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7174704 |
Split shroud exhaust nozzle
A variable geometry convergent-divergent nozzle for a gas turbine engine includes a centerbody extending rearward along a longitudinal axis of the engine which has a throat section of increased...
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7155898 |
Thrust vector control system for a plug nozzle rocket engine
A thrust vector control system for a plug nozzle rocket engine for propelling and maneuvering a vehicle is disclosed. The plug nozzle rocket engine includes a housing having a nozzle throat, a plug...
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7152410 |
System and method for dumping surge flow into eductor primary nozzle for free turbine
A method and apparatus for dumping surge bleed air into a primary nozzle of a free gas turbine engine. The surge bleed air is introduced into gas turbine exhaust flow within the primary nozzle to...
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7117682 |
Turbojet axisymmetric nozzle controlled hot flap shutter
A controlled hot flap shutter for a turbojet nozzle includes a friction surface made of metal, and including straight lateral flanks to reduce the gap between each controlled hot flap shutter and...
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7117681 |
Thrust control valve
A thrust control valve includes a nozzle having a gas supply chamber, a gas jetting chamber and a connecting passage therebetween. The nozzle has an upstream inner surface defining the gas supply...
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7114323 |
Jet exhaust noise reduction system and method
A system for reducing jet noise emission from an internally mixed gas turbine engine exhaust, comprising a fan/core flow mixer having a plurality of mixer lobes and a common flow nozzle having an...
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7100358 |
Turbine exhaust case and method of making
A structural turbine exhaust case of a gas turbine engine, comprises inner and outer case portions; a bearing housing connected to the inner case portion for supporting a main spool of the gas...
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7096668 |
Cooling and sealing design for a gas turbine combustion system
An interface region between a combustion liner and a transition duct of a gas turbine combustor is disclosed having improved cooling such that component life is increased and metal temperatures are...
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7096662 |
Variable area throat exhaust nozzle with vectorable sideways shifting of exhaust flow
A nozzle includes a sideways split and aftwardly swept nozzle ramp extends between a fixed lower nozzle wall and a pivotal upper nozzle wall pivotally connected to an aft end of the nozzle and...
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7096661 |
Axial divergent section slot nozzle
An axial divergent section slot nozzle for an engine is provided. The nozzle has a plurality of spaced apart divergent flaps, at least one device for moving the divergent flaps to change a cross...
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7093423 |
Methods and apparatus for operating gas turbine engines
A method of assembling a gas turbine engine includes coupling an annular exhaust duct to the gas turbine engine, coupling a plurality of chevrons to the annular exhaust duct, and coupling a chevron...
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7082766 |
One-piece can combustor
A can combustor for an industrial turbine includes a transition piece transitioning directly from a combustor head-end to a turbine inlet using a single piece transition piece. In an exemplary...
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