|
Match
|
Document |
Document Title |
|
|
US20090320486 |
DUPLEX TAB EXHAUST NOZZLE
An exhaust nozzle includes a conical duct terminating in an annular outlet. A row of vortex generating duplex tabs are mounted in the outlet. The tabs have compound radial and circumferential aft...
|
|
|
US20090320446 |
Performance improvements for pulse detonation engines
A device and method for improving the performance of a pulse detonation engine. The device includes at least one of an exhaust structure and an ejector. The exhaust structure can be configured as a...
|
|
|
US20090314885 |
SYSTEM, METHOD AND APPARATUS FOR FLUIDIC EFFECTORS FOR ENHANCED FLUID FLOW MIXING
A fluidic effector provides enhanced plume mixing for an aircraft engine. Air jet injectors are located on both the external and internal cowl surfaces and angled in opposite directions to induce...
|
|
|
US20090277181 |
AIRCRAFT PROPULSION UNIT THAT COMPRISES AN EXHAUST PIPE WITH A SCALLOPED TRAILING EDGE
A propulsion unit includes at least one exhaust pipe ( 62, 76 ) that includes an air discharge that is delimited by a trailing edge ( 78, 82 ). The end part of the exhaust pipe ( 62, 76 ) includes...
|
|
|
US20090217670 |
EXHAUST NOZZLE SEAL WITH SEGMENTED BASESHEET DISPOSED BETWEEN SIDE RAILS
An aircraft engine exhaust nozzle basesheet includes longitudinally extending plurality of basesheet segments having panel bodies between segment leading and trailing edges and slidable sealing...
|
|
|
US20090211258 |
Rocket nozzles for unconventional vehicles
Improved rocket nozzle designs for vehicles with nozzles embedded in or protruding from surfaces remote from the desired thrust axis. The nozzle configurations are for rocket vehicles where the...
|
|
|
US20090199565 |
STAVE AND RING CMC NOZZLE
An engine exhaust nozzle comprises a plurality of CMC staves attached to one or more support rings arranged axially. The support rings provide a circumferential load path between the staves and for...
|
|
|
US20090162213 |
Pumping Ejector
The present invention provides a fluid pumping ejector. The ejector includes a reservoir containing a primary fluid and a mixing duct. An ejector nozzle ejects the primary fluid from said reservoir...
|
|
|
US20090145134 |
ROCKET ENGINE NOZZLE SYSTEM
The rocket engine nozzle system comprises a set of individual nozzles distributed in a ring around a central core of axially symmetrical shape that presents a central axis. Each individual nozzle...
|
|
|
US20090145133 |
EXHAUST LINER ATTACHMENT ARRANGEMENT
A turbine engine exhaust nozzle is disclosed that includes an exhaust liner having a first attachment structure. A liner support member includes a second attachment structure. A pin cooperates with...
|
|
|
US20090133406 |
FAN NOZZLE OF ADJUSTABLE SECTION
Varying the flowsection for air leaving the fan as a function of flying conditions. According to the invention, the nozzle has a ring of deformable panels arranged close to its trailing edge, each...
|
|
|
US20090133405 |
Combustible outgassing material lined altitude compensating rocket nozzle
A fixed sized bell rocket nozzle is lined with a layer of combustible material that is ignited during launch ignition and burns to outgas into the rocket exhaust for spatially variably confining...
|
|
|
US20090114740 |
NOZZLE ASSEMBLY WITH FLOW CONDUITS
A nozzle assembly for a turbine engine has a convergent portion for converging fluid flow from a turbine engine core. A divergent portion for diverging fluid flow from the turbine engine core is in...
|
|
|
US20090100678 |
ROCKET ENGINE NOZZLE AND METHOD OF FABRICATING A ROCKET ENGINE NOZZLE USING PRESSURE BRAZING
A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a...
|
|
|
US20090084111 |
TURBOMACHINE NOZZLE COWL HAVING JET NOISE REDUCTION PATTERNS
The invention relates to a cowl for a turbomachine nozzle, the cowl including a plurality of repetitive patterns disposed to extend a trailing edge of said cowl and spaced circumferentially apart...
|
|
|
US20090071164 |
FLUTED CHEVRON EXHAUST NOZZLE
A gas turbine engine exhaust nozzle includes a fluted shell terminating in a row of chevrons. The nozzle is radially serpentine circumferentially around the shells and has a circumferentially...
|
|
|
US20090064681 |
Scalloped Flexure Ring
A scalloped flexure ring. An illustrative embodiment of the flexure ring includes a ring body having a first ring body edge and a generally scalloped second ring body edge and a plurality of...
|
|
|
US20090064660 |
NOZZLE WITH YAW VECTORING VANE
An exhaust vane disposed in a divergent section of an aircraft gas turbine engine exhaust nozzle is sideways pivotable about a vane pivot axis. The nozzle vane pivot axis may be centrally located...
|
|
|
US20090031730 |
Nozzle Arrangement for a Gas Turbine Engine
A nozzle arrangement for a gas turbine engine includes an engine nozzle and an ejector nozzle arranged axially downstream thereof. A gap S is formed between the outlet of the engine nozzle and the...
|
|
|
US20090019857 |
MODULAR CHEVRON EXHAUST NOZZLE
An exhaust nozzle for a gas turbine engine includes a modular chevron. The chevron includes dual skins fixedly joined together at a base flange, and at a rim extending along the trailing edge of...
|
|
|
US20090013663 |
METHANE ENGINE FOR ROCKET PROPULSION
Disclosed is a methane engine for rocket propulsion. A methane supply pump ( 36 ) operated by a turbine ( 30 ) supplies a part of methane to a nozzle cooling channel ( 56, 156 ) installed on a...
|
|
|
US20090000304 |
INTEGRATED SUPPORT AND MIXER FOR TURBO MACHINERY
A support and air mixer includes an inner annular member, an outer annular member shaped and positioned such that an annular air gap is formed between the inner annular member and the outer annular...
|
|
|
US20080256957 |
Joint for a shape memory material
A joint between a first component ( 30 ) and a second component ( 32 ) and the second component ( 32 ) comprises a shape memory material component. The first component ( 30 ) has a half dovetail...
|
|
|
US20080236939 |
Exhaust silencer assembly
An exhaust silencer assembly for use with a gas turbine engine, the exhaust silencer assembly comprising an exhaust duct extension disposed downstream from an exhaust diffuser of the gas turbine...
|
|
|
US20080143058 |
TWO-PIECE AFT CLOSURE FOR A ROCKET MOTOR CASE
An aft closure assembly manufactured from two separate and distinct pieces made from different materials is provided for a rocket motor case. The aft closure assembly includes at least a retaining...
|
|
|
US20080120979 |
MORPHING STRUCTURE
An apparatus is provided that includes a body having a first wall and a second wall, at least one appending structure extending from an end of the body and at least one actuator positioned between...
|
|
|
US20080120978 |
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...
|
|
|
US20080115484 |
Mixer For Separate-Stream Nozzle
A mixer for a separate-stream turbojet nozzle, the mixer comprising along a longitudinal axis (X-X′) both a fastener shroud ( 10 ) for connecting said mixer to the exhaust casing of the nozzle,...
|
|
|
US20080098742 |
Combined control for supplying cooling air and support air in a turbine engine nozzle
A balance pressure control is provided for flaps which pivot in a rear of a gas turbine engine nozzle to change the cross-sectional area of the nozzle. An actuator drives a sync ring to move the...
|
|
|
US20080078161 |
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...
|
|
|
US20080078159 |
Wet Active Chevron Nozzle For Controllable Jet Noise Reduction
Disposed at or toward the trailing edge of one or more nozzles associated with a jet engine are injection ports which can selectively be made to discharge a water stream into a nozzle flow stream...
|
|
|
US20080078162 |
TURBINE EXHAUST CASE COWLING FOR A GAS TURBINE ENGINE
The cowling is used around a turbine exhaust case in gas turbine engine. It comprises a substantially conical wall with a longitudinal split forming opposite ends. Each end is directly...
|
|
|
US20080078163 |
Gas turbine engine nozzle liner with thermally compliant attachment brackets
A gas turbine engine has the convergent flaps and seals of an adjustable cross-sectional area nozzle connected to associated liners with a thermally compliant bracket. The bracket includes spaced...
|
|
|
US20080072604 |
Pressure balance control for gas turbine engine nozzle
A balance pressure control is provided for flaps which pivot in a rear of a gas turbine engine nozzle to change the cross-sectional area of the nozzle. An actuator drives a sync ring to move the...
|
|
|
US20080060344 |
EXHAUST DUCT AND TAIL CONE ATTACHMENT OF AIRCRAFT ENGINES
An annular exhaust duct of a gas turbine engine includes inner and outer cases co-axially disposed, and radially spaced apart by a plurality of airfoils radially extending therebetween. The outer...
|
|
|
US20080047273 |
TURBOMACHINE NOZZLE COVER PROVIDED WITH TRIANGULAR PATTERNS HAVING PAIRS OF VERTICES FOR REDUCING JET NOISE
The pattern relates to a cover for a turbomachine nozzle, the cover having a plurality of patterns each with an outline of triangular shape having a base and two vertices that are spaced downstream...
|
|
|
US20080041061 |
Multiple vane variable geometry nozzle
Nozzles having variable geometry are disclosed that are comprised of a plurality of vanes that contact one another and can slide with respect to one another. A control element forces the vanes to...
|
|
|
US20080041062 |
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...
|
|
|
US20080022689 |
Low profile attachment hanger system for a cooling liner within a gas turbine engine swivel exhaust duct
An exhaust duct assembly includes a cooling liner spaced apart from an exhaust duct case that articulate for use in a short take off vertical landing (STOVL) type of aircraft. The cooling liner...
|
|
|
US20080022690 |
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...
|
|
|
US20080016873 |
Outlet Device for a Jet Engine and a Jet Engine Comprising Such an Outlet Device
An outlet device for a jet engine includes an outlet nozzle and a plurality of guide vanes arranged movably in the outlet nozzle for guiding a gas from the jet engine for the purpose of steering a...
|
|
|
US20080000236 |
Seal assembly
A sprung seal assembly includes a flexible sprung seal having a center section disposed between opposing curved and cantilevered first and second end sections. First and second free edges of the...
|
|
|
US20080000235 |
Fan variable area nozzle for a gas turbine engine fan nacelle
A fan variable area nozzle (FVAN) selectively rotates a synchronizing ring relative the static ring to adjust a flap assembly through a linkage to vary an annular fan exit area through which fan...
|