Did You Know...
...that it was melting ice cream that inspired the invention of the outboard motor? It was a lovely August day and Ole Evinrude was rowing his boat to his favorite island picnic spot. As he rowed, he watched his ice cream melt and wished he had a faster way to get to the island. At that moment the idea for the outboard motor was born!
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| Number | Title | Issue Date |
| 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 downstream end to an exhaust casing, the jacket serving to transmit for... | 10/07/2008 |
| 7377099 | System and method for cooling lateral edge regions of a divergent seal of an axisymmetric nozzle An axisymmetric nozzle for a gas turbine engine has divergent flaps and seals disposed about a central longitudinal axis thereof. The divergent flaps and seals each have an inner surface defining cooling air inlet holes at an upstream portion, cooling air exit holes... | 05/27/2008 |
| 7302793 | Methods and apparatus to reduce turbine engine nozzle basesheet stresses A method facilitates assembling a flap system for a gas turbine engine exhaust nozzle including at least one backbone assembly. The method comprises providing a basesheet including a pair of circumferentially-spaced sides coupled together by an upstream side and a d... | 12/04/2007 |
| 7296397 | Ventilation system for a convergent divergent exhaust nozzle The invention relates to a ventilation system for a convergent divergent exhaust nozzle in a bypass turbojet comprising an afterburn chamber surrounded by an annular passage through which circulates a stream of cooling air, a convergent divergent axisymmetric nozzle... | 11/20/2007 |
| 7293401 | Jet engine noise suppressor An embodiment of the invention is a technique to suppress noise in a jet engine. A noise suppressor includes an exhaust duct to exhaust a first stream from an air stream taken from an inlet. The exhaust duct has an exit end. The air stream is divided into the first ... | 11/13/2007 |
| 7240493 | Method and device for reducing engine noise A method and device to reduce the noise produced by jet aircraft engines and/or other supersonic nozzles involves the use of corrugated engine seals (30) for the secondary internal divergent flaps (14) of the nozzle (10). Such corrugated seals (... | 07/10/2007 |
| 7188477 | High temperature dynamic seal for scramjet variable geometry A seal assembly for use in an engine, such as a scramjet engine, having a movable element, such as inlet cowl flap, is provided. The movable element has an outboard structural member which requires thermal protection. The seal assembly includes a sealing element and... | 03/13/2007 |
| 7178325 | Divergent flap for a gas turbine engine A divergent flap assembly of a gas turbine engine includes a hotsheet, a backbone structure for supporting the hotsheet, and a plow portion secured to the backbone structure to bridge a gap between the hotsheet and an external flap. The plow portion is fabricated fr... | 02/20/2007 |
| 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 the tracking flap shutters adjacent thereto. ... | 10/10/2006 |
| 7108231 | Adjustment mechanism for a variable-shape wing Adjustment mechanism for adjustment area of variable-shape flow surface with two opposite skin surfaces includes plurality of whirl chambers swivelably arranged next to one another so that the whirl chambers are swivelable relative to one another, and the whirl cham... | 09/19/2006 |
| 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 sectional area of the nozzle in a throat region, and a bridge member po... | 08/29/2006 |
| 7032835 | Convergent/divergent nozzle with modulated cooling A nozzle system includes a multiple of circumferentially distributed convergent flaps, divergent flaps and inter-flap seals which circumscribe an engine centerline and define the radial outer boundary of a gas path. Each divergent flap includes a multiple of cooling... | 04/25/2006 |
| 7013650 | Flexible flap for a variable-section turbomachine nozzle In a variable-section turbomachine nozzle, a plurality of flexible follower flaps are provided that are interposed between adjacent controlled flaps against which the follower flaps are held by fastener means, each follower flap comprising a plurality of independent... | 03/21/2006 |
| 6993914 | Convergent-divergent turbojet nozzle The present invention relates to a convergent-divergent turbojet nozzle (1) comprising driven divergent flaps (4a), follower divergent flaps (4b) interposed between the driven flaps, and means (32) for supplying cooling air ... | 02/07/2006 |
| 6962044 | Method and apparatus of asymmetric injection into subsonic flow of a high aspect ratio/complex geometry nozzle The present invention reveals a method and apparatus for controlling the effective area and thrust vector angle of a fluid flow. In one embodiment, the fluid flow is controlled in an advanced, high aspect ratio, complex aperture geometry nozzle using asymmetric inje... | 11/08/2005 |
| 6935097 | Lock assembly that inhibits thrust reverser movement at or near the stowed position A lock assembly for a thrust reverser system that prevents thrust reverser deployment when the thrust reversers are in the stowed position, but does not prevent thrust reverser movement, in either the deploy or stow directions, when the thrust reversers are out of t... | 08/30/2005 |
| 6935098 | Turbomachine nozzle with noise reduction A nozzle comprising an inner barrel, a centerbody disposed inside the inner barrel so as to define a first channel for a primary flow, and an outer barrel surrounding the inner barrel so as to define a second annular channel for a secondary flow, the free end of the... | 08/30/2005 |
| 6895742 | Bifold door thrust reverser A fan thrust reverser includes an outer louver door joined to an inner blocker door by a drive link in a bifold configuration. The louver door is stowed closed in the outer skin of a fan nacelle outside the blocker door stowed closed in the inner skin of the nacelle... | 05/24/2005 |
| 6779336 | Cooled variable geometry exhaust nozzle A variable geometry exhaust nozzle 10 for a turbine engine includes convergent and divergent flaps 12, 18 that circumscribe a gaspath 26 and define convergent and divergent nozzle sections 30, 32 with a throat 34 therebetween. A pr... | 08/24/2004 |
| 6658854 | Methods and apparatus for retaining gas turbine engine nozzle basesheets A method for assembling a flap and seal system for a gas turbine engine exhaust nozzle including a plurality of backbone assemblies facilitates attaching a basesheet to a backbone. The method includes attaching an attachment system including at least one ... | 12/09/2003 |
| 6378781 | Exit area control mechanism for convergent divergent nozzles A convergent-divergent nozzle with an exit area control mechanism includes convergent and divergent petals extending from a nozzle structure on which a synchronising ring is allowed to rotate and to move in a radial direction. Angled lever arms pivot on t... | 04/30/2002 |
| 6378294 | System for activating an adjustable tube by means of an elastic ring for a thrust nozzle A steerable nozzle for a reaction engine comprises a fixed portion (1) for connection to the engine, a plurality of steerable flaps (21) mounted on one end (11) of the fixed portion, and flap steering means (3, 4, 22, 31). The nozzle is characterized in t... | 04/30/2002 |
| 6360527 | Axisymmetric, converging-diverging exhaust nozzle swiveled by a guided ring An axisymmetric, converging-diverging exhaust nozzle swiveled by a guided vectoring ring (20). The guides comprise three axial apertures (44) which are each located in a base firmly joined to relatively fixed structure and of which the center planes inter... | 03/26/2002 |
| 6349539 | Axisymmetric, converging-diverging, jet-deflecting turbojet-engine exhaust-nozzle An axisymmetric, converging-diverging turbojet-engine exhaust nozzle for jet deflection. The diverging flaps are connected by linkrods to a vectoring ring (13). The vectoring ring (13) is driven by linear actuators (20) anchored in the stationary structur... | 02/26/2002 |
| 6347510 | Axi-nozzle ejector seal A nozzle for a gas turbine engine is provided which includes an outer casing, a convergent section, a divergent section, an external fairing, and a collapsible seal member. The divergent section has an aft end and a forward end, and the forward end of the... | 02/19/2002 |
| 6299077 | Actuation system for convergent/divergent nozzle The horsepower requirements for the actuation system for a convergent/divergent exhaust nozzle for a gas turbine engine is reduced by the judicious selection of the crank arms and their location on a torque shaft that rotates to move a connecting link att... | 10/09/2001 |
| 6298658 | Multi-stable thrust vectoring nozzle A stream of primary gas flowing through a bi-stable thrust vectoring nozzle becomes attached to a first or second surface extending downstream of the nozzle, each surface incorporating one or more control ports for controlling to which surface the stream ... | 10/09/2001 |
| 6276126 | Axisymmetric, directable and adjustable turbojet-engine exhaust nozzle An axially symmetric turbojet-engine exhaust nozzle which is directable as a unit. The exhaust nozzle is situated downstream of an exhaust duct (1) fitted with a spherical wall (5). A single control ring (12) driven by linear actuators (30) allows regulat... | 08/21/2001 |
| 6212877 | Vectoring ring support and actuation mechanism for axisymmetric vectoring nozzle with a universal joint A vectoring ring support and actuation apparatus is provided for transferring the side loads acting on a vectoring ring and generated by a gas turbine engine thrust vectoring nozzle to a relatively stationary portion of the engine and tilting the vectorin... | 04/10/2001 |
| 6199772 | Linear actuation and vectoring ring support mechanism for axisymmetric vectoring nozzle Three vectoring ring support and actuation apparatuses are disposed in an equi-angular manner circumferentially about the engine casing. Each of the vectoring ring support and actuation apparatuses includes a vectoring ring means to transfer side loads fr... | 03/13/2001 |
| 6192671 | Cross bar centering mechanism for slave petals in covergent divergent nozzles with variable geometry Divergent petal arrangement for convergent-divergent nozzles with thrust vectoring capability through changes in the divergent section geometry, in which the position of each slave divergent petals 4 is determined by a centering mechanism 31, made up by t... | 02/27/2001 |
| 6148608 | Divergent petal arrangement for a convergent-divergent aircraft engine nozzle Divergent petal arrangement for convergent-divergent nozzles for application in aircraft engines, where the divergent section comprises master divergent petals (3) and slave divergent petals (4), having the latter a bent cross section with the concave sid... | 11/21/2000 |
| 6142416 | Hydraulic failsafe system and method for an axisymmetric vectoring nozzle A nozzle failsafe nozzle actuating system for an aircraft gas turbine engine variable exhaust nozzle having a plurality of pivotal flaps circumferentially disposed about a nozzle centerline and bounding an exhaust gas flowpath in the nozzle is provided wi... | 11/07/2000 |
| 6109021 | Vectoring nozzle calibration A method and system are used to calibrate a plurality of actuators joined to an actuation ring in a control system for vectoring exhaust flaps in a vectoring nozzle. The actuators include output rods which are positioned to respective first positions at w... | 08/29/2000 |
| 6102307 | Load strut for a variable geometry nozzle A load strut for divergent master petals of variable geometry nozzles, of the type which exhibit a control system constituted by three ring-like pieces, the external ring piece being divided into two half-rings, which joins the two half-rings and the corr... | 08/15/2000 |
| 6098400 | Divergent petal for gas turbine engine nozzle Divergent petal for a gas turbine engine nozzle. This petal (2) is articulated in its front edge to a convergent petal (1), by means of a cylindrical joint (4) while its back surface is articulated at an intermediate point to a compression bar (5) by mean... | 08/08/2000 |
| 6070830 | Faceted exhaust nozzle A fixed geometry duct defining a gas turbine engine exhaust nozzle includes a plurality of circumferentially adjoining flat triangular facets and coaxial first and second openings at opposite ends thereof. A method of making the duct includes scribing a p... | 06/06/2000 |
| 5893518 | Attachment means for flaps of variable exhaust nozzle The external flaps of a variable exhaust nozzle for a gas turbine engine are attached to the nozzle by a pair of pivotal rods attached to the nozzle's internal support structure and slidably fits into elongated spaced bushings extending along the longitud... | 04/13/1999 |
| 5842643 | Articulated exhaust nozzle fairing A variable area exhaust nozzle includes a divergent flap joined to an outer flap for allowing relative rotation and translation therebetween. An articulated fairing joins the aft ends of the divergent and outer flaps for providing aerodynamic streamlining... | 12/01/1998 |
| 5839663 | Gas turbine exhaust nozzle flap and flap seal apparatus An exhaust nozzle for a gas turbine engine is provided which includes a plurality of flaps and an abradable coating. Each flap includes seal surfaces with depressions disposed therein. The flaps are disposed about a structure within the engine, and are pi... | 11/24/1998 |
