Bizarre Patents
Dining Table Having Integral Dishwasher
A space-saving dishwasher, which may be installed within a counter top or table, having a dish-carrying rack that is vertically shiftable through the open top of the dishwasher for facilitating loading and unloading of the dishes.
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| Number | Title | Issue Date |
| 7805925 | Gas turbine engine exhaust duct ventilation A centerbody for the exhaust system of a gas turbine engine having an upstream end mounted within an exhaust duct casing of the exhaust system. The centerbody includes a plurality of ventilation openings defined in a centerbody wall which provide fluid flow communic... | 10/05/2010 |
| 7392651 | Turbomachine nozzle cover for reducing jet noise A cowl for a turbomachine nozzle, the cowl having a plurality of repeated patterns disposed circumferentially at a trailing edge, each pattern being asymmetrical about a midplane of the pattern containing a longitudinal axis of the cowl, and each pattern having a fi... | 07/01/2008 |
| 7370836 | Missile defense system and methods for evading heat seeking missiles A method for aiding a helicopter pilot to avoid a heat seeking missile includes the step of detecting a threat from a missile. The method also includes the step of reducing heat emanating from the helicopter's engine and rapidly reducing altitude. Then, when the thr... | 05/13/2008 |
| 7367531 | Systems and methods for evading heat seeking missles A method and system in an airborne aircraft to evade a heat seeking missile includes the steps of detecting the launch or “lock on” of a heat seeking missile and reducing the radiation from the aircraft's engine by reducing the engine speed to idle. The method m... | 05/06/2008 |
| 7350619 | Auxiliary power unit exhaust duct with muffler incorporating an externally replaceable acoustic liner Methods and apparatus are provided for an exhaust duct having an externally replaceable acoustic liner. The exhaust duct includes a forward section that is configured to be axially coupled with a bulkhead collar on the aircraft, a body section that is coupled to the... | 04/01/2008 |
| 7313909 | High-emissivity infrared coating applications for use in HIRSS applications A high emissivity (Hi-E) coating for use on the exhaust baffles of HIRSS systems. HIRSS systems were developed to reduce the infrared (IR) signature of helicopter engines. Increasing operating temperatures of helicopter engines have made the HIRSS systems less effec... | 01/01/2008 |
| 7310939 | Device for reducing the jet noise of a turbomachine A device for reducing the jet noise of a turbomachine, the turbomachine having a longitudinal axis and a substantially cylindrical nozzle extending along the longitudinal axis of the turbomachine, having a downstream end for mixing the flows of gas inside and outsid... | 12/25/2007 |
| 7308966 | Device for reducing jet engine exhaust noise using oscillating jets A device for reducing engine exhaust noise in an aircraft engine includes a number of oscillating jets which direct an oscillating flow into the engine exhaust. The oscillating jets are connected via channels to a turbomachinery source of high pressure gas, where th... | 12/18/2007 |
| 7287725 | Missile control system and method A missile includes a control system having divert and attitude control system thrusters with control valves. Each of the control valves has a nozzle plate having a plurality of small nozzles therein. The nozzle plate includes a pair of portions, one of which is rota... | 10/30/2007 |
| 7284364 | Passive exhaust suppressor and method A passive exhaust system is described that provides effective infrared signature suppression without affecting radar cross-section while maintaining stable function in crosswinds. A passive exhaust system may include an array of ducts with each duct having a primary... | 10/23/2007 |
| 7251927 | Jet nozzle mixer A second stage external jet nozzle mixer (20) includes identically formed lobes which equal in number the lobes of the first stage internal mixer. The external mixer works with the internal mixer, and furthers the mixing of the jet engine internal bypass flow... | 08/07/2007 |
| 7246481 | Methods 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 that air discharged from the noise suppression system generates a st... | 07/24/2007 |
| 7237378 | Turbomachine with low noise emissions for aircraft The invention relates to a turbomachine (1) for an aircraft comprising a gas generator (4) designed such that hot gases are ejected from a combustion chamber (28) towards the upstream side of the turbomachine, and also comprising a plurality of ... | 07/03/2007 |
| 7225607 | Gas turbine braking apparatus and method A device is provided which can serve one or more of the multiple functions of impeding rotation of a shaft de-coupled turbine rotor, selectively impeding rotation of a first spool of the engine, for example to permit a second spool to generate power for use in groun... | 06/05/2007 |
| 7219498 | Waffled impingement effusion method A combined impingement effusion method comprises brazing or welding a waffled impingement plate to the cold back-side surface of component having effusion holes there through. The impingement plate comprises a plurality of small baffle cells to relieve the thermal s... | 05/22/2007 |
| 7206111 | Sterically hindered PI-bridge nonlinear optical chromophores, processes including same, and devices therefrom In various embodiments, chromophores are described that include novel electron acceptors, novel electron donors, and/or novel conjugated bridges that are useful in nonlinear optical applications. In some embodiments, the present invention provides chromophore archit... | 04/17/2007 |
| 7178338 | Variable area nozzle An exhaust nozzle assembly for a gas turbine engine, the assembly comprises a main axis, an inner nozzle, an outer nozzle, a translatable centre-body and an actuator for translating the centre-body between a forward position and a rearward position. The centre-body ... | 02/20/2007 |
| 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 secondary flux flowing between an external wall of the nozzle and an intern... | 02/13/2007 |
| 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 create a mixed flow which may be used as a combined driver flow to com... | 12/26/2006 |
| 7137245 | High area-ratio inter-turbine duct with inlet blowing A bypass channel for use in an inter-turbine transition duct of a gas turbine engine is connected to a suction port disposed upstream of a high-pressure turbine and an injection port disposed downstream of the high-pressure turbine. The flow through the bypass chann... | 11/21/2006 |
| 7111448 | Jet nozzle mixer An external jet nozzle mixer includes identically formed lobes. The external mixer works with the internal mixer further to mix the engine internal bypass flow with the internal jet engine core flow to level the disparate flow velocities, to reduce the peak velociti... | 09/26/2006 |
| 7065957 | Segmented mixing device for jet engines and aircraft Disclosed is a means for reducing jet engine exhaust noise wherein mixing is enhanced between adjacent exhaust flows and between exhaust flow and free-stream flow. Also disclosed is a means for improving the thrust of jet engines and for reducing the noise and drag ... | 06/27/2006 |
| 7055329 | Method and apparatus for noise attenuation for gas turbine engines using at least one synthetic jet actuator for injecting air A method enables a gas turbine engine to be operated. The method comprises channeling exhaust gases from a core engine through an exhaust assembly and past at least one flow boundary surface, and selectively operating a noise suppression system extending from the at... | 06/06/2006 |
| 7043898 | Combined exhaust duct and mixer for a gas turbine engine A gas turbine engine including a gas exhaust duct assembly which comprises an annular shroud forming at least a section of an inner wall of a gas exhaust duct, a plurality of strut members radially projecting from the shroud, and a plurality of insert members. The s... | 05/16/2006 |
| 7025165 | Device to reduce the visible and infrared signature of a military vehicle A device to reduce the visible and infrared signature of a military combat vehicle by diluting the engine's exhaust and cooling gases. The device includes a caisson receiving both sources of heat flow to ensure a single outlet for both the exhaust gases and the cool... | 04/11/2006 |
| 7017331 | Jet nozzle mixer A second stage external jet nozzle mixer (20) includes identically formed lobes which equal in number the lobes of the first stage internal mixer. The external mixer works with the internal mixer, and furthers the mixing of the jet engine internal bypass flow... | 03/28/2006 |
| 7000378 | Gas turbine engine exhaust nozzle having a noise attenuation device driven by shape memory material actuators 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 extend in a generally axial direction from a downstream portion of the n... | 02/21/2006 |
| 6971229 | Confluent exhaust nozzle A gas turbine engine exhaust nozzle includes a nacelle having an inlet and main outlet at opposite ends, and a main duct extending therebetween. A secondary bypass duct extends radially through the nacelle upstream of the main outlet and includes an unobstructed sec... | 12/06/2005 |
| 6971240 | Methods and apparatus for exhausting gases from gas turbine engines A method facilitates assembling a gas turbine engine. The method comprises mounting a core engine to a vehicle, coupling a fuselage radially outward and around the core engine, and coupling an exhaust nozzle to the core engine to channel exhaust gases discharged fro... | 12/06/2005 |
| 6968695 | Compact lightweight ramjet engines incorporating swirl augmented combustion with improved performance A ramjet powered device that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which th... | 11/29/2005 |
| 6964699 | Rocket motor exhaust scrubber A wet scrubber having a series of chambers for capturing and cooling exhaust gases generated during static test firing of rocket motors. Exhaust gas enters an inlet to a first chamber and is cooled and slowed by a spray solution. HCL gas is condensed and absorbed by... | 11/15/2005 |
| 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 |
| 6918243 | Bi-propellant injector with flame-holding zone igniter A bi-propellant injector (66) includes a first injector element (68) and a second injector element (70) injecting a first propellant (69) and a second propellant (71), respectively, into a combustion chamber (53). A flame-ho... | 07/19/2005 |
| 6907724 | Combined cycle engines incorporating swirl augmented combustion for reduced volume and weight and improved performance A combined-cycle engine having at least one core engine and at least one ramjet engine. The ramjet utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an ox... | 06/21/2005 |
| 6854260 | Jet nozzle mixer An external jet nozzle mixer (20) includes identically formed lobes (48), equal in number those of the internal mixer (42). External mixer (20) works with internal mixer (42), further to mix the engine internal bypass flow with the... | 02/15/2005 |
| 6826901 | Convergent/divergent segmented exhaust nozzle A segmented exhaust nozzle for attenuating noise from a turbofan jet engine without adversely impacting the operability or operability limit related performance of the engine. The exhaust nozzle includes spaced apart fan nozzle inner and outer walls which form an an... | 12/07/2004 |
| 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 positions. In the first position the flow altering components are disposed sub... | 04/13/2004 |
| 6684622 | Rocket exhaust plume signature tailoring Methods and arrangements for tailoring rocket exhaust plume signatures of rocket exhaust systems are disclosed. The tailoring of the rocket exhaust plume signature is accomplished by providing and locating at least one structure having materials and/or ad... | 02/03/2004 |
| 6658839 | Convergent/divergent segmented exhaust nozzle A segmented exhaust nozzle for attenuating noise from a jet engine without adversely impacting the operability or operability limit related performance of the engine. The exhaust nozzle includes spaced apart fan nozzle inner and outer walls which form an ... | 12/09/2003 |
| 6655124 | External system and method for rocket exhaust plume signature tailoring Systems and methods are disclosed for tailoring rocket exhaust plume signatures of fuel-propelled vehicles. An uncombusted fuel is injected or sprayed into the exhaust plume of an ignited rocket. The injected or sprayed fuel modifies the rocket exhaust pl... | 12/02/2003 |
