Bizarre Patents
Cloaking System Using Optoelectronically Controlled Camouflage
A Cloaking System designed to operate in the visible light spectrum, utilizes optoelectronics and/or photonic components to conceal an object within it.
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| Number | Title | Issue Date |
| 6672847 | Standing wave excitation cavity fluid pump A pump includes an outer body; and a wall within said outer body. The outer body and the wall define a pumping cavity and an excitation cavity within the outer body. An excitable medium is contained within the excitation cavity. An excitation source is co... | 01/06/2004 |
| 6322306 | Anti-rotation clips An anti-rotation clip is adapted to be attached to a fastener or connector assembly to ensure the tightened threaded connection of the assembly. The anti-rotation clip in one embodiment of the invention includes one or more co-axial clips to radially and ... | 11/27/2001 |
| 6313560 | Thermally protected electric machine An electric machine including a magnetic component, forming part of its rotor or stator that loses its magnetic characteristics above a certain chosen temperature is disclosed. This magnetic material forms part of a magnetic circuit that guides flux about... | 11/06/2001 |
| 6309177 | Concentricity ring There is provided a method of assembling a gas turbine engine using a concentricity ring to compensate for assembly tolerances. The blade tips of the gas turbine during turbine rotation define a tip surface of rotation concentric the shaft axis. Due to cu... | 10/30/2001 |
| 6293085 | Shaft decouple logic for gas turbine engine The present invention is addressed to a control logic for determining the occurrence of shaft decoupling in a gas turbine engine. The control logic in the preferred embodiment receives inputs for shaft rotational speed and/or compressor pressure and uses ... | 09/25/2001 |
| 6289677 | Gas turbine fuel injector A fuel injector for a combustor and a gas turbine engine, wherein the combustor includes a combustor wall defining a combustion chamber tube surrounded by pressurized air. The injector comprises a nozzle tip assembly protruding through the combustor wall ... | 09/18/2001 |
| 6290092 | Disposable protective closure A disposable closure for covering an opening of a first component during handling and shipping. The disposable closure comprises a body from which an offset interference member extends to prevent a second component from being erroneously connected to the ... | 09/18/2001 |
| 6289676 | Simplex and duplex injector having primary and secondary annular lud channels and primary and secondary lud nozzles A fuel injector for a combustor presented either as a simplex or duplex pressurized fuel injector, wherein the fuel is introduced into the injector to provide a swirl to the fuel in a first annular channel which communicates with a coaxial conical fuel sw... | 09/18/2001 |
| 6280139 | Radial split diffuser The invention relates to a radial split diffuser with an inner casing and an outer casing joined together along a cylindrical joint. Each diffuser passage is intersected by and extends transversely across the joint. The advantages of this design include: ... | 08/28/2001 |
| 6278262 | Auxiliary power unit system and method of operating an auxiliary power unit An auxiliary power unit ("APU") system and methods used to bring such system on-line and off-line are disclosed. An APU generator forming part of an APU system, is brought "on-line" smoothly in order to replace a primary generator operating at a steady-st... | 08/21/2001 |
| 6269628 | Apparatus for reducing combustor exit duct cooling The present invention is directed to gas turbine engines in which distinct components are integrally cast so as to increase resistance to thermal stress and thus decrease the amount of cooling airflow required to maintain the structural integrity of the c... | 08/07/2001 |
| 6267147 | Accumulator/oil tank for journal oil supply A combined oil tank and oil accumulator vessel having an internal chamber, and a moveable spring-loaded barrier within the internal chamber defining a low pressure oil tank portion and a high pressure accumulator portion separated by the moveable barrier.... | 07/31/2001 |
| 6256995 | Simple low cost fuel nozzle support The invention relates to a simple low cost fuel nozzle support stem that can be manufactured to meet extremely close tolerances with enhanced structural rigidity through use of a cylindrical stem body machined from solid bar stock. Superior thermal contro... | 07/10/2001 |
| 6253538 | Variable premix-lean burn combustor A method and device are provided to enable optimizing combustion conditions of a continuous combustion device to produce low emissions of nitric oxide, carbon monoxide and hydrocarbons at all operative conditions. The continuous combustion device includes... | 07/03/2001 |
| 6247317 | Fuel nozzle helical cooler A fuel injector for a gas turbine engine, including an axial fuel chamber and a spiral metering valve in the chamber.... | 06/19/2001 |
| 6237322 | Oil pump The invention relates to an oil pump driven by a hydraulic motor, that is itself driven by fuel pumped by a remote fuel pump through the engine fuel line. The hydraulic fuel driven oil pump is particularly advantageous for use in a gas turbine engine, to ... | 05/29/2001 |
| 6227801 | Turbine engine having improved high pressure turbine cooling A turbine engine having improved high pressure turbine cooling is disclosed. In the engine, relatively cool intermediate pressure (P2x) air is diverted from a region of a compressor section and over a high work turbine blade at a lower static pressure tha... | 05/08/2001 |
| 6227794 | Fan case with flexible conical ring There is provided a hardwall fan case for encasing a forward fan in a gas turbine engine. The fan case has a stiff annular shell spaced radially outward from the tips of the fan blades and a flexible ring which is an integral structural part of the shell.... | 05/08/2001 |
| 6217277 | Turbofan engine including improved fan blade lining An improved rotary engine, engine lining and engine casing and lining combination are disclosed. The engine is preferable a turbofan engine and includes a fan blade, rotatably mounted within a generally cylindrical casing for rotation about a lengthwise e... | 04/17/2001 |
| 6206090 | Concentric fuel/oil filters and heat exchanger package The invention relates to a combined heat exchanger and fluid filter that can be used in a gas turbine engine for example to simultaneously filter lubricating oil and fuel while transferring thermal energy between the oil and fuel. Conventionally, fuel and... | 03/27/2001 |
| 6183195 | Single slot impeller bleed A structure and a method to form the structure are provided for an impeller bleed passage of a compressor for a gas turbine engine. The compressor has an impeller assembly which includes an impeller rotor rotatably supported within an annular shroud havin... | 02/06/2001 |
| 6182437 | Fuel injector heat shield The invention relates to a method of inhibiting instability during operation of a gas turbine engine, where the instability is due to the uncontrolled interaction between the air filled gap defined by a heat shield and a fuel passage in a conventional fue... | 02/06/2001 |
| 6182436 | Porus material torch igniter The igniter for the combustor in a gas turbine engine includes a tubular member extending beyond the igniter tip, wherein the tubular member is a porous ceramic or high temperature nickel alloy. Fuel is fed to the bore of the tubular member by capillary a... | 02/06/2001 |
| 6183193 | Cast on-board injection nozzle with adjustable flow area A Tangential On-Board Injection (TOBI) nozzle or a Radial On-Board Injection (ROBI) nozzle with adjustable flow area in a gas turbine engine for directing a cooling air flow into a rotor assembly of the turbine is disclosed. The TOBI or ROBI nozzle is a u... | 02/06/2001 |
| 6179555 | Sealing of T.O.B.I feed plenum The invention provides a novel sealing device and plenum assembly particularly adapted for forming a plenum inwardly of a circumferential stator blade array in a gas turbine engine. A Tangential On Board Injection plenum (T.O.B.I.) is defined by assembly ... | 01/30/2001 |
| 6176677 | Device for controlling air flow in a turbine blade The present invention relates to gas turbines and more particularly to a device for controlling the flow of cooling air through a flowpath in a turbine blade. The device can be inserted in the inlet opening of the blade flowpath and be retained therein. T... | 01/23/2001 |
| 6176074 | Shaft decouple logic for gas turbine The present invention is addressed to a control logic for determining the occurrence of shaft decoupling in a gas turbine engine. The control logic in the preferred embodiment receives inputs for shaft rotational speed and/or compressor pressure and uses ... | 01/23/2001 |
| 6164911 | Low aspect ratio compressor casing treatment A compressor for a gas turbine engine, comprising a casing having an inner surface defining a plurality of circumferentially spaced-apart grooves adjacent the tips of a row of rotor blades. Each groove as a depth which is less than half the width thereof ... | 12/26/2000 |
| 6155056 | Cooling louver for annular gas turbine engine combustion chamber The invention provides in a gas turbine engine combustion chamber, an array of elongate louver strips between fuel nozzles of a combustion chamber dome wall, to cool the dome wall and contain combustion gases in the area between nozzles. The elongate louv... | 12/05/2000 |
| 6149380 | Hardwall fan case with structured bumper The invention provides a novel hardwall fan case for encasing the radial periphery of a forward fan in a gas turbine engine. The fan case includes a rigid annular fan case shell spaced a selected radial distance from the tips of the fan blades, thus defin... | 11/21/2000 |
| 6145300 | Integrated fan / low pressure compressor rotor for gas turbine engine An integrated fan and low pressure compressor rotor having a hub with a circumferential array of primary blades. Each primary blade has a forward fan blade portion housed in the engine inlet radially extending from the hub to the fan case and a rearward c... | 11/14/2000 |
| 6141968 | Fuel nozzle for gas turbine engine with slotted fuel conduits and cover A stem member for a gas turbine fuel nozzle includes inlet and outlet ends which are respectively adapted to be connected to a fuel adapter which is coupled to a fuel injector and a tip assembly having at least one spray orifice for atomizing fuel into a ... | 11/07/2000 |
| 6134874 | Integral inertial particle separator for radial inlet gas turbine engine An integral inertial particle separator with a de-icing feature in the form of a bifurcated radial intake for a gas turbine engine with an outside wall of the radial intake disposed in contact with heated oil from the engine lubrication system. To dischar... | 10/24/2000 |
| 6125624 | Anti-coking fuel injector purging device The invention relates to an air purge system for preventing coke buildup in gas turbine engine fuel injectors, and in particular in the relatively small orifice pressure atomizers of a primary fuel injector. The inventors have recognized that after engine... | 10/03/2000 |
| 6125312 | Maintenance and warranty control system for aircraft The system provides engine maintenance information automatically from fault code data received from an onboard engine performance monitoring computer. The maintenance information is provided by an HTML repair guide electronically called by the control sys... | 09/26/2000 |
| 6122905 | Compressor bleed valve A bleed valve is in fluid communication with the compressor fluid flow path and the bypass fluid flow path whereby a piston extends radially of the valve and includes a piston head radially remote from the compressor fluid flow path. A pneumatic chamber s... | 09/26/2000 |
| 6123506 | Diffuser pipe assembly The invention provides a diffuser assembly constructed of internal and external concentrically nested bowl-shaped shells for directing an outward flow of compressed air from a centrifugal compressor impeller to an axially rearward diffused annular flow. T... | 09/26/2000 |
| 6116852 | Turbine passive thermal valve for improved tip clearance control A gas turbine engine blade tip clearance control system and method is described. An annular housing is formed about an engine casing to which an annular shroud segment assembly is secured and closely spaced about blade tips of a stage of blades. The annul... | 09/12/2000 |
| 6109877 | Turbine blade-to-disk retention device The invention provides a turbine blade retention device installed in an axially extending gap between the blade root bottom and the slot floor. The retention device has two parts: a blade root retention clip and a spacer bar. The clip has an elongated web... | 08/29/2000 |
| 6109562 | Aircraft construction An aircraft construction having an aircraft engine and an engine nacelle having a wall housing the engine. A cowl door is provided in the wall of the nacelle providing access to the engine to service it. An exhaust duct extends from the engine through the... | 08/29/2000 |
