Bizarre Patents
User-operated amusement apparatus for kicking the user's buttocks
An apparatus including a user-operated and controlled apparatus for self-infliction of repetitive blows to the user's buttocks by a plurality of elongated arms bearing flexible extensions that rotate under the user's control.
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| Number | Title | Issue Date |
| 8176739 | Coanda injection system for axially staged low emission combustors The low emission combustor includes a combustor housing defining a combustion chamber having a plurality of combustion zones. A liner sleeve is disposed in the combustion housing with a gap formed between the liner sleeve and the combustor housing. A secondary nozzl... | 05/15/2012 |
| 8037688 | Method for control of thermoacoustic instabilities in a combustor A method for controlling a temperature distribution within a combustor having a plurality of chamber sections comprising controlling a fuel-to-air ratio in the chamber sections. At least two chamber sections have different fuel-to-air ratios to create a non-uniform ... | 10/18/2011 |
| 7370467 | Turbofan case and method of making A casing for a gas turbine includes a fan case, an intermediate case and a gas generator case integrated with one another. ... | 05/13/2008 |
| 7363756 | Method for combustion of a fuel In a method for the combustion of a fuel, a fuel or a premixed combustible mixture is introduced into a combustion space as a combustible fluid open jet. The velocity of the open jet is selected in such a way that it is impossible for a stable flame front to form, i... | 04/29/2008 |
| 7337614 | Engine fueling method A gas turbine engine is piloted with a pilot flow of fuel delivered to a combustor as a liquid. A first additional flow of the fuel is also delivered to the combustor as a liquid. A second additional flow of the fuel is vaporized and delivered to the combustor as a ... | 03/04/2008 |
| 7308793 | Apparatus and method for reducing carbon monoxide emissions The present invention discloses an apparatus and method for reducing the carbon monoxide emissions emitted by a pilot injector of a gas turbine combustor. Multiple embodiments of a means for establishing a recirculation zone are disclosed whereby a portion of the fu... | 12/18/2007 |
| 7302801 | Lean-staged pyrospin combustor A combustor assembly includes a combustor chamber having a primary and intermediate zone that provides for reduced flame temperatures. The combustor assembly includes first and second pluralities of injectors. The first plurality of injectors introduces fuel to a pr... | 12/04/2007 |
| 7249946 | Thermal generator and combustion method for limiting nitrogen oxides emissions by re-combustion of fumes The invention relates to a thermal generator comprising a furnace tube (2) wherein a fuel is burnt, recombustion means (14, 15) for reducing the nitrogen oxides content present in said fumes and means (3) for recovering the heat of the fumes res... | 07/31/2007 |
| 7249721 | Device and method for injecting a liquid fuel into an air flow for a combustion chamber The present invention relates to a device for injecting a liquid fuel into a pressurized air flow (7), in particular for a combustion chamber, comprising a hollow cylindrical body (10) of longitudinal axis (YY′) delimiting a substantially cylindrical... | 07/31/2007 |
| RE39596 | Method and apparatus for the destruction of volatile organic compounds A system for the destruction of volatile organic compounds while generating power. In a preferred embodiment the system comprises a combustor and a reaction chamber connected to an exit of the combustor. A primary inlet to the combustor supplies a primary fuel to th... | 05/01/2007 |
| 7194863 | Turbine speed control system and method One embodiment of the invention provides a turbine control system that adjusts the control thresholds of two-position valves, which provide propellant to the turbine, based on turbine load so as to compensate for increased turbine speed overshoot at low load and the... | 03/27/2007 |
| 7185497 | Rich quick mix combustion system A premix chamber for a combustor of a gas turbine engine comprises a cylindrical chamber having a premix chamber wall, the cylindrical chamber having a chamber inlet end longitudinally separated from a chamber outlet end along a central axis, a chamber inlet plate i... | 03/06/2007 |
| 7117676 | Apparatus for mixing fluids A premixer for a combustor to entrain a selected volume of fuel in an oxidizer to be combusted to heat the oxidizer. The combustor is for a gas powered turbine which employs the hypergolic or high energy air stream which will allow a fuel to be combusted in the abse... | 10/10/2006 |
| 7104065 | Damping arrangement for reducing combustion-chamber pulsation in a gas turbine system A description is given of a damping arrangement for reducing resonant vibrations in a combustion chamber (1), with a combustion-chamber wall (2), which is of double-walled design and, with an outer wall-surface part (22) and an inner wall-surfac... | 09/12/2006 |
| 7096671 | Catalytic combustion system and method Aspects according to the invention relate to a catalytic combustor system for a turbine engine and an associated method. Catalytic combustors are used in connection with turbine engines because they can minimize the formation of oxides of nitrogen during combustion.... | 08/29/2006 |
| 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 lowered. An aft end of a combustion liner is telescopically received... | 08/29/2006 |
| 7093444 | Simultaneous combustion with premixed and non-premixed fuels and fuel injector for such combustion The present invention relates to a premixed fuel injector for low NOx emission and high heating load combustion. The premixed fuel injector of the present invention comprises a center nozzle and a plurality of outer nozzles arranged around the center nozzle, wherein... | 08/22/2006 |
| 7093441 | Gas turbine annular combustor having a first converging volume and a second converging volume, converging less gradually than the first converging volume A gas turbine engine combustor has inboard and outboard walls. A forward bulkhead extends between the walls and cooperates therewith to define a combustor interior volume. In longitudinal section, a first portion of the combustor interior volume converges from fore ... | 08/22/2006 |
| 7093438 | Multiple venture tube gas fuel injector for a combustor A gas fuel injector includes a first header plate; a second header plate spaced downstream from the upstream header plate; and a plurality of venturi tubes arranged in rows and sealably secured to the first and second header plates. Each of the venturi tubes include... | 08/22/2006 |
| 7089741 | Gas turbine combustor A gas turbine combustor includes a combustion liner in which a combustion region is formed; and a housing provided for a wall of the combustion liner in a predetermined circumferential region of the combustion liner to form a resonance space between the combustion l... | 08/15/2006 |
| 7065955 | Methods and apparatus for injecting cleaning fluids into combustors A method details injecting water into a gas turbine engine to facilitate cleaning an inner surface of a combustor. The method comprises removing an axial fuel injector from the combustor, wherein the fuel injector includes a nozzle stem, and inserting a spray nozzle... | 06/27/2006 |
| 7065954 | Turbine, particularly useful for small aircraft A turbine includes a combustion chamber with deflectors generating vortices in a secondary gas flow into the combustion chamber, thereby confining the flame front from penetrating into the cold region of the chamber under variable operating conditions, simplifying c... | 06/27/2006 |
| 7007478 | Multi-venturi tube fuel injector for a gas turbine combustor A combustor for a gas turbine includes a main fuel injector for receiving compressor discharge air and mixing the air with fuel for flow to a downstream catalytic section. The main fuel injector includes an array of venturis each having an inlet, a throat and a diff... | 03/07/2006 |
| 7007486 | Apparatus and method for selecting a flow mixture A counter-flow system for use in a turbine for selecting various mixtures of fluids for use with the system. The system may be used for a combustor for a gas powered turbine which employs a heat exchanger to combust a fuel without the emission of undesired chemical ... | 03/07/2006 |
| 7003960 | Method and appliance for supplying fuel to a premixing burner A method and an appliance are described for supplying fuel to a premixing burner for operating a gas turbine, which premixing burner has at least one burner shell (1, 2) at least partially bounding an axially extending premixing burner space, having a premixi... | 02/28/2006 |
| 7003939 | Method for the adaption of the operation of a staged combustion chamber for gas turbines This invention relates to a fuel injection system for a staged combustion chamber (1) of a gas turbine aero-engine, in which a certain quantity of fuel is permanently supplied to the pilot burner(s) (3) and in which fuel is apportioned to the main burn... | 02/28/2006 |
| 7003958 | Multi-sided diffuser for a venturi in a fuel injector for a gas turbine A combustor for a gas turbine includes a main fuel injector for receiving compressor discharge air and mixing the air with fuel for flow to a downstream catalytic section. The main fuel injector includes an array of venturis each having an inlet, a throat and a diff... | 02/28/2006 |
| 6939392 | System and method for thermal management A system for the management of thermal transfer in a gas turbine engine includes a heat generating sub-system in operable communication with the engine, a fuel source to supply a fuel, a fuel stabilization unit to receive the fuel from the fuel source and to provide... | 09/06/2005 |
| 6931862 | Combustor system for an expendable gas turbine engine A combustor system for a miniature gas turbine engine includes fuel injection via orifices which direct fuel into fuel-air injection tubes which feed a fuel-rich mixture of fuel and air into a leading end of the combustor liner to form a primary burning region. Fuel... | 08/23/2005 |
| 6915636 | Dual fuel fin mixer secondary fuel nozzle A dual fuel premix nozzle and method of operation for use in a gas turbine combustor is disclosed. The dual fuel premix nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of gas fuel and compressed air in order to provide ... | 07/12/2005 |
| 6908303 | Premixed air-fuel mixture supply device A premixed air-fuel mixture supply device is joined to a combustor liner included in a combustor for a gas turbine or an aircraft engine. The premixed air-fuel mixture supply device has a pilot fuel injection unit having an inner wall, and a prevaporizing, premixing... | 06/21/2005 |
| 6880339 | Combination of a premixing chamber and a combustion chamber, with low emission of pollutants, for gas turbines running on liquid and/or gas fuel An improved combination (110) of a premixing chamber (112) and a combustion chamber (111), with low emission of pollutants, for gas turbines running on liquid and/or gas fuel, in which the combustion chamber (111) has a truncated conical ... | 04/19/2005 |
| 6467272 | Means for wear reduction in a gas turbine combustor A wear reduction means for a fuel nozzle interface of an industrial gas turbine combustor is disclosed. The wear reduction means includes a replaceable insert welded into the engagement location of the fuel nozzle tip. The fuel nozzle tip is coated with a... | 10/22/2002 |
| 6253555 | Combustion chamber comprising mixing ducts with fuel injectors varying in number and cross-sectional area A three stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36,40,44) is supplied with premixed fuel and air by respective fu... | 07/03/2001 |
| 6192688 | Premixing dry low nox emissions combustor with lean direct injection of gas fule Lean premixed combustion of a hydrocarbon fuel and air is combined with lean direct injection of hydrocarbon fuel and carrier fluid such as air or inert gas or a mixture of air and inert gas into a combustor downstream of the premixed reaction zone in ord... | 02/27/2001 |
| 6105370 | Method and apparatus for rejecting waste heat from a system including a combustion engine A method and apparatus are provided for rejecting waste heat (12) from a system (10) including a combustion engine (14), an oxidizer supply (16), and a fuel supply (18). The method includes the steps of providing a fuel flow (32) from the fuel supply (18)... | 08/22/2000 |
| 6047550 | Premixing dry low NOx emissions combustor with lean direct injection of gas fuel Lean premixed combustion of a hydrocarbon fuel and air is combined with lean direct injection of hydrocarbon fuel and air into a combustor downstream of the premixed reaction zone in order to achieve extremely low levels of emissions of oxides of nitrogen... | 04/11/2000 |
| 6000212 | Catalytic combustion chamber with pilot stage and a method of operation thereof A catalytic combustion chamber is provided with at least two catalytic combustion zones arranged in flow series. In a first mode of operation fuel is supplied from first fuel injectors, positioned upstream of the first catalytic combustion zone, into the ... | 12/14/1999 |
| 5950417 | Topping combustor for low oxygen vitiated air streams A multi-stage topping combustor unit having rich burn, and lean burn zones followed by a quench/dilution zone. Combustible fuel gas is supplied only to the rich burn zone, and an oxygen-containing air-flue gas mixture is supplied to all three zones in a f... | 09/14/1999 |
| 5927076 | Multiple venturi ultra-low nox combustor An ultra-low NOx gas turbine combustor having a dual fuel capability. The combustor has a plurality of venturis in flow communication with a corresponding number of fuel lances such that fuel injected from each lance into a corresponding venturi is mixed ... | 07/27/1999 |
