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        <title>Free Patents Online: Power plants</title>
        <link>http://www.freepatentsonline.com./rssfeed/rsspat060.xml</link>
        <description>USPTO Class 060 Power plants</description>
        <language>en-us</language>
        <lastBuildDate>Tue, 15 Dec 2009 08:00:00 EST</lastBuildDate>
        <item>
            <title><![CDATA[Method of recovering carbon dioxide from a synthesis gas stream]]></title>
            <link>http://www.freepatentsonline.com./7632476.html</link>
            <description><![CDATA[A method of recovering carbon dioxide from a synthesis gas stream generated within a synthesis gas facility. After the synthesis gas stream is passed through at least one process heat exchanger of the steam generation system located downstream of the water-gas shift reactor, the temperature of the synthesis gas stream is increased while simultaneously adding steam to the synthesis gas stream. Thereafter, the synthesis gas stream is added to an absorption system having an absorption zone utilizing a solvent to absorb the carbon dioxide and a regeneration zone to disengage the carbon dioxide from the solvent and thereby regenerate the solvent. Heat is transferred from the synthesis gas stream to the regeneration zone to promote disengagement of the carbon dioxide from the steam and such that between about 40 percent and about 90 percent of the carbon dioxide originally present in the synthesis gas stream is recovered.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Premix burner for operating a combustion chamber]]></title>
            <link>http://www.freepatentsonline.com./7632091.html</link>
            <description><![CDATA[A premix burner for producing an ignitable fuel/air mixture has a swirl generator with at least two burner shells (B) which complement one another to form a throughflow body, which in each case have a first burner shell section ( 1 ) with a partial cone shape and together enclose an axially conically widening swirl space and which mutually define, in the axial cone longitudinal direction, tangential air inlet slots (LS), through which the combustion feed air (L) passes into the swirl space, in which an axially spreading swirl flow forms, and includes fuel feeds which are arranged at least in sections along the tangentially running air inlet slots (LS). A second burner shell section ( 8 ) curved in opposition to the first burner shell section ( 1 ), in each case designed in a partial cone shape, is added flush to the first burner shell section ( 1 ), a third burner shell section ( 9 ) adjoins the second burner shell section ( 8 ) flush, the third burner shell section ( 9 ) having a curvature tangentially adapted to the second burner shell section ( 8 ), and the third burner shell section ( 9 ) defines, on the one side in each case, one of the tangential air inlet slots (LS) and provides a leading edge ( 12 ) serving for the combustion feed air (L).]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Variable geometry guide vane for a gas turbine engine]]></title>
            <link>http://www.freepatentsonline.com./7632064.html</link>
            <description><![CDATA[A variable geometry inlet guide vane for a gas turbine aircraft engine includes an aerodynamic shell for turning inlet flow to a turbine or compressor and an internal spar spaced from the airfoil shell by an air gap. A number of actuation mechanisms grounded to the spar and connected to the inner surface of the aerodynamic shell adjust the shape of the shell in response to varying operating conditions of the engine, imbalanced aerodynamic loading of the shell or vibration or other transient loads on the shell.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Hydraulic system for limited wheel slip of traction drive system]]></title>
            <link>http://www.freepatentsonline.com./7631951.html</link>
            <description><![CDATA[A hydraulic system for limited wheel slip of a traction drive system includes first and second pilot directional valves between a hydraulic pump and first and second hydraulic wheel motors. If a wheel slips, the first or second pilot directional valves moves to a first position directing some hydraulic fluid through a restricted passage to the slipping motor and the remainder through an unrestricted passage to the opposite motor. Absent wheel slip, the pilot directional valve is in a second position directing all of the hydraulic fluid through an unrestricted passage to the corresponding motor. The first and second pilot directional valves detect wheel slippage and move between the first and second positions based on a first pilot signal corresponding to the pressure sensed entering the respective pilot directional valve, which is balanced against a biased spring and a second pilot signal from the opposite motor.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Hydraulic steering arrangement]]></title>
            <link>http://www.freepatentsonline.com./7631590.html</link>
            <description><![CDATA[The invention concerns a hydraulic steering arrangement ( 1 ) with a supply connection arrangement (P, T), a working connection arrangement (A, B) connectable to a steering motor ( 5 ), a steering unit ( 6 ) located between the supply connection arrangement (P, T) and the working connection arrangement (A, B), and a steering valve ( 14 ) whose outlet is connected to the working connection arrangement (A, B). It is endeavored to keep the load of such a steering arrangement small. For this purpose, the steering unit ( 6 ) is made as an open-center steering unit, an inlet ( 20 ) of the steering valve ( 14 ) being connected to a pressure supply arrangement ( 22 ) that can be activated by an activation of the steering valve ( 14 ).]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Methods and apparatus for assembling gas turbine engines]]></title>
            <link>http://www.freepatentsonline.com./7631504.html</link>
            <description><![CDATA[A combustor assembly is provided. The combustor assembly includes a combustion chamber and at least one transition portion extending downstream from the combustion chamber to facilitate channeling combustion gases from the combustor assembly. The assembly also includes at least one air control system coupled to the at least one transition portion. The air control system including at least one biasing mechanism coupled to a controller to facilitate reducing emissions from the combustor assembly operation.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Combustor with enhanced cooling access]]></title>
            <link>http://www.freepatentsonline.com./7631503.html</link>
            <description><![CDATA[A combustor for a gas turbine engine having an inner combustor wall and an outer combustor wall with a number of heat shields mounted internally thereto with fasteners. Each combustor wall has an end wall defining a combustor dome with a number of: fuel nozzle openings; impingement air openings; and heat shield fastener openings. Each of the end walls has an overlapping portion with mutually engaging sealing surfaces with the openings within the overlapping portions being aligned in overlapping pairs, where an exterior overlapping portion has at least one of the aligned openings of one overlapping pair being of larger dimension than the aligned opening in an interior overlapping portion.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Local cooling hole pattern]]></title>
            <link>http://www.freepatentsonline.com./7631502.html</link>
            <description><![CDATA[A combustor assembly includes an inner and an outer liner defining a combustion chamber. The inner and outer liner includes a plurality of cooling holes that are spaced a specified distance apart. The cooling holes include a specified inclination angle and circumferential angle. A first group of cooling holes is spaced apart according to a uniform geometric pattern and density. A second group disposed between the first group and some structural feature within the liner assembly is disposed at a non-uniform pattern and a hole density equal to the density of the first group of cooling holes. The non-uniform cooling hole arrangement increases cooling flow effectiveness to accommodate local disturbances and thermal properties.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Profiled sealing body with spring section]]></title>
            <link>http://www.freepatentsonline.com./7631501.html</link>
            <description><![CDATA[The present invention relates to a sealing body for sealing an outer component with respect to an inner component, in particular for a combustion chamber of a gas turbine. The outer component has a passage opening, through which the inner component projects out of the outer component. In the installed state, the sealing body is arranged in the region of the passage opening, surrounds the inner component in a circumferentially continuous manner, bears in a circumferentially continuous manner, by means of an inner sealing zone, against an outer sealing surface of the inner component and bears in a circumferentially continuous manner, by means of an outer sealing zone, against an inner sealing surface of the outer component. The sealing body is produced by deformation from at least one metal sheet that is in strip form and is circumferentially continuous. The inner sealing zone and the outer sealing zone are formed at a profiled section of the sealing body along the entire circumference.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Methods and apparatus to facilitate decreasing combustor acoustics]]></title>
            <link>http://www.freepatentsonline.com./7631500.html</link>
            <description><![CDATA[A method for operating a combustion system is provided. The method includes coupling the main swirler to the pilot swirler such that the main swirler substantially circumscribes the pilot swirler, supplying fuel to a first fuel circuit defined in the main swirler, and inducing swirling to the supplied fuel via a first set of swirler vanes positioned within the main swirler. The method also includes supplying fuel to a second fuel circuit defined in the main swirler, inducing swirling to the supplied fuel via a second set of swirler vanes positioned within the main swirler, each of the second set of swirler vanes comprising at least one second fuel passage defined therein, and coupling a shroud in flow communication to at least one of the first set of swirler vanes and the second set of swirler vanes, the shroud comprising at least one third fuel passage defined therein.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Axially staged combustion system for a gas turbine engine]]></title>
            <link>http://www.freepatentsonline.com./7631499.html</link>
            <description><![CDATA[An axially staged combustion system is provided for a gas turbine engine comprising a main body structure having a plurality of first and second injectors. First structure provides fuel to at least one of the first injectors. The fuel provided to the one first injector is adapted to mix with air and ignite to produce a flame such that the flame associated with the one first injector defines a flame front having an average length when measured from a reference surface of the main body structure. Each of the second injectors comprising a section extending from the reference surface of the main body structure through the flame front and having a length greater than the average length of the flame front. Second structure provides fuel to at least one of the second injectors. The fuel passes through the one second injector and exits the one second injector at a location axially spaced from the flame front.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Bearing health monitor]]></title>
            <link>http://www.freepatentsonline.com./7631498.html</link>
            <description><![CDATA[A turbocharger monitor including a sensor adapted and positioned with respect to a turbocharger housing to sense passing compressor blades, generating both rotor rotation information and rotor displacement information. A controller is configured to receive the generated information from the blade sensor, and to establish rotor rotation speed and an indicator of bearing condition.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Turbine heat shield with ribs]]></title>
            <link>http://www.freepatentsonline.com./7631497.html</link>
            <description><![CDATA[A turbocharger ( 10 ) with a heat shield ( 60 ) positioned between the turbine wheel ( 30 ) and the bearing housing ( 20 ), wherein the heat shield defines a gap ( 70 ) between the turbine wheel ( 30 ). The heat shield ( 60 ) and is provided with at least one rib ( 80 ) extending into the gap. In this gap, in the case of a conventional flat heat shield, the turbine wheel backface may act in the manner of a centrifugal pumping, pumping gas out from within the gap, creating a region of reduced pressure adjacent the outboard side of the turbine shaft bearing, drawing oil out the shaft bearing and into the space between the turbine wheel backface and the heat shield. The inventive heat shield has raised structures designed to interfere with the rotational and centrifugal flow of gas in the gap between heat shield and turbine wheel backface, thus prevent oil bypass.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Hydraulic unit with integral oil cooler]]></title>
            <link>http://www.freepatentsonline.com./7631496.html</link>
            <description><![CDATA[A hydraulic unit including an integrated fluid cooler. The fluid cooler includes a flow-through type heat exchanger. The hydraulic unit can include a pump, a motor, or both a pump and a motor. The fluid cooler can be carried by a housing of the hydraulic unit and a fan for moving air through the fluid cooler and circulating air over at least a portion of the housing of the hydraulic unit can be interposed between the fluid cooler and the housing. The fluid cooler can also be configured to function as a fan shroud. Fluid from the hydraulic unit as well as fluid from other sources can be circulated through the fluid cooler.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Hydraulic drive device for work machine]]></title>
            <link>http://www.freepatentsonline.com./7631495.html</link>
            <description><![CDATA[To provide a hydraulic drive device for a work machine that is capable of ensuring reduction in fuel consumption even in actual work where an operating condition changes every moment. Operating condition identifying unit ( 41 ) for identifying the operating condition and hydraulic pump control system ( 40 b ) for controlling absorption torque of hydraulic pump ( 18 ) are provided. When the operating condition identified by operating condition identifying unit ( 41 ) is a specific operating condition, hydraulic pump control system ( 40 b ) controls the absorption torque of hydraulic pump ( 18 ) to achieve hydraulic pump absorption torque characteristic line (PLb) matching the absorption torque of hydraulic pump ( 18 ) with output torque of engine ( 17 ) at engine output torque point Mb at which a fuel consumption rate is substantially minimum.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Hydrostatic transmission of a hydrostatic-mechanical power distribution transmission]]></title>
            <link>http://www.freepatentsonline.com./7631494.html</link>
            <description><![CDATA[A hydrostatic transmission of a hydrostatic-mechanical power distribution transmission in which the high-pressure limiting valves in the hydrostatic transmission are eliminated or adjusted to enable a working pressure higher than the working pressure on which the maximum pressure is based. For short time intervals, a pressure substantially higher than the pressure on which the maximum pressure is based under constant load of the hydrostatic transmission, can be adjusted. The hydrostatic transmission has high-pressure sensors connected with the control of the hydrostatic-mechanical power distribution transmission.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Exhaust gas purification control of diesel engine]]></title>
            <link>http://www.freepatentsonline.com./7631493.html</link>
            <description><![CDATA[A diesel particulate filter ( 14 ) which traps particulate matter and a NOx trap catalyst ( 13 ) which traps nitrogen oxides are installed in series in an exhaust passage ( 10 ) of a diesel engine ( 1 ). A controller ( 21 ) calculates a particulate matter deposition amount in the diesel particulate filter ( 14 ) (S 4 ). The controller ( 21 ), when the particulate matter deposition amount exceeds a first predetermined amount (PM 2 ), prevents sharp increase of the particulate matter deposition amount by prohibiting rich spike where the oxygen concentration of the exhaust gas is controlled to a value corresponding to a rich air-fuel ratio in order to regenerate the NOx trap catalyst ( 13 ) (S 301 , S 302 , S 306 ), and prevents the particulate matter deposition amount of the diesel particulate filter ( 14 ) from reaching a limit.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[System and method for inhibiting uncontrolled regeneration of a particulate filter for an internal combustion engine]]></title>
            <link>http://www.freepatentsonline.com./7631492.html</link>
            <description><![CDATA[Inhibiting uncontrolled regeneration of a particulate filter fluidly coupled to an exhaust manifold of an internal combustion engine may comprise reducing an oxygen concentration of exhaust gas supplied to the particulate filter if active regeneration of the particulate filter is in progress and rotational speed of the engine speed thereafter drops to an idle speed range from an elevated rotational speed that is greater than the idle speed range. Reducing the oxygen concentration of the exhaust gas supplied to the particulate filter may include any one or combination of reducing the oxygen concentration of intake air supplied to the intake manifold, reducing the air portion of the air-to-fuel ratio of the air-fuel mixture supplied to the engine and removing oxygen from the exhaust gas supplied to the particulate filter.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Method and system for passive regeneration of compression ignition engine exhaust filters]]></title>
            <link>http://www.freepatentsonline.com./7631491.html</link>
            <description><![CDATA[A method and system for passively regenerating particulate filters, catalyze soot filters and NOx adsorber catalysts for a vehicle having a compression ignition engine having an engine control module (ECM) including an integrated engine and emission system map, and an integrated starter/alternator/flywheel/retarder assembly, comprising sensing the condition of the particulate filters, catalyzed soot filters, and NOx adsorber catalysts and generating an initiate cleaning cycle signal upon sensing that the filters and catalysts require cleaning, monitoring operation of the engine and vehicle to determine the engine speed and vehicle speed and generating an engine speed/vehicle speed operating signal, receiving the initiate passive cleaning engine cycle signal and the engine speed vehicle speed operating signal, and initiating engine control parameter adjustments to modify engine operation to promote passive regeneration of the filters.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[System for assisting regeneration of pollution management means]]></title>
            <link>http://www.freepatentsonline.com./7631490.html</link>
            <description><![CDATA[The invention concerns a system for assisting regeneration of pollution management means ( 1 ) integrated in an exhaust line ( 3 ) of a diesel engine ( 4 ), wherein the engine ( 4 ) is associated with common ramp means ( 7 ) injecting fuel into the cylinders thereof, based on at least one post-injection and adapted to implement, in isocouple, through modification of the engine operation control parameters, at least two strategies called level 1 and level 2 and a second regeneration strategy including level 1 strategies and a sequence alternating level 2 and over-calibrated level 2 strategies, enabling different thermal levels to be achieved in the exhaust line. The invention is characterized in that it comprises means ( 8 ) for analyzing the vehicle running conditions and means ( 8 ) for comparing same to threshold values, to implement the first regeneration strategy for running conditions higher than the threshold values or the second regeneration strategy for running conditions lower than the threshold values.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Strategy for selectively bypassing a DPF in a hybrid HCCI combustion engine]]></title>
            <link>http://www.freepatentsonline.com./7631489.html</link>
            <description><![CDATA[In a conventional diesel combustion mode, one or more cylinders ( 12 ) of an engine ( 10 ) is or are fueled to cause conventional diesel combustion in each such cylinder. The resulting exhaust gas is treated by a diesel particulate filter ( 36 ) in an exhaust system ( 34 ) before exiting the exhaust system. In an alternative diesel combustion mode, such as HCCI, one or more cylinders of the engine are fueled to create in each such cylinder an in-cylinder fuel-air charge that ignites by auto-ignition as the charge is increasingly compressed. Also a bypass valve ( 38 ) is opened so that the resulting exhaust gas bypasses the DPF as the exhaust gas passes through the exhaust system.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Oxidation catalyst for removing fine soot particulates from exhaust gases and method of removing fine soot particulates using the same]]></title>
            <link>http://www.freepatentsonline.com./7631488.html</link>
            <description><![CDATA[Disclosed herein is an oxidation catalyst for use in removing fine soot particulates from exhaust gases of diesel engines, incinerators, boilers or other combustion devices, and to a method of removing fine soot particulates using the oxidation catalyst. The oxidation catalyst of the current invention functions to effectively remove fine soot particulates at a low temperature, and also, has thermal durability, and thus, the activity of the catalyst may be stably maintained even under thermal stress for a long time period. Further, the catalyst prevents poisoning due to a sulfur compound present in exhaust gases, and can maintain stable activity.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Constant volume rocket motor]]></title>
            <link>http://www.freepatentsonline.com./7631487.html</link>
            <description><![CDATA[The present invention is a constant volume rocket motor that uses a non-detonating constant-volume, bipropellant combustion process in pulse-mode operation. Opening and closing of the combustion chamber exhaust outlet is controlled by an actuated reciprocating thrust valve (RTV). Fuel enters the combustion chamber at low pressure with the RTV closed. The valve opens after or during combustion when combustion chamber pressure is at or near maximum. The motor has applications in reaction control systems and attitude control systems in spacecraft.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Thrust orienting nozzle]]></title>
            <link>http://www.freepatentsonline.com./7631486.html</link>
            <description><![CDATA[The present invention relates to a thrust orienting nozzle, shaped in such a way as to divide a principal propulsion gas flow coming from at least one gas generator into a first flow and a second flow for an ejection in a first half-nozzle and in a second half-nozzle and comprising at least one of following two piloting means: a means of dividing the principal flow into each of the two half-nozzles, and a means of orienting the thrust vector produced by each of the two half-nozzles.  The invention applies in particular to the yaw control of an aircraft without a vertical tail unit.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Tip turbine engine with a heat exchanger]]></title>
            <link>http://www.freepatentsonline.com./7631485.html</link>
            <description><![CDATA[A liquid-air heat exchanger extracts thermal energy from an engine lubricating fluid system. The liquid-air heat exchanger is located within a tailcone section and is in communication with a portion of the fan bypass airflow which enters the tailcone section through an annular tailcone exhaust nozzle entrance to transfer thermal energy into the combined airflow out of the engine to recover thrust loss ducted from the fan bypass stream.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[High pressure ratio aft fan]]></title>
            <link>http://www.freepatentsonline.com./7631484.html</link>
            <description><![CDATA[A fan assembly for a gas turbine engine includes a turbine rotor adapted to be disposed aft of a core of the gas turbine engine; a row of turbine blades carried by the rotor, each turbine blade extending from the rotor to a tip, the turbine blades adapted to extract energy from a stream of pressurized combustion gases generated by the core; and at least two rows of axially-spaced apart, radially-extending fan blades carried by the row of turbine blades for rotation therewith.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Method and system for reduction of jet engine noise]]></title>
            <link>http://www.freepatentsonline.com./7631483.html</link>
            <description><![CDATA[In an aspect, a method is provided for attenuating jet engine noise. Air velocity, adjacent to an inlet fan duct outer wall, is increased to a greater rate than typical velocity of an operational engine ambient inlet airflow, adjacent to the inlet fan duct outer wall. Boundary layer and associated turbulence is reduced or eliminated. Refraction and absorption of inlet sound into an acoustic liner is optimized. In an aspect, air velocity is increased by injecting air. In an aspect, air velocity is increased by exerting a suction force. In an aspect, a system is provided to attenuate jet engine noise. In an aspect, a fluid duct is provided opening to an inlet fan duct outer wall and to aft of a fan rotor.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Multiple phase power supply for rocket engines]]></title>
            <link>http://www.freepatentsonline.com./7631482.html</link>
            <description><![CDATA[Conventional power supplies that actify the grids of electric rockets use an output capacitor to smooth the output DC voltage signal. Large capacitors tend to store a great amount of energy. Arcing acts to transfer this energy to create a well or pit on an accelerator grid of the electric rockets that may eventually cause repeating arcing or perforation on the accelerator grid. Various embodiments of the present invention eliminate or reduce the need to use an output capacitor. Additionally, various embodiments of the present invention use multiple phases of an input signal into the power supply to cause the output DC voltage signal to be substantially smooth.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Cooled duct for gas turbine engine]]></title>
            <link>http://www.freepatentsonline.com./7631481.html</link>
            <description><![CDATA[A cooled exhaust duct for use in gas turbine engines is provided. The cooled exhaust duct includes an axial centerline, a circumference, an annulus, and a plurality of radially expandable bands. The annulus is disposed between a first wall and a second wall, and extends along the axial centerline. The first wall is disposed radially inside of the second wall. Each of the plurality of radially expandable bands extends circumferentially within the annulus. The bands are axially spaced apart from one another. Each band includes a first portion attached to the first wall, a second portion attached to the second wall and an intermediate portion connected to the first and second portions. The bands create circumferentially extending compartments that inhibit axial travel of the cooling air within the annulus.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Modular tip turbine engine]]></title>
            <link>http://www.freepatentsonline.com./7631480.html</link>
            <description><![CDATA[A tip turbine engine assembly includes a compressor module ( 12 ) and a fan module ( 14 ) located aft of the compressor module ( 12 ). The compressor module ( 12 ) and fan module ( 14 ) are fastened together along a mating portion with seals that generally prevent airflow from escaping through the mating portion. The compressor module ( 12 ) and fan module ( 14 ) are independently attachable to each other such that the compressor module ( 12 ) may be attached or detached to or from the fan module ( 14 ) without having to significantly disassemble the fan module ( 14 ), and verse visa.]]></description>
            <pubDate>Tue, 15 Dec 2009 08:00:00 EST</pubDate>
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