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Gas Turbine Engine patents



      
           
This page is updated frequently with new Gas Turbine Engine-related patent applications. Subscribe to the Gas Turbine Engine RSS feed to automatically get the update: related Gas RSS feeds. RSS updates for this page: Gas Turbine Engine RSS RSS


Gas turbine engine tip clearance control

Gas turbine engine tip clearance control

Eccentric diaphragm adjusting pins for a gas turbine engine

Eccentric diaphragm adjusting pins for a gas turbine engine

Eccentric diaphragm adjusting pins for a gas turbine engine

Turbine engine and vane system

Date/App# patent app List of recent Gas Turbine Engine-related patents
10/23/14
20140314568
 Gas turbine engine tip clearance control patent thumbnailGas turbine engine tip clearance control
A gas turbine engine is disclosed having a thermoelectric device capable of changing a tip clearance in a turbomachinery component. In one non-limiting form the turbomachinery component is a compressor.
10/23/14
20140314567
 Gas turbine engine tip clearance control patent thumbnailGas turbine engine tip clearance control
A gas turbine engine is disclosed having a thermoelectric device capable of changing a tip clearance in a turbomachinery component. In one non-limiting form the turbomachinery component is a compressor.
10/23/14
20140314550
 Eccentric diaphragm adjusting pins for a gas turbine engine patent thumbnailEccentric diaphragm adjusting pins for a gas turbine engine
The present invention relates to a stator stage (100) for a gas turbine and a method of adjusting a relative position between a vane segment (110) and a centre section (101) of the stator stage. A groove (102) is formed between a first rim (103) and a second rim (104) of a radially outer edge of the centre section, wherein the groove, the first rim and the second rim run along a circumferential direction (131).
10/23/14
20140314548
 Turbine engine and vane system patent thumbnailTurbine engine and vane system
One embodiment of the present invention is a unique vane system. Another embodiment is a unique gas turbine engine.
10/23/14
20140314542
 Gas turbine engine exhaust diffuser with movable struts patent thumbnailGas turbine engine exhaust diffuser with movable struts
An exhaust diffuser for a gas turbine engine gas turbine engine includes a multiple of circumferentially spaced struts that extend between an inner gaspath wall and an outer gaspath wall, at least one of the multiple of circumferentially spaced struts movable about a strut axis.. .
10/23/14
20140314540
 Gas turbine engine synchronization ring patent thumbnailGas turbine engine synchronization ring
A synchronization ring for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a synchronization ring for a variable vane assembly. A plurality of rollers are attached to the synchronization ring for engaging a case on the gas turbine engine..
10/23/14
20140312611
 Locking fluid fittings patent thumbnailLocking fluid fittings
A fluid conduit for a gas turbine engine includes a first fluid conduit attachable to a second fluid conduit and securable together with a lockable connector. The connector includes a first portion including external threads and a second portion receiving the first portion and including internal threads mating to the external threads of the first portion.
10/23/14
20140311164
 Gas turbine engine and turbine blade patent thumbnailGas turbine engine and turbine blade
One embodiment of the present invention is a unique turbine blade for a gas turbine engine. Another embodiment is a unique gas turbine engine.
10/23/14
20140311163
 Method of manufacturing a turbomachine component, an airfoil and a gas turbine engine patent thumbnailMethod of manufacturing a turbomachine component, an airfoil and a gas turbine engine
One embodiment of the present invention is a unique method of manufacturing a component for a turbomachine, such as an airfoil. Another embodiment is a unique airfoil.
10/23/14
20140311157
 Vane carrier temperature control system in a gas turbine engine patent thumbnailVane carrier temperature control system in a gas turbine engine
A vane carrier temperature control system for use in a gas turbine engine includes a first cooling air source, a second cooling air source, and an air temperature control system. The first cooling air source supplies a first portion of vane carrier cooling air extracted from a compressor section of the engine to a first section of a vane carrier that supports a plurality of rows of vanes within a turbine section of the engine.
10/23/14
20140311155
Flow splitter for a fluid system of a gas turbine engine
A gas turbine engine is disclosed having a working fluid system capable of moving a working fluid. The working fluid system includes a flow splitter capable of splitting the working fluid into different streams.
10/23/14
20140311154
Flow merging device for a fluid system of a gas turbine engine
A gas turbine engine is disclosed having a working fluid system capable of moving a working fluid. The working fluid system includes a flow union member capable of combining different streams of working fluid.
10/23/14
20140311153
Combustor assembly for a gas turbine engine
A combustor assembly for a gas turbine engine includes a hanger and a combustor liner fixed to the hanger such as, for example, by an annular weld joint. The combustor liner has an inner surface extending along an axis and is operable to define either a radial outer boundary or a radial inner boundary of the combustion chamber.
10/23/14
20140311152
Reverse flow ceramic matrix composite combustor
A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner enclosing a combustion chamber. The inner liner having a dome portion at an upstream end of the combustor and a downstream combustor exit defined between a small exit duct portion and a large exit duct portion.
10/23/14
20140311150
Fuel nozzle for a pre-mix combustor of a gas turbine engine
A fuel nozzle for use in a gas turbine includes a pre-mix flow passage for directing a flow segment of a flow of a working fluid through the fuel nozzle. A first swirler vane and a second swirler vane extend within the pre-mix flow passage.
10/23/14
20140311149
Gas turbine engine fan blade airfoil profile
A fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of cartesian coordinates set forth in table 1.
10/16/14
20140308175
Catalytic combustor in gas turbine engine
A catalytic combustor (2) in a gas turbine engine (gt) includes a casing (54) for accommodating a catalyst carrier (10) therein, a catalyst retaining body (62) interposed between the casing (54) and the catalyst carrier (10) for retaining an outer peripheral surface of the catalyst carrier (10) to an inner peripheral surface of the casing (54) and also for preventing a gas (g2) from leaking in a downstream direction through an outer periphery of the catalyst carrier (10), a support material (64) disposed on a downstream side of the direction of flow of the gas to be treated in the catalyst carrier (10) for holding the catalyst carrier (10), and a downstream side regulating member (72) disposed on the downstream side of the catalyst retaining body (62) for avoiding a movement of the catalyst retaining body (62) in a direction of flow of the gas (g2).. .
10/16/14
20140308174
Catalytic combustor in gas turbine engine
A catalytic combustor (2) for use in a gas turbine engine (gt) includes catalyst units (u1, u2, u3) in a multistage. The catalyst unit (u1, u2, u3) in each stage includes a support material (64) for supporting the respective catalyst unit (u1, u2, u3) against the pressure of a gas.
10/16/14
20140308113
Structure and method for providing compliance and sealing between ceramic and metallic structures
A structure providing compliance and sealing between ceramic or ceramic composite (cmc) part and a metallic part has an interface component for centering the cmc part in the metallic part, thus reducing thermal stress motion of the cmc component. In gas turbine engine applications, the structure comprises a cmc blade track inserted in a clip placed within a metallic hanger.
10/16/14
20140306460
High speed direct drive generator for a gas turbine engine
A motor/generator apparatus for direct coupling to a high rpm, high power shaft is disclosed for one or more of starting and/or extracting power from a gas turbine engine, controlling engine responsiveness, providing a temporary power boost, providing some engine braking and modulating compressor and turbine transient performance as engine power is changed. For example, an axial flux motor/generator configuration is disclosed in which a centrifugal gas compressor rotor is also the rotor of an axial electrical flux motor/generator.
10/16/14
20140305136
Mounting arrangement
A gas turbine engine is provided that has a rigid dressing raft mounted to a rigid part of the gas turbine engine. The rigid dressing raft includes at least a part of a component or system of the gas turbine engine.
10/16/14
20140305134
Rigid raft for a gas turbine engine
A rigid raft is provided for a gas turbine engine. The raft has an electrical system and/or a fluid system embedded in the material of the raft.
10/16/14
20140305130
Aircraft environmental control system inlet flow control
A system and method for controlling bleed air flow into an air cycle machine that includes a bleed air inlet and a conditioned air outlet is provided. The system and method include discharging bleed air from an operating gas turbine engine, sensing exhaust gas temperature (egt) of the gas turbine engine, sensing conditioned air temperature at the conditioned air outlet, and controlling bleed air flow into the air cycle machine based on the sensed egt and on the sensed conditioned air temperature..
10/16/14
20140305129
Gas turbine engine support strut assembly
Support strut assembly for supporting a casing of a functional unit of gas turbine is provided having a strut body for supporting the casing to ground, a ball pivot element mounted to the strut body and a rocker lever mounted to the ball pivot element. The rocker lever inserts into a bearing bore of a support body as part of the casing or ground, the rocker lever inserts into the bearing bore via clearance fit so a pivotal point is generated at a first contact area between the rocker lever and an inner surface of the bearing bore, the rocker lever pivots within the bearing bore around the pivotal point.
10/16/14
20140304989
Rotor blade assembly tool for gas turbine engine
A rotor blade assembly tool for coupling a plurality of circumferentially spaced rotor blades to a rotor disc of a turbine rotor assembly, includes a base ring with an array of circumferentially spaced resilient fingers axially extending from the base ring. The resilient fingers are configured each to radially abut a blade seal, damper or other engine component against radially inner facing surfaces of platforms of the respective blades when the blades are being seated onto the disc during an assembly procedure.
10/09/14
20140301861
Airfoil having an erosion-resistant coating thereon
A compressor blade having an airfoil that comprises oppositely-disposed convex and concave surfaces, oppositely-disposed leading and trailing edges defining therebetween a chord length of the airfoil, a forward-most nose of the airfoil located at the leading edge and having a profile, a blade tip, and an erosion-resistant coating. The coating is present on the concave surface near the trailing edge, optionally present on the nose, optionally present on the convex surface, wherein the convex surface is free of the erosion resistant coating within at least 20% of the chord length from the nose.
10/09/14
20140301849
Turbine split ring retention and anti-rotation method
A gas turbine engine disk split retainer ring system is provided and includes an apparatus and method for retaining a split ring in relation to a turbine cover plate or disk. Pegs are used to capture and retain a split retainer ring of the gas turbine rotor in relation to the cover plate.
10/09/14
20140301834
Turbine cylinder cavity heated recirculation system
A turbine engine heating system configured to heat compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine heating system may include a heating air extraction system configured to withdraw air from the turbine engine and to pass that air thru a heating element configured to increase a temperature of the air supplied by the heating air extraction system.
10/09/14
20140301820
Turbine engine shutdown temperature control system with nozzle injection for a gas turbine engine
A turbine engine shutdown temperature control system configured to limit thermal gradients from being created within an outer casing surrounding a turbine blade assembly during shutdown of a gas turbine engine is disclosed. By reducing thermal gradients caused by hot air buoyancy within the mid-region cavities in the outer casing, arched and sway-back bending of the outer casing is prevented, thereby reducing the likelihood of blade tip rub, and potential blade damage, during a warm restart of the gas turbine engine.
10/09/14
20140298821
Gas turbine engine provided with heat exchanger, and method for starting same
A method of starting a gas turbine engine includes a primary warming step of warming a heat exchanger (6) by means of a compressed gas (g1) while with the use of an inverter motor (im) the rotation speed of the engine is maintained at a partial rotation speed, a secondary warming step of warming the heat exchanger (6) by activating a main combustor (2) to gradually increase the temperature of an exhaust gas (g3) while with the use of the inverter motor (im) the rotation speed is maintained at the partial rotation speed, and a speed increasing step of increasing the rotation speed to the rated rotation speed with the use of the inverter motor (im) while the fuel burning amount of the main combustor (2) is increased.. .
10/09/14
20140298820
Gas turbine engine and method for starting same
A starting method for a gas turbine engine includes a primary warming step of warming up the gas turbine engine while a constant primary warm-up rotation speed is maintained by an inverter motor and a secondary warming step of warming up the gas turbine engine while a constant secondary warm-up rotation speed is maintained by further increasing the speed of the inverter motor. The primary warming step terminates when an electric power required by the inverter motor attains a predetermined preset electric power value.
10/09/14
20140298818
Control method and control device for lean fuel intake gas turbine
A method and a device for controlling a lean fuel intake gas turbine engine, which can stably maintain operation of the gas turbine engine by preventing misfire and burnout of a catalytic combustor even when a catalyst in the combustor is deteriorated. A difference between measured temperatures of an inlet and an outlet of the combustor with respect to a methane concentration in an intake gas that is to be taken into the lean fuel intake gas turbine engine is compared with reference temperature difference data that is data indicating difference between temperatures of the inlet and the outlet of the combustor including a catalyst in its initial state to be a reference, and at least one of the inlet temperature and the outlet temperature of the combustor is controlled based on a difference between the measured temperature difference and the reference temperature difference data..
10/09/14
20140298788
Gas turbine engine including pneumatic actuator system
A gas turbine engine that includes a compressor section and a pneumatic actuator system is delivered. The pneumatic actuator system includes a bleed air duct that receives bleed air from the compressor section and delivers the bleed air through an accumulator and to an actuator.
10/02/14
20140297155
Aircraft power outtake management
A system and method for controlling the operation of a gas turbine engine supplying power to an aircraft. The engine is controlled according to a reading of an amount of power drawn from the supplied power.
10/02/14
20140294598
Turbine blade
The cooling effectiveness of a turbine blade that a gas turbine engine or the like is provided with is further increased by providing a convex portion that is arranged in the inner portion of a cooling air hole and that is provided projecting out from the inner wall surface of the cooling air hole.. .
10/02/14
20140294589
Asymmetrically slotted rotor for a gas turbine engine
A spool for a gas turbine engine includes at least one rotor disk defined along an axis of rotation and at least one rotor ring defined along the axis of rotation, with the rotor ring being in contact with the rotor disk. The rotor disk and rotor ring are contoured to define a smooth rotor stack load path..
10/02/14
20140294581
Gas turbine engine access panel
An integrated access panel is disclosed that can be used to assist in adjusting a component like a fan blade of a turbofan engine. In one form the integrated access panel is hinged at one end such that the panel remains attached during adjustment of the fan blade.
10/02/14
20140294572
Wall section for the working gas annulus of a gas turbine engine
A seal segment is provided for a shroud ring of a rotor of a gas turbine engine. The seal segment is positioned, in use, radially adjacent the rotor.
10/02/14
20140294571
Seal segment
A seal segment is provided for a shroud ring of a rotor of a gas turbine engine. The seal segment is positioned, in use, radially adjacent the rotor.
10/02/14
20140294564
Auxiliary power units and other turbomachines having ported impeller shroud recirculation systems
Embodiments of a turbomachine, such as a gas turbine engine, are provided. In one embodiment, the turbomachine includes an impeller, a main intake plenum in fluid communication with the inlet of the impeller, and an impeller shroud recirculation system.
10/02/14
20140294562
Strut for a gas turbine engine
The strut is for use in a gas turbine engine has body, typically having an airfoil shape, having a leading edge and a trailing edge. The leading edge has at least one gas inlet in direct fluid communication with at least one outlet located in the trailing edge through which gas may be redirected from the leading edge to the trailing edge through the strut for injection back into a wake region downstream of the strut..
10/02/14
20140294559
Multiple mode gas turbine engine gas fuel system with integrated control
A method for operating a gas turbine engine is disclosed. The method includes determining whether the gas turbine engine fuel system is in a steady state mode or a transient mode.
10/02/14
20140291993
Method for operating lean fuel intake gas turbine engine, and gas turbine power generation device
A method for stably operating a lean fuel intake gas turbine engine by controlling the rotation speed of the lean fuel intake gas turbine engine for which it is difficult to control the rotation speed by controlling a fuel flow rate, is provided. In a method for operating a lean fuel intake gas turbine engine (gt) configured to use, as a fuel, a combustible component contained in a low-concentration methane gas to drive a power generator, a power converter (17) is provided between an external electric power system (19) and the power generator (11), and a rotation speed of the power generator (11) is controlled by the power converter (17), to control a rotation speed of the gas turbine engine (gt)..
10/02/14
20140290272
Gas turbine engine cooling arrangement
A gas turbine engine comprises a compressor, a combustion chamber, an outer casing, an inner casing and a cooling arrangement. The outer casing surrounds the compressor and the combustion chamber and the combustion chamber has turbine nozzle guide vanes.
10/02/14
20140290271
Mounting arrangement
A rigid electrical raft is provided to a gas turbine engine via a fusible mount arrangement. The rigid electrical raft may be a part of an electrical system of the gas turbine engine, for example a part of the electrical harness.
10/02/14
20140290269
Duct blocker seal assembly for a gas turbine engine
A seal system for a gas turbine engine includes a cover plate with a radial flange; a seal carrier adjacent the cover plate; an outer compliant seal supported by the seal carrier; an inner compliant seal supported by the seal carrier, the inner compliant seal engaged with the radial flange; and a spring between the cover plate and the seal carrier.. .
10/02/14
20140290268
Gas turbine engine geared architecture axial retention arrangement
A gas turbine engine includes a fan, an engine static structure, a geared architecture to drive the fan and supported relative to the static structure, a fan drive turbine to drive the geared architecture, a first member secured to the geared architecture, and a second member secured to the engine static structure and configured to cooperate with the first member to limit movement of the geared architecture relative to the static structure. A fan drive gear system and method are also disclosed..
10/02/14
20140290266
Fuel and actuation system for gas turbine engine
A fuel system for an aircraft comprises a boost pump, a main fuel pump and a motive pump. The boost pump receives fuel from a storage unit.
10/02/14
20140290265
Gas turbine engine with transmission
A multi spool gas turbine engine with a differential having a selectively rotatable member which rotational speed determines a variable ratio between rotational speeds of driven and driving members of the differential. The driven member is engaged to the first spool and a rotatable shaft independent of the other spools (e.g.
10/02/14
20140290262
Low flow correction for gas turbine engine fuel valve characteristics
A method for controlling a gas turbine engine fuel control valve during low flow conditions includes positioning the fuel control valve in an operating position. The method also includes determining a fuel control valve flow sensor flow rate while in the operating position and determining a corrected effective flow area (“cda”) of the fuel control valve.
10/02/14
20140290261
Compensation for gas turbine engine fuel valve characteristics
A method for operating a gas turbine engine fuel system with a fuel control valve is disclosed. The method includes metering fuel through the fuel control valve with an effective flow area versus command data set.
10/02/14
20140290254
Cyclonic dirt separating turbine accelerator
A dirt separator assembly for a gas turbine engine comprises a cyclonic accelerator in flow communication with compressor discharge air, the accelerator having a plurality of passages, each passage having an inlet, an outlet and at least one vent located in the passage, a plurality of turning vanes disposed along each of the passages, the passage turning tangentially between the inlet and the outlet, the accelerator passages decreasing from a first cross-sectional area to a second cross-sectional area and said turning vanes inducing helical swirl of compressed cooling air, and, at least one vent located in the accelerator passages for expelling dust separated from the swirling compressed cooling air.. .
10/02/14
20140290252
Gas turbine engine provided with scroll
A gas turbine engine having high reliability is provided by suppressing occurrence of thermal stress between a scroll and a support member thereof. A gas turbine engine equipped with a combustor of a single-can type includes a scroll to guide a combustion gas fed from a combustor to a turbine while swirling the combustion gas about a rotation axis, a flange member to support the scroll with respect to the gas turbine engine from an inner peripheral side of the scroll, and a coupling member of an annular shape to couple the scroll and the flange member with each other.
10/02/14
20140290213
Duct blocker seal assembly for a gas turbine engine
A seal system for a gas turbine engine includes an annular seal carrier and an annular compliant seal mounted around the annular seal carrier, the compliant seal includes a multiple of legs in cross-section.. .
09/25/14
20140286782
Turbine blade staking pin
A staking pin for a gas turbine engine is disclosed. The staking pin may include a solid portion extending part of a length of the staking pin, and a hollow portion extending an additional part of the length of the staking pin.
09/25/14
20140286781
Integral fan blade wear pad and platform seal
A fan section for a gas turbine engine includes a fan hub having a slot. A platform is supported by the fan hub.
09/25/14
20140286773
Gas turbine engine
The gas turbine engine (s1) includes: turbine blades (7b); and a cooling air supply unit (11) to supply cooling air to the turbine blades (7b). A flow path surface (31) is formed so as to be positioned in an upstream side of the turbine blades (7b) and so as to be connected to a base surface (32) in which the turbine blades (7b) are provided.
09/25/14
20140286771
Cooling passages for turbine buckets of a gas turbine engine
The present application and the resultant patent provide a turbine bucket for a gas turbine engine. The turbine bucket may include a platform, an airfoil extending radially from the platform, and a number of cooling passages defined within the airfoil and near an outer surface of the airfoil.
09/25/14
20140286765
Composite aerofoil vane
A composite aerofoil vane for a gas turbine engine extends in use in a generally radial direction across an axially- and circumferentially-extending annular duct. The vane comprises a plurality of first reinforcing fibres extending in a generally radial direction and a plurality of second reinforcing fibres extending in generally axial and circumferential directions.
09/25/14
20140286763
Gas turbine outer case active ambient cooling including air exhaust into sub-ambient cavity
A gas turbine engine including an outer case and an exhaust gas passage defined within the outer case for conducting an exhaust gas flow from a turbine section of the gas turbine engine. A cooling channel is associated with an outer surface of the outer case, the cooling channel having a channel inlet and a channel outlet.
09/25/14
20140286760
Seal assembly including grooves in an inner shroud in a gas turbine engine
A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a rotating blade assembly having a plurality of blades that rotate with a turbine rotor during operation of the engine, and a stationary vane assembly having a plurality of vanes and an inner shroud. The inner shroud includes a radially outwardly facing first surface, a radially inwardly facing second surface, and a plurality of grooves extending into the second surface.
09/25/14
20140286751
Cooled turbine ring segments with intermediate pressure plenums
A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system is provided within the panel and includes an elongated intermediate plenum extending parallel to leading and trailing edges of the ring segment, and is located radially between an inner side of the panel and a hook structure extending from an outer side of the panel.
09/25/14
20140286748
Fan containment case with thermally conforming liner
A fan section of a gas turbine engine includes a fan containment case assembly includes an outer case of an aluminum alloy. The outer case extends circumferentially around an axial centerline.
09/25/14
20140286746
Compressor shroud reverse bleed holes
A gas turbine engine compressor includes a rotor defining a central axis of rotation and a plurality of blades which project into an annular compressor gas flow passage, and a shroud circumferentially surrounding the rotor and having a radially inner surface adjacent to the blade tips. Bleed holes extend through the shroud adjacent the blade tips, each of the bleed holes having an inlet end disposed in the shroud radially inner surface and an outlet end disposed in a shroud radially outer surface.


Popular terms: [SEARCH]

Gas Turbine Engine topics: Gas Turbine, Gas Turbine Engine, Downstream, High Speed, Circulation, Heat Exchanger, Attenuation, Variable Inlet Guide Vanes, Variable Inlet Guide Vane, Guide Vane, Guide Vanes, Inlet Guide Vanes

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This listing is a sample listing of patent applications related to Gas Turbine Engine for is only meant as a recent sample of applications filed, not a comprehensive history. There may be associated servicemarks and trademarks related to these patents. Please check with patent attorney if you need further assistance or plan to use for business purposes. This patent data is also published to the public by the USPTO and available for free on their website. Note that there may be alternative spellings for Gas Turbine Engine with additional patents listed. Browse our RSS directory or Search for other possible listings.
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