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TWO-STAGE COMBUSTOR FOR GAS TURBINE ENGINE

Thu, 03 Nov 2016 08:00:00 EDT

A combustor for a gas turbine engine comprises an inner annular liner wall and an outer annular liner wall cooperating to form a combustion chamber of the combustor. A first dome wall has a circumferential array of first fuel injection bores. A second dome has a circumferential array of second fuel injection bores. An intermediate wall extends between the first dome wall and the second dome wall. A first combustion stage is defined by the inner liner wall forward end, the first dome wall and the intermediate wall. A second combustion stage is defined at least by the outer liner wall forward end, the second dome wall and the intermediate wall, the first combustion stage communicating with the first fuel injection bores, the second combustion stage communicating with the second fuel injection bores.



AXIAL STAGED COMBUSTOR WITH RESTRICTED MAIN FUEL INJECTOR

Thu, 03 Nov 2016 08:00:00 EDT

A combustor for a gas turbine engine comprises a combustion chamber having a pilot injector at one end and at least one main injector spaced radially from the pilot injector. The main injector includes a fluid flow path with a plug that restricts flow at least at an interior portion of the flow path. A gas turbine engine is also disclosed.



NOZZLE FOR A GAS TURBINE COMBUSTOR

Thu, 03 Nov 2016 08:00:00 EDT

The disclosure concerns a nozzle for a gas turbine combustor, the nozzle comprising an inner channel, a swirl channel, a mixing zone and an outlet channel, wherein the nozzle extends from an inlet to an outlet, the swirl channel is disposed around the inner channel, the inner channel and the swirl channel extend from the inlet to the mixing zone, the mixing zone extends from the inner channel and the swirl channel to the outlet channel, and the outlet channel extends from the mixing zone to the outlet. A burner and a gas turbine comprising the nozzle are also described, along with a method of using the nozzle.



ONLINE ESTIMATION OF SPECIFIC GRAVITY OF GAS FUEL

Thu, 03 Nov 2016 08:00:00 EDT

A method for determining an estimate of the specific gravity of a fuel for a gas turbine engine is disclosed. The gas turbine engine includes a fuel control valve and one or more fuel injectors. The method includes determining a first estimate of the specific gravity based on an orifice flow model of the fuel control valve. The method also includes determining a second estimate of the specific gravity based on a combined orifice flow model of the one or more fuel injectors. The method further includes recursively filtering the first estimate and the second estimate to determine a third estimate of the specific gravity.



THERMAL MECHANICAL DIMPLE ARRAY FOR A COMBUSTOR WALL ASSEMBLY

Thu, 03 Nov 2016 08:00:00 EDT

A thermal mechanical dimple array for combustor liners of gas turbine engines are located at known hot spots along liner to reduce stress and minimize cracking. Such arrays have indentations in the liners at the hot spots that act to thermal mechanically flex the liner at the hot spot away from the heat source and distribute stresses such that cracking of the liner is reduced and durability is improved.



REFLECTIVE COATING FOR COMPONENTS

Thu, 03 Nov 2016 08:00:00 EDT

A component includes a substrate formed from a metallic or ceramic material and a thermal barrier coating positioned on the substrate. The component also includes a ceramic reflective coating integral with the thermal barrier coating. The reflective coating includes an arrangement of features configured to reflect at a wavelength at which peak emission from a heat source occurs. A method of making a component includes positioning a thermal barrier coating on the component and determining a wavelength emitted from a heat source. The method of making a component also includes producing an arrangement of features using a metamaterial to form a reflective coating and integrating the reflective coating with the thermal barrier coating.



HEAT TRANSFER TUBE, BOILER AND STEAM TURBINE DEVICE

Thu, 03 Nov 2016 08:00:00 EDT

A furnace wall tube which is provided in a boiler, an interior of the furnace wall tube having a supercritical pressure and a heating medium flowing through the interior, includes: a groove portion formed on an inner circumferential surface and having a spiral shape toward a tube axis direction; and a rib portion formed to protrude inward in a radial direction by the groove portion of the spiral shape. In a cross section taken along the tube axis direction, when a width of the groove portion in the tube axis direction is defined as Wg, a height of the rib portion in the radial direction is defined as Hr and a tube outer diameter is defined as D, the width Wg of the groove portion, the height Hr of the rib portion, and the tube outer diameter D satisfy Wg/(Hr·D)>0.40.



Hydraulic Drive System

Thu, 03 Nov 2016 08:00:00 EDT

A hydraulic drive system (1) including a meter-in compensator (37) and a bleed-off compensator (42) comprises a plurality of sensors (64 to 68), a controller (62), and an outlet pressure switching valve (61) The controller (62) determines whether or not the state of a wheel loader (2) which is detected based on the signals output from the sensors (64 to 68) meets a predetermined steering limiting condition. When the controller (62) determines that the state of the wheel loader (2) meets the steering limiting condition, it outputs a command signal to the outlet pressure switching valve (61). The outlet pressure switching valve (61) reduces the flow rate of the hydraulic oil flowing to steering cylinders (18L, 18R), in response to the command signal in such a manner that the flow rate becomes lower than that corresponding to the operation amount of a handle of a steering device (35).



HYDRAULIC DAMPENER FOR USE ON MINE SHOVELS

Thu, 03 Nov 2016 08:00:00 EDT

A dampener includes an external reservoir which stores hydraulic fluid due to fluid expansion caused by heat generated by fluid flow through valves that cause a drop in fluid pressure. The primary manifold controls hydraulic fluid flow within the dampener. A diverter valve communicates with the passageways between the dampener and the external reservoir. Hydraulic flow is bi-directional between the primary manifold and the accumulator. Hydraulic fluid flow is restricted when flowing from the primary manifold to the accumulator but is unrestricted when flowing from the accumulator back to the primary manifold and dampener.



METER PLATE FOR BLADE OUTER AIR SEAL

Thu, 03 Nov 2016 08:00:00 EDT

One exemplary embodiment according to this disclosure relates to a system includes a blade outer air seal (BOAS), and a meter plate. A portion of the meter plate is provided radially outward of a radially outermost surface of the BOAS.



MICROCHANNEL SOLAR ABSORBER

Thu, 03 Nov 2016 08:00:00 EDT

A solar absorber includes a panel having an outer surface configured to absorb an incident concentrated broad spectrum visible solar radiation, an inlet port, an outlet port, and a plurality of channels defined within the panel that form a flow path between the inlet port and the outlet port. The plurality of channels are sized to facilitate laminar flow of a working fluid therethrough.



Renewable Energy System and Methods for Creating Renewable Energy

Thu, 03 Nov 2016 08:00:00 EDT

A renewable energy device includes a wheel rotatably mounted on a base to spin about an axis of rotation and having a plurality of hollow, barbell-shaped fluid subassemblies fixed symmetrically about the axis. The fluid subassemblies each have a longitudinal axis radiating away from the axis of rotation, a hollow outer end defining a circular, ring-shaped, outer travel path when rotated about the axis of rotation, a hollow inner end defining a circular, ring-shaped, travel path disposed within the outer travel path when rotated about the axis of rotation, a hollow conduit fluidically connecting the outer and inner ends to define an interior cavity, and a room-temperature-boiling-point fluid disposed in the interior cavity. Inner and outer thermal variance subassemblies cover approximately half of respective ones of the inner and outer travel paths on at least one side of the wheel.



METHOD FOR CONTROLLING A PROPULSION SYSTEM

Thu, 03 Nov 2016 08:00:00 EDT

The invention relates to the field of propulsion assemblies, and in particular to rocket engines of the “expander” type, wherein at least one propulsion chamber (40) is fed with at least a first propellant by a first pump (33) coupled to a first turbine (34) that is driven by partial expansion of said first propellant upstream from said propulsion chamber (40) after passing, downstream from the first pump (33), through a heat exchanger (23) heated by said propulsion chamber (40). A method of the invention for controlling such a propulsion assembly (10) comprises the steps of determining whether there exists a risk of instability for the propulsion assembly (10), and in response to determining that said risk of instability exists, using a branch connection (28) situated between the first turbine (34) and the propulsion chamber (40) to shed a portion of said first propellant.



EXHAUST PURIFICATION SYSTEM FOR INTERNAL COMBUSTION ENGINE

Thu, 03 Nov 2016 08:00:00 EDT

Rich control is performed to hold an air-fuel ratio of an exhaust gas discharged from an engine combustion chamber temporarily richer than the stoichiometric air-fuel ratio by injecting additional fuel into a cylinder in an expansion stroke or exhaust stroke while an exhaust gas recirculation rate is made lower than a base exhaust gas recirculation rate. A variable valve timing mechanism able to change an overlap period is provided. When ending rich control (ta2), the injection of additional fuel is stopped and the overlap period (OL) is increased from a base overlap period (OLB) and held there while an EGR rate (REGR) is kept lower than a base EGR rate (REGRB) and when a delay time (dt) elapses, the EGR rate and the overlap period are reset to the base EGR rate and the base overlap period.



EXHAUST INJECTION CONTROL METHOD FOR EXHAUST GAS POST-TREATMENT DEVICE

Thu, 03 Nov 2016 08:00:00 EDT

When particulate matter (PM) has accumulated on a diesel particulate filter (DPF), multiple-injection, post injection, and exhaust pipe injection are performed such that a reduction gas is burned in a diesel oxidation catalyst (DOC) to raise the exhaust gas temperature, burn the PM accumulated on the DPF, and regenerate the DPF. A light-off performance map is prepared, in advance, by determining burning efficiency relative to the DOC temperature during the post injection and the exhaust pipe injection, both when the catalyst is fresh and when the catalyst has deteriorated. The DOC temperature suitable for the exhaust pipe injection is set from a degree of the catalyst deterioration on the basis of the light-off performance map. The multiple-injection and/or the post injection is performed when the DOC temperature is less than the set temperature, and the exhaust pipe injection is performed when the DOC temperature is equal to or greater than the set temperature.



CONTROL SYSTEM OF INTERNAL COMBUSTION ENGINE

Thu, 03 Nov 2016 08:00:00 EDT

A control system of an internal combustion engine is provided. The engine includes a turbocharger, a bypass passage, a wastegate valve, an exhaust-gas recirculation passage, and an exhaust-gas recirculation valve. The control system includes a valve closing detector and an electronic control unit. The valve closing detector is configured to detect start of an operation to close the wastegate valve. The electronic control unit is configured to start an operation to close the exhaust-gas recirculation valve when the start of the operation to close the wastegate valve is detected by the valve closing detector, such that both of the wastegate valve and the exhaust-gas recirculation valve are closed during supercharging by the turbocharger.



CONTROL CONCEPT FOR CLOSED LOOP BRAYTON CYCLE

Thu, 03 Nov 2016 08:00:00 EDT

An improved closed loop Brayton cycle for a power plant is provided that includes a heater, at least one turbine, a recuperator, at least one cooler, at least one compressor, a bypass line and a flap valve arrangement in a closed circuit in which working fluid is circulated to produce electricity via a generator. Depending upon the requirement, such as, in case of gird load disconnection, speed of a shaft-line to which the turbine, the compressor and the generator are configured is also required to be reduced without any impact on the pressure drop in the cycle. For that the non-tight flap valve arrangement is configured on each conduit between the heater and the at least one turbine in a closest possible proximity to each turbine inlet.



TURBINE ENGINE THERMAL MANAGEMENT

Thu, 03 Nov 2016 08:00:00 EDT

A gas turbine engine including core engine is provided. Air may enter the core engine through an inlet and travel through and engine air flowpath extending through the core engine, e.g., generally along an axial direction of the gas turbine engine. The gas turbine engine additionally includes a cooling air flowpath extending outwardly generally along the radial direction of the gas turbine engine. The cooling air flowpath extends between an inlet in flow communication with engine air flowpath and an outlet defined by an opening in an outer casing of the core engine. Moreover, the gas turbine engine includes a heat exchanger positioned at least partially within the outer casing the core engine with the cooling air flowpath extending over or through the heat exchanger.



BLADE/DISK DOVETAIL BACKCUT FOR BLADE/DISK STRESS REDUCTION FOR A FIRST STAGE OF A TURBOMACHINE

Thu, 03 Nov 2016 08:00:00 EDT

A turbine portion for a gas turbine includes a first stage rotor disk having a plurality of dovetail slots, and a plurality of airfoils coupled to the first stage rotor disk. Each of the plurality of airfoils includes a radial centerline and a blade dovetail mounted in a corresponding one of the plurality of dovetail slots. At least one of the plurality of dovetail slots and the blade dovetail of one of the plurality of airfoils includes a stress reducing backcut spaced between about 1.733-inches (4.402-cm) and about 2.233-inches (5.67-cm) from the radial centerline.



GRID SCALE ENERGY STORAGE SYSTEMS USING THERMAL STORAGE COUPLED WITH GAS TURBINE AIR AND STEAM INJECTION

Thu, 03 Nov 2016 08:00:00 EDT

The invention relates generally to an electrical power and storage system and more specifically to ways and methods of using a thermal storage medium as a heat source to heat compressed air from a power augmentation system for use in a gas turbine engine.



2-STAGE SLOPES THRUST BEARING PAD DESIGN AT MIST LUBRICATION CONDITION

Thu, 03 Nov 2016 08:00:00 EDT

A turbocharger is provided including a turbine wheel and a compressor wheel attached to one another by a shaft. A thrust plate includes a plate body having an aperture there through and defining a plurality of circumferentially spaced pad regions that define a land region that is perpendicular to a rotational axis of the shaft. The plate body further defines a plurality of two stage slope regions adjacent to each of the land regions. The two stage slope regions include a steep slope portion and a gradual slope portion disposed between the steep slope portion and the land regions. The rotary assembly of the turbocharger including a thrust surface that engages the pad regions. The two-stage slope regions provide improved loading capacity by the combination of better lubricant oil availability due to the steep slope region and optimized tribological performance due to the gradual slope region.



INTEGRATED TURBOSHAFT ENGINE

Thu, 03 Nov 2016 08:00:00 EDT

A system includes an engine coupled with a primary shaft that drives a first electric generator for generating electrical power via a gear subsystem, The system also includes a turbocharger assembly having at least one gas turbine engine configured for driving the primary shaft and coupled in parallel with the engine. The turbocharger assembly includes multiple compressors configured to provide a flow of compressed fluid into both the engine and the at least one gas turbine engine and multiple turbines configured to utilize exhausts from both the engine and the one gas turbine for driving the primary shaft. Further, the system includes a controller configured to operate a plurality of valves for controlling optimal intake fluid pressure into the engine and the turbocharger assembly and fuel injections into the engine and the at least one gas turbine engine.



A TURBOCOMPOUND ASSEMBLY, IN PARTICULAR IN THE FIELD OF INDUSTRIAL VEHICLES

Thu, 03 Nov 2016 08:00:00 EDT

A turbocompound assembly, in particular in the field of industrial vehicles, comprising a power turbine paired with the engine crankshaft, wherein the paring is carried out through said assembly, wherein the assembly comprises a differential arrangement, wherein the pinion of the power turbine defines a sun gear meshing into two or more planet gears, which in turn mesh into a ring gear coupled with the engine crankshaft.



ENGINE SYSTEM AND CONTROLLER, CONTROL SYSTEM AND CONTROL METHOD FOR ENGINE SYSTEM

Thu, 03 Nov 2016 08:00:00 EDT

A controller for an engine system includes an exhaust-driven turbocharger including a compressor and a turbine, an exhaust gas recirculation unit configured to recirculate exhaust gas from a downstream portion of the turbine in an exhaust gas passage to an upstream portion of the compressor in an intake gas passage, and a cooling unit configured to cool the turbine, the controller includes an electronic control unit. The electronic control unit is configured to set a degree of cooling of the turbine based on a predetermined condition in which a gas temperature at an outlet portion of the compressor is higher than a predetermined temperature and the recirculating of exhaust gas is performed, and set a higher degree of cooling of the turbine when the predetermined condition is satisfied compared to a degree of cooling of the turbine when the predetermined condition is not satisfied.



INTERNAL COMBUSTION ENGINE COUPLED TURBOCHARGER WITH AN INFINITELY VARIABLE TRANSMISSION

Thu, 03 Nov 2016 08:00:00 EDT

A turbocharger for use with an internal combustion engine is provided. The turbocharger comprises a differential device having a carrier portion, a compressor portion, and a turbine portion. The compressor portion is in driving engagement with a first portion of the differential device. The turbine portion is in driving engagement with a second portion of the differential device. The carrier portion of the differential device is in driving engagement with an infinitely variable transmission. The infinitely variable transmission is in driving engagement with the internal combustion engine. The turbocharger is simply controlled, reduces turbo lag, decreases a boost threshold of the turbocharger, and increases an efficiency of the internal combustion engine.



ENGINE SYSTEM WITH INTAKE AIR-SUPPLY TURBINE AND MOTOR-DRIVEN COMPRESSOR

Thu, 03 Nov 2016 08:00:00 EDT

A method for operation of an engine. The method includes during a first operating condition, permitting intake airflow through an intake air-supply turbine positioned upstream of a cylinder to drive a generator, the generator coupled to an energy storage device, and inhibiting intake airflow through a motor-driven compressor arranged in parallel flow arrangement with the intake air-supply turbine, the motor driven compressor coupled to a motor coupled to the energy storage device. The method further includes during a second operating condition, permitting intake airflow through the motor-driven compressor while the motor-driven compressor receives rotation input from the motor, and inhibiting intake airflow through the intake air-supply turbine.



MOUNTING CONFIGURATION FOR A HEAT DUCT IN AN ELECTRIC GENERATOR

Thu, 03 Nov 2016 08:00:00 EDT

An exhaust pipe mounted heat duct in an electrical generator includes an exhaust pipe coupleable to an internal combustion engine of the electrical generator to receive exhaust therefrom, the exhaust pipe having a first support member and a second support member extending outwards from the exhaust pipe. The exhaust pipe mounted heat duct also includes a heat duct assembly comprising a first component and a second component, the first component mounted to the first support member and a second component mounted to the second support member, the first component coupled to the second component to substantially surround the exhaust pipe.



MIXER WITH INTEGRATED DOSER CONE

Thu, 03 Nov 2016 08:00:00 EDT

A mixer for a vehicle exhaust system includes an outer housing having an upstream end and a downstream end. An upstream baffle has an inlet opening configured to receive exhaust gas and is mounted at the upstream end of the outer housing. A downstream baffle has an outlet opening configured to conduct exhaust gases to a downstream exhaust component and is mounted at the downstream end of the outer housing. A doser opening is formed within the outer housing at a location between the upstream and downstream baffles. A cone has a narrow end with an inlet opening and a wide end with an outlet opening. A tapered body portion extends from the narrow end to the wide end, with the cone being aligned with the doser opening. An extension portion extends outwardly from the wide end of the cone and provides a wall that surrounds the outlet opening.



CATALYTIC CONVERTER AND METHOD FOR DESIGNING THE CATALYTIC CONVERTER

Thu, 03 Nov 2016 08:00:00 EDT

A catalytic converter capable of uniformizing an exhaust gas flow velocity to realize uniform temperature distribution and improved purification performance, and a method for designing the catalytic converter. A catalytic converter includes a catalyst base composed of an inner base material part having inner cell holes and an outer base material part having outer cell holes, and an exhaust pipe composed of an upstream-side pipe, a catalyst housing pipe and a downstream-side pipe. In the catalytic converter, a flow path cross-sectional area of the upstream-side pipe defined as S1, a cross-sectional area of the inner base material part defined as S2, a cross-sectional area of the catalyst base defined as S3, a hydraulic diameter of the inner cell holes defined as d1 and a hydraulic diameter of the outer cell holes defined as d2, satisfy the relationship, S1≦S2≦S3(−0.2242 (d12/d22)2+0.1141 (d12/d22)+0.617).



FULL ROTATION MIXER

Thu, 03 Nov 2016 08:00:00 EDT

A mixer for a vehicle exhaust system includes an upstream baffle with at least one inlet opening configured to receive engine exhaust gas, a downstream baffle with at least one outlet opening configured to conduct engine exhaust gases to a downstream exhaust component, and an outer peripheral wall surrounding the upstream and downstream baffles and defining a mixer central axis. An intermediate plate is positioned between the upstream and downstream baffles to block direct flow from the inlet opening to the outlet opening. The intermediate plate initiates a rotational flow path that directs exhaust gases exiting the inlet opening through a rotation of more than 360 degrees about the mixer central axis before exiting the outlet opening.



SYSTEM AND METHODS FOR PURGING RESIDUAL EXHAUST AND UNCOMBUSTED FUEL TO AN EXHAUST CATALYST

Thu, 03 Nov 2016 08:00:00 EDT

A method for an engine is provided. Following an engine-off event, engine cylinders are sequentially positioned with an intake valve open and an exhaust valve open. The contents of the engine cylinder are then purged to an exhaust catalyst. In this way, existing vehicle hardware may be used to evacuate residual hydrocarbons and uncombusted fuel to the exhaust catalyst, provided the catalyst remains above the light-off temperature.



ENGINE SYSTEM

Thu, 03 Nov 2016 08:00:00 EDT

An engine system is provided. The engine system includes a first engine adapted to generate a first exhaust flow. The engine system includes a first aftertreatment unit associated with the first engine. The first aftertreatment unit receives at least a portion of the first exhaust flow therein. The engine system includes a second engine adapted to generate a second exhaust flow. The engine system also includes a second aftertreatment unit associated with the second engine. The second aftertreatment unit receives the second exhaust flow therein. The engine system further includes a distribution unit coupled to the first aftertreatment unit and the second aftertreatment unit. The distribution unit is adapted to selectively bypass a remaining portion of the first exhaust flow to the second aftertreatment unit. The remaining portion of the first exhaust flow is adapted to introduce an amount of unburned hydrocarbon (CxH2x) in to the second aftertreatment unit.



ENGINE DEVICE

Thu, 03 Nov 2016 08:00:00 EDT

An engine includes an exhaust gas purification device for treating exhaust gas. The exhaust gas purification device is arranged on the upper surface side of the engine Regarding structure in which an exhaust throttle device is provided in an installation portion of an exhaust manifold on one side of the engine, the exhaust throttle device is inclined and disposed with respect to the right side surface of the engine in a plan view, and a gap is formed between the right side surface of a head cover and the inner side surface of the exhaust throttle device.



METHOD OF RECYCLING ENERGY IN PROCESS OF BUTADIENE PREPARATION (As Amended)

Thu, 03 Nov 2016 08:00:00 EDT

Provided is a method for recycling energy in process of butadiene preparation, which includes, in the process of preparing butadiene using oxidative dehydrogenation reaction, steps of: a) supplying part or all of a light gas discharged from a solvent absorption tower to a turbine to produce electricity; b) passing the light gas passed through the turbine through one or more device units provided with a heat exchanger; and c) feeding the light gas passed through the device units provided with the heat exchanger into a reactor, according to which more economical butadiene preparation process is provided, by reducing net energy value required in process of butadiene preparation using oxidative dehydrogenation reaction.



DEVICE AND METHOD FOR CONVERTING HEAT INTO MECHANICAL ENERGY

Thu, 03 Nov 2016 08:00:00 EDT

A device for converting heat into mechanical energy is disclosed. The device includes a channel flow boiler having at least one channel adapted to heat a working fluid for generating a liquid-gas mixture; an expansion device adapted to expand the liquid-gas mixture; and a movable element arranged such that the expanding liquid-gas mixture at least partially converts an internal and/or kinetic energy of the liquid-gas mixture into mechanical energy associated with the movable element; wherein the channel flow boiler and/or the expansion device is adapted to supply heat to the liquid-gas mixture.



METHOD FOR ENHANCED COLD STEAM TURBINE START IN A SUPPLEMENTARY FIRED MULTI GAS TURBINE COMBINED CYCLE PLANT

Thu, 03 Nov 2016 08:00:00 EDT

A method for enhanced cold (or warm) steam turbine start in a supplementary fired multi-gas turbine combined cycle plant is disclosed. Boiler supplementary firing, which is normally used to increase steam flow when the plant gas turbine is at maximum load, is used to augment steam production with a partly loaded, temperature matched gas turbine. This is done to satisfy minimum required steam flow for a cold (or warm) steam turbine start. Lighting the supplementary firing burners in the heat recovery steam generator/boiler and setting them at a minimum or low heat load serves to add enough steam, at the proper temperature, to insure a successful cold or warm steam turbine start when the gas turbine load and related steam production capacity from the gas turbine exhaust flow are limited by the need to match the required steam temperature and/or maintain low gas turbine exhaust emissions.



SYSTEM AND METHOD FOR REGULATING PRESSURE FOR A TURBOMACHINE

Thu, 03 Nov 2016 08:00:00 EDT

A pressure regulating system which is an arrangement with a turbo machine for example a nuclear steam turbine. Main lubricant oil pump supply fluid for example lubricant oil to the nuclear steam turbine passes through a cooler and via filter through a main supply line. The pressure regulating system is connected to the main supply line through an actuating line. Based on requirement of the fluid excessive fluid can be diverted through the actuating line to the pressure regulating system and from there to oil tank. In oil tank an auxiliary lubricant oil pump is provided to supplement the supply of the lubricant oil to the nuclear steam turbine. An emergency lubricant oil pump has also been provided to supply the lubricant oil to the nuclear steam turbine in case when regular supply is not working.



VARIABLE VANE POSITIONING APPARATUS FOR A GAS TURBINE ENGINE

Thu, 03 Nov 2016 08:00:00 EDT

A variable vane assembly for a gas turbine engine includes at least one synchronization ring, a plurality of variable vanes connected to the synchronization ring, a plurality of torque boxes disposed circumferentially about the synchronization ring, a drive ring coupled to each of the torque boxes such that the drive ring causes an approximately identical torque to be applied to the synchronization ring from the torque boxes simultaneously, and an actuator coupled to one of the plurality of torque boxes and operable to drive the drive ring through the torque box.



BLADE/DISK DOVETAIL BACKCUT FOR BLADE/DISK STRESS REDUCTION FOR A SECOND STAGE OF A TURBOMACHINE

Thu, 03 Nov 2016 08:00:00 EDT

A turbine portion for a gas turbine includes a second stage rotor disk having a forward surface, an aft surface, and a plurality of dovetail slots. Each of the plurality of dovetail slots includes an upstream side and a downstream side. A plurality of airfoils is coupled to the second stage rotor disk. Each of the plurality of airfoils includes a radial centerline and a blade dovetail having a dovetail skew axis mounted in a corresponding one of the plurality of dovetail slots. At least one of the plurality of dovetail slots and the blade dovetail of at least one of the plurality of airfoils includes at least one stress reducing backcut spaced at least between about 1.446-inches (3.673-cm) and about 3.200-inches (8.13-cm) from a plane intersecting the radial centerline. The plane is substantially normal to the dovetail skew axis.



ROTOR BLADE HAVING A FLARED TIP

Thu, 03 Nov 2016 08:00:00 EDT

A rotor blade includes an airfoil having a blade tip and a tip cavity formed at the blade tip. The tip cavity includes a tip cap that is recessed radially inwardly from the tip and surrounded continuously by pressure and suction side walls of the airfoil. The tip cap further includes an aperture that extends through the tip cap and provides for fluid communication between an internal cavity defined within the airfoil and the tip cavity. An exhaust port provides for fluid communication out the tip cavity through one of the pressure side wall, the suction side wall or the trailing edge. A portion of at least one of the suction side wall and the pressure side wall that defines the tip cavity extends obliquely outwardly from the tip cavity with respect to a radial direction.



TURBINE AIRFOIL TURBULATOR ARRANGEMENT

Thu, 03 Nov 2016 08:00:00 EDT

A turbine airfoil includes a leading edge and a trailing edge. Also included is a cooling channel extending in a radial direction and tapering inwardly toward the trailing edge, the cooling channel at least partially defined by a pressure side face and a suction side face. Further included is a first plurality of turbulators protruding from one of the pressure side face and the suction side face to define a first height, the first plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other. Yet further included is a second plurality of turbulators protruding from one of the pressure side face and the suction side face to define a second height that is less than the first height, the second plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other.



GAS TURBINE ENGINE COMPRESSOR ROTOR VAPORIZATION COOLING

Thu, 03 Nov 2016 08:00:00 EDT

A gas turbine engine rotor includes a rotor that provides a cooling cavity. The cooling cavity has a first chamber and a second chamber that are fluidly connected to one another by a passageway. At least one of the first and second rotor portions is configured to support a blade that is fluidly isolated from the cavity. A phase change material is arranged in the cavity. The phase change material is configured to be arranged in the first chamber in a first state and in the second chamber in the second state. The passageway is configured to carry the phase change material between the second and first chambers once changed between the first and second states.



HYDRAULIC SYSTEM FOR DRIVING A VIBRATORY MECHANISM

Thu, 03 Nov 2016 08:00:00 EDT

A hydraulic system for driving a vibratory mechanism of a compaction roller includes at least one hydraulic motor connectable to a vibratory mechanism and a first hydraulic pump fluidly connected to the at least one hydraulic motor and arranged for supplying pressurised hydraulic fluid to the at least one hydraulic motor. The hydraulic system further includes a second hydraulic pump fluidly connected to the at least one hydraulic motor and arranged for supplying pressurised hydraulic fluid to the at least one hydraulic motor. A corresponding method for controlling a vibratory mechanism of a compaction roller is also provided.



COOLED COOLING AIR SYSTEM FOR A GAS TURBINE

Thu, 03 Nov 2016 08:00:00 EDT

In an aircraft including a gas turbine engine having a compressor including a compressor booster, a turbine, and a nacelle, a system for cooling compressor discharge air provided to the turbine to cool the turbine includes a heat exchanger provided in a nacelle compartment of the gas turbine engine configured to cool the compressor discharge air by exchanging heat from the compressor discharge air to a cooling fluid; and a cooling fluid circuit configured to circulate cooling fluid through the heat exchanger and a heat sink, wherein the heat sink is at least one of an inlet of the nacelle compartment, an inlet of the compressor booster, or outlet guide vanes of the gas turbine engine.