Solar Turbines Inc. Patent applications |
Patent application number | Title | Published |
20150292362 | METHOD OF REMANUFACTURING A MACHINE COMPONENT - A method is provided for remanufacturing a machine component having multiple holes. The holes are provided to match in alignment with corresponding holes of an adjacent component in a machine assembly. First and second sets of holes are selected from the holes of the machine component on the basis of being located within first and second limits of positional tolerance with respect to corresponding holes of the adjacent component. Each hole from the first set of holes is bored to define openings in axial alignment with holes of the adjacent component. Each hole from the second set of holes is bored to an enlarged diameter and then plugged with a deformable insert. Each of these inserts is then drilled to define openings in axial alignment with holes of the adjacent component. | 10-15-2015 |
20150266099 | FIXTURE FOR VERTICAL LATHE MACHINE - A vertical lathe fixture is provided. The vertical lathe fixture includes a main body and a sub-plate. The sub-plate includes a top surface and a bottom surface defining a thickness of the sub-plate therebetween. The top surface of the sub-plate is configured to be coupled to the main body and the bottom surface is configured to be coupled to a chuck of a vertical lathe machine. The sub-plate also includes a center pad provided at a center of the top surface. The center pad is configured to centrally align the sub-plate with respect to the main body. The sub-plate further includes a plurality of receiving pads provided in a radial pattern on the top surface and in relation to the center pad. The receiving pads are configured to hold the main body in a stationary position with respect to the sub-plate during rotation of the vertical lathe fixture. | 09-24-2015 |
20150211901 | COVER ASSEMBLY - A cover is provided for a sensor port. The cover includes an open end disposed proximal to the sensor port. The cover further includes a closed end disposed in opposing relation to the open end. The cover further includes a passage laterally defined between the open end and the closed end. The passage is disposed proximal to the open end and is configured to allow fluid communication of the sensor port with atmosphere. | 07-30-2015 |
20150211379 | SYSTEM FOR MONITORING HEALTH OF A SEAL - A system for monitoring a health of one or more seals includes a flow control valve, and a controller. The flow control valve is located upstream of the seal and disposed in fluid communication therewith. The flow control valve is configured to maintain a pre-determined fluid pressure between the flow control valve and the seal. The controller is communicably coupled to the flow control valve. The controller is configured to receive a position of the flow control valve, and determine the health of the seal based on the received position of the flow control valve. | 07-30-2015 |
20150116934 | POWER SYSTEM ENCLOSURE - A power system enclosure is provided. The power system enclosure includes a housing accommodating a power source. The power system enclosure further includes an enclosure inlet connected to the housing to allow entry of an intake fluid into the housing. An enclosure exhaust is connected to the housing to route fluid from the housing. Further, a relief damper is disposed in the enclosure exhaust. At least a portion of the relief damper is configured to open when a pressure within the housing exceeds a predetermined threshold value. | 04-30-2015 |
20150101780 | HEAT EXCHANGER FOR POWER SYSTEM - The present disclosure provides a heat exchanger for a power system. The heat exchanger includes a housing. The housing includes a first side and a second side. The second side is configured to be received in a receptacle of a power system enclosure. The heat exchanger includes at-least one heat exchange tube supported between one or more of side walls of the housing. The heat exchanger includes a screen attached to the second side of the housing. The screen includes at-least one inlet opening for the heat exchange tube, and at-least one outlet opening for the heat exchange tube. The heat exchanger further includes a flange attached to the first side of the housing wherein the flange is configured to be removably attached to an outer surface around the receptacle of the power system enclosure. | 04-16-2015 |
20150078689 | JOURNAL BEARING - A journal bearing is provided for mounting a gear component thereon and for reducing vibrations from operation of the gear component. The journal bearing includes a cylindrical body having two recessed portions defined thereon. The journal bearing further includes a primary passage extending longitudinally through the cylindrical body, and two secondary passages radially extending from the primary passage to the recessed portions. An angle of the two secondary passages with respect to a horizontal plane of the journal bearing is based on at least one of a magnitude and direction of a pre-determined bearing load, a rotational speed of the gear component, a clearance between the journal bearing and the gear component, oil properties, wherein the oil is introduced between the journal bearing and the gear component, and one or more system stability parameters. | 03-19-2015 |
20150032232 | SYSTEM AND METHOD FOR SERVER REDUNDANCY - A system is provided. The system includes a plurality of nodes. One of the plurality of nodes is designated as a server node, and the others of the plurality of nodes are designated as Human Machine Interface (HMI) client nodes. The designated server node comprises a network interface configured to communicate with a Programmable Logic Controller (PLC) either directly or through a network switch. Each of the designated HMI client nodes includes a network interface configured to communicate with the designated server node through one or more of a network switch, and another designated HMI client node. Also, the each of the designated HMI client nodes includes a failover module configured to detect a failure of the designated server node and designate a new server node from among the designated HMI client nodes based on detecting the failure of the designated server node. | 01-29-2015 |
20140356150 | GRAIN MICROSTRUCTURE IN DAMPERS OF GAS TURBINE ENGINE - A damper for a gas turbine engine is provided. The damper comprises a first portion, a second portion, and a surface. The second portion angularly extends from the first portion to define an interior corner therebetween. The surface bounds the first portion, the second portion, and the interior corner. The damper further comprises a grain composition containing columnar grains and equiaxed grains. The equiaxed grains are disposed adjacent to the surface such that a volume of the columnar grains is less than a volume of the equiaxed grains in the grain composition. | 12-04-2014 |
20140291455 | FLUID LINE CLAMP - A fluid line clamp includes one or more blocks with holes for receiving fluid lines therein. The fluid line clamp further includes a first backing plate, a second backing plate, and a shielding plate. The first and second backing plates are spaced apart from each other to receive the blocks therebetween. The shielding plate is disposed at a distance from the blocks and includes an inner surface, and an outer surface. The inner surface of the shielding plate is rigidly attached to the backing plates. The outer surface of the shielding plate is configured to rigidly attach to a hot body of a machine. | 10-02-2014 |
20140169959 | SEALING SYSTEM FOR FLANGED JOINT - A sealing system is provided for a flanged joint. The sealing system includes a split seal and a spring. The split seal includes a radial outer surface, an axial outer surface, and a chamfered surface inclined with respect to the radial outer surface and the axial outer surface. The spring is disposed in urging contact with the chamfered surface and configured to apply an axial force, and a radial force on the axial outer surface, and the radial outer surface respectively. | 06-19-2014 |
20140137565 | COMBINATION AIR ASSIST AND PILOT GASEOUS FUEL CIRCUIT - When starting a dual fuel turbine engine on liquid fuel, a flow of air assist into a combined pilot gaseous fuel and air assist tube is supplied. The velocity of the flow of air assist is increased as it is expelled through an outlet of the tube. The flow of air assist is directed into a first end of a pilot injector barrel. Additional air is drawn into the first end of the pilot injector barrel from an enclosure containing both the first end of the pilot injector barrel and the tube outlet. Liquid pilot fuel is supplied at a second end of the pilot injector barrel, and this fuel is atomized by the flow of the air assist and additional air. The atomized pilot liquid fuel may then be combusted, | 05-22-2014 |
20140017989 | POWER SYSTEM ENCLOSURE - A power system enclosure is provided. The power system enclosure includes a box, and a ventilation system. The ventilation system includes an enclosure inlet, and an enclosure exhaust. The enclosure inlet and the enclosure exhaust are disposed outside the box. The enclosure inlet is connected to the box to allow entry of air. The enclosure exhaust includes an enclosure exhaust, and one or more gas detectors. The exhaust duct is connected to the box to route gases from the box. The gas detectors are disposed in the enclosure exhaust to detect and generate a signal indicative of a presence of carbon monoxide in the gases. | 01-16-2014 |
20140013767 | BAFFLE ASSEMBLY FOR BLEED AIR SYSTEM OF GAS TURBINE ENGINE - A baffle assembly for a housing of a combustor system of a gas turbine engine is provided. The baffle assembly includes a baffle retainer and a baffle. The baffle retainer includes a retainer tube and a collar. The retainer tube is received within a bleed port of the housing. The collar is defined at an upper end of the retainer tube and is configured to rest against the housing. The baffle includes a baffle tube rigidly attached to an inner surface of the retainer tube. | 01-16-2014 |
20130323052 | RETAINING RING - A retaining ring assembly for a gas turbine engine. The retaining ring assembly may include a discontinuous ring member having first and second portions of reduced cross-sectional area. The second portion may be configured to overlap the first portion. Further, the first and second portions may each include a transition portion configured to transition from a main portion of the ring member to a respective one of the first and second portions. Also, each transition portion may include a rounded fillet extending along the length of the transition portion. | 12-05-2013 |
20130306830 | ENGINE SKID ASSEMBLY - A skid assembly for a gas turbine engine includes a first segment having a first engine support structure and a second segment having one or more second engine support structures. The first engine support structure configured to support a gas producer group of the gas turbine engine and the one or more second engine support structures configured to support a turbine power group of the gas turbine engine. A replaceable member removably attached to the first segment and the second segment. | 11-21-2013 |
20130283799 | RESONANCE DAMPER FOR DAMPING ACOUSTIC OSCILLATIONS FROM COMBUSTOR - A resonance damper for damping acoustic oscillations within a combustor housing of a gas turbine engine is provided. The resonance damper includes a container, an opening, and a pipe. The container is configured to be attached to an interior wall of the combustor housing and has a cavity. The opening is provided on the container. The pipe is rigidly connected to the opening to define the resonance damper with the cavity. | 10-31-2013 |
20130259703 | TURBINE NOZZLE - A nozzle arrangement for a gas turbine engine comprising a first housing member and a second housing member. The nozzle arrangement may further include a first nozzle and a second nozzle. Each of the first nozzle and second nozzle may extend between the first housing member and the second housing member so as to form a doublet. A plurality of cooling apertures may be arranged on at least one of the first nozzle, the second nozzle, the first housing member, or the second housing member so as to provide a different degree of first order cooling across the doublet. | 10-03-2013 |
20130255260 | RESONANCE DAMPER FOR DAMPING ACOUSTIC OSCILLATIONS FROM COMBUSTOR - A resonance damper for damping acoustic oscillations within a combustor housing of a gas turbine engine is provided. The resonance damper comprises a baffle plate, multiple openings, and multiple tubes. The baffle plate is configured to be attached to an interior wall of the combustor housing. The baffle plate defines a cavity with the interior wall of the combustor housing. The openings are provided on the baffle plate. Each of the tubes is received within each of the openings to define the resonance damper with the cavity. | 10-03-2013 |
20130224052 | METHOD OF MANUFACTURING A HOUSING - A method of manufacturing a plurality of housings. The method may include maintaining an inventory of initial products. Each of the initial products may include a central hollow body extending along a longitudinal axis and monolithically formed with at least one of a suction passage and a discharge passage. Each of the products may have a same initial length. The method may further include receiving a first order for a first housing having a first length and machining a first product to the first length to form the first housing. Also, the method may include receiving a second order for a second housing having a second length and machining a second product to the second length to form the second housing. The first length and the second length may be different. | 08-29-2013 |
20130202192 | APPARATUS AND METHOD FOR OPTICALLY MEASURING CREEP - A method of measuring creep strain in a gas turbine engine component, where at least a portion of the component has a material disposed thereon, and where the material has a plurality of markings providing a visually distinct pattern. The method may include capturing an image of at least a portion of the markings after an operational period of the gas turbine engine, and determining creep strain information of the component. The creep strain information may be determined by correlating the image captured after the operational period to an image captured before the operational period. | 08-08-2013 |
20130192237 | FUEL INJECTOR SYSTEM WITH FLUIDIC OSCILLATOR - A fuel injector system for a turbine engine may include a center body disposed about a longitudinal axis and a barrel housing positioned radially outwardly from the center body to define an annular passageway therebetween. The fuel injector may also include one or more fuel discharge outlets positioned in the annular passageway. The one or more fuel discharge outlets may be configured to discharge pulses of a fuel into the annular passageway. The fuel injector may further include one or more fluidic oscillators fluidly coupled to the one or more fuel discharge outlets. The one or more fluidic oscillators may be configured to induce pulsations in the fuel discharged by the one or more fuel discharge outlets. | 08-01-2013 |
20130152594 | GAS TURBINE AND FUEL INJECTOR FOR THE SAME - A fuel injector for a gas turbine engine includes an injector housing having a central cavity configured to fluidly couple with a combustor of the gas turbine engine. The fuel injector may include a fuel nozzle at the upstream end of the central cavity. The fuel nozzle may be configured to direct a first fuel into the central cavity. The fuel injector may also include an annular air inlet disposed circumferentially about the fuel nozzle at the upstream end of the central cavity, and an annular air discharge outlet circumferentially disposed about the exit opening of the central cavity. The fuel injector may further include an annular fuel discharge outlet circumferentially disposed about the air discharge outlet. The fuel discharge outlet may be configured to discharge a second fuel into the combustor circumferentially around the air discharge outlet. | 06-20-2013 |
20130152593 | GAS TURBINE AND FUEL INJECTOR FOR THE SAME - A fuel injector for a gas turbine engine may include an injector housing having a central cavity configured to be fluidly coupled to a combustor of the turbine engine. The central cavity may also be configured to direct a first fuel into the combustor substantially unmixed with air. The fuel injector may also include an annular air discharge outlet circumferentially disposed about the downstream end of the central cavity. The air discharge outlet may be configured to discharge compressed air into the combustor circumferentially about the first fuel from the central cavity. The fuel injector may also include an annular fuel discharge outlet circumferentially disposed about the air discharge outlet at the downstream end. The fuel discharge outlet may be configured to discharge a second fuel into the combustor circumferentially about the compressed air from the air discharge outlet. | 06-20-2013 |
20130125548 | FLOW CONDITIONER FOR FUEL INJECTOR FOR COMBUSTOR AND METHOD FOR LOW-NOx COMBUSTOR - An injector for a gas turbine combustor including a catalyst coated surface forming a passage for feed gas flow and a channel for oxidant gas flow establishing an axial gas flow through a flow conditioner disposed at least partially within an inner wall of the injector. The flow conditioner includes a length with an interior passage opening into upstream and downstream ends for passage of the axial gas flow. An interior diameter of the interior passage smoothly reduces and then increases from upstream to downstream ends. | 05-23-2013 |
20130000128 | Cutting tool for cable with a metal shield - A tool for cutting and slitting the shielding of an electrical cable includes a cutting platform configured to engage the shield of the cable. A driven cutting blade is mounted for movement past the cutting platform into the shield. A fixture is provided for supporting the cable in a desired orientation during a cutting or slitting operation. The fixture includes a first cable support that defines a ring cut plane and a second cable support that defines a slitting plane | 01-03-2013 |
20120324900 | PHASE AND AMPLITUDE MATCHED FUEL INJECTOR - A fuel injector for a turbine engine may include a body member disposed about a longitudinal axis, and a barrel member located radially outwardly from the body member. The fuel injector may also include an annular passageway extending between the body member and the barrel member from a first end to a second end. The first end may be configured to be fluidly coupled to a compressor of the turbine engine and the second end may be configured to be fluidly coupled to a combustor of the turbine engine. The fuel injector may also include a perforated plate positioned proximate the first end of the passageway. The perforated plate may be configured to direct compressed air into the annular passageway with a first pressure drop. The fuel injector may also include at least one fuel discharge orifice positioned downstream of the perforated plate. The at least one fuel discharge orifice may be configured to discharge a fuel into the annular passageway with a second pressure drop. The second pressure drop may have a value between about the first pressure drop and about 1.75 times the first pressure drop. | 12-27-2012 |
20120006411 | FLUID COMPRESSION SYSTEM - A fluid compression system is disclosed. The fluid compression system may include a first compressor disposed in a first fluid conduit, a first valve disposed in the first fluid conduit upstream of the first compressor, a second valve disposed in the first fluid conduit downstream of the first compressor, a second compressor in fluid communication with the first compressor and configured to selectively pump fluid from the first compressor. | 01-12-2012 |