Entries |
Document | Title | Date |
20080276595 | Gas Turbine Protection Device - A gas turbine protection apparatus, which can output a gas turbine protection signal only when a combustor is abnormal, without increasing the number of temperature sensors such as thermocouples. For this purpose, a BPT deviation change amount large automatic stop signal is outputted when a BPT deviation change amount of any of the thermocouples exceeds a BPT deviation change amount large set value, and a BPT deviation change amount large signal is outputted from a determining section ( | 11-13-2008 |
20080289315 | SYSTEM FOR DISSIPATING ENERGY IN THE EVENT OF A TURBINE SHAFT BREAKING IN A GAS TURBINE ENGINE - The present invention relates to a device for, in a gas turbine engine, braking a turbine comprising a rotor, having at least one disk ( | 11-27-2008 |
20090064655 | Actuator Arrangement and a Method of Operating an Actuator - Interruption in supervisory position control signals can cause problems with respect to actuators which upon loss of such control signals for the actuator will generally slew to a fixed idle position. In such circumstances a machine such as a gas turbine engine in which an actuator is associated will not sustain performance even though there is continued local power supply to the actuator. By utilising a local controller which stores actuator response profiles for certain machine status stages through perturbation or marginal activation of the actuator an appropriate actuator response profile can be chosen and therefore sustaining control signals presented to the actuator to maintain machine operation. | 03-12-2009 |
20090126336 | SYSTEM PROVIDING BRAKING IN A GAS TURBINE ENGINE IN THE EVENT OF THE TURBINE SHAFT BREAKING - The present invention relates to a device for, in a gas turbine engine, braking a turbine comprising a rotor driving a shaft capable of rotating with respect to a stator in the event of said shaft breaking. The device is one which comprises a first braking member ( | 05-21-2009 |
20090241508 | FUEL NOZZLE TO WITHSTAND A FLAMEHOLDING INCIDENT AND A METHOD OF FORMING THE SAME - A nozzle is provided and includes an outer annulus defined by an exterior wall and an interior wall and including air inlets through which air flows to a fuel mixing zone and a combustion zone, an inner annulus disposed within the interior wall and including a fuel volume into which fuel is fed to a distal end thereof, which is adjacent to and isolated from the combustion zone and an airflow line, disposed between the fuel volume and the interior wall, through which air flows to the combustion zone with the airflow line and the combustion zone isolated from the fuel volume, and a fuse configured to melt during a flameholding incident and to form a breach through which fuel flows from the fuel volume, bypassing the fuel mixing zone, to a fuel burning zone downstream from the fuel mixing zone. | 10-01-2009 |
20090277153 | Composite component - A composite component such as a fan casing liner panel for a gas turbine engine comprises an abradable layer and a layer. The layer is provided with a septum layer, to which the abradable layer is bonded. The septum layer is perforated by holes, which enable air to be extracted from the region between the septum layer and the abradable layer during the process of bonding the components together, for example by a vacuum bonding process. | 11-12-2009 |
20090293447 | Method for the provision of fire protection for titanium components of an aircraft gas turbine and titanium components for an aircraft gas turbine - A method provides fire protection for titanium components of an aircraft gas turbine. To enable the use of titanium components on aircraft gas turbines without the risk of titanium fire, a surface-near, nonflammable, intermetallic phase of titanium and at least one further metal, selected from the group of aluminum, nickel, vanadium and chromium, including combinations thereof, is produced in the surface of the component by a diffusion process. | 12-03-2009 |
20090301055 | Gas Turbine Engine Systems and Methods Involving Vibration Monitoring - Gas turbine engine systems and methods involving vibration monitoring are provided. In this regard, a representative vibration monitoring method for a gas turbine engine includes: receiving information corresponding to detected vibrations of a gas turbine engine; isolating vibrations attributable to rotating blades of the gas turbine engine from the detected vibrations; and comparing the isolated vibrations to information corresponding to predicted vibrations of the rotating blades. | 12-10-2009 |
20090313966 | METHOD AND APPARATUS FOR DETERMINING FAILURES OF GAS SHUTOFF VALVES IN GAS TURBINES - A controller for a turbine power plant that is operable to identify a failure condition and measure a shutoff valve performance. | 12-24-2009 |
20100077721 | COMPOSITE FAN CASE WITH INTEGRAL CONTAINMENT ZONE - A turbofan engine which has a composite fan case surrounding a fan with a plurality of fan blades is disclosed. The composite fan case includes a containment zone having an inner fabric layer composed of resin-impregnated fibres substantially uni-axially oriented in a common angular direction corresponding to a blade release angle of the fan blades. The fan case also includes a composite outer shell and an energy absorbing core disposed radially between the inner fabric layer and the composite outer shell. The energy absorbing core includes non resin impregnated multidirectional fibres. | 04-01-2010 |
20100101205 | DEVICE FOR DEFLECTION AND RETENTION OF AIRCRAFT ENGINE DEBRIS - A protective device for treating at least one piece of debris that comes from a source of an aircraft, in particular a compressor stage or a turbine stage of an aircraft power plant, and to prevent it from reaching a target of the aircraft, characterized in that it has a geometry and a position relative to the source and to the target that make it possible to deflect the debris with the most energy so as to protect the target that is placed in a predefined protected zone. | 04-29-2010 |
20100170217 | SYSTEMS AND METHODS FOR DETECTING A FLAME IN A FUEL NOZZLE OF A GAS TURBINE - A system may detect a flame about a fuel nozzle of a gas turbine. The gas turbine may have a compressor and a combustor. The system may include a first pressure sensor, a second pressure sensor, and a transducer. The first pressure sensor may detect a first pressure upstream of the fuel nozzle. The second pressure sensor may detect a second pressure downstream of the fuel nozzle. The transducer may be operable to detect a pressure difference between the first pressure sensor and the second pressure sensor. | 07-08-2010 |
20100199628 | Interlocking Retention Strip - An impingement shield assembly for a turbine includes a first impingement shield portion and a second impingement shield joined to the first impingement shield portion. The assembly also includes a first connection portion formed on the first impingement shield portion, a second connection portion formed on the first impingement shield portion and first and second wedge weld portions that mate with and hold the first and a second connection portions in a fixed relationship to one another. | 08-12-2010 |
20100251688 | CONTAINMENT SYSTEM FOR A GAS TURBINE ENGINE - A containment system for a gas turbine engine comprises a force absorbing arrangement for absorbing the force exerted thereon by an ejected portion of a failed component of the engine. The force absorbing arrangement circumferentially surrounds a major proportion of the axial length of the engine. | 10-07-2010 |
20100257838 | MODEL BASED HEALTH MONITORING OF AERODERIVATIVES, ROBUST TO SENSOR FAILURE AND PROFILING - A method for monitoring the health of a turbine is provided. The method comprises monitoring a turbine engine having a plurality of engine modules and determining one or more health estimates, which may included trended data, for one or more of the engine modules, based on a plurality of engine parameters. The method further determining and transmitting appropriate notifications that indicate repairs to be made to the turbine engine. | 10-14-2010 |
20100275573 | FUEL NOZZLE FLASHBACK DETECTION - A combustor of a turbine engine having a combustion zone defined therein is provided and includes a fuel nozzle, including two or more burners, each of the burners having a passage defined therein through which combustible materials are permitted to travel toward the combustion zone, a plurality of sensors disposed in relative association with each of the burners to respectively sense static pressures within the passages of each of the burners and to respectively issue sensed static pressure signals accordingly, and a controller, coupled to the sensors and receptive of the signals, which is configured to determine from an analysis of the signals whether any of the burners are associated with a flashback risk and to mitigate the flashback risk in accordance with the determination. | 11-04-2010 |
20100275574 | BORESCOPE PLUG WITH BRISTLES - In one embodiment, a system includes a rotary machine including a casing, a shaft extending through the casing, and multiple blades coupled to the shaft inside the casing. The system also includes a plug disposed in an opening in the casing, wherein the plug includes a filler coupled to a base, and the filler is configured to break away upon impact with the blades. | 11-04-2010 |
20100281843 | MULTI-STAGE COMPRESSOR FAULT DETECTION AND PROTECTION - In certain embodiments, a system includes a controller configured to obtain an inter-stage pressure measurement between stages of a multi-stage compressor. The controller is also configured to identify actual damage in the multi-stage compressor based at least in part on the inter-stage pressure measurement. | 11-11-2010 |
20100287906 | FIBER-OPTIC DYNAMIC SENSING MODULES AND METHODS - A fiber-optic dynamic sensing module comprises a support member, a beam extending from the support member, and a pre-strained fiber Bragg grating sensor and a strain-free fiber Bragg grating sensor mounted on the beam. The pre-strained and strain-free fiber Bragg grating sensors each comprise a Bragg grating inscribed in a fiber. The Bragg grating of the pre-strained fiber Bragg grating sensor is packaged more tightly along a longitudinal direction of the beam than the Bragg grating of the strain-free fiber Bragg grating sensor. | 11-18-2010 |
20100287907 | SYSTEM AND METHOD OF ESTIMATING A GAS TURBINE ENGINE SURGE MARGIN - An example method of estimating a gas turbine engine surge margin and surge margin deterioration includes monitoring debris in at least a portion of an engine and establishing an estimated surge margin for the engine using information from the monitoring The method may use gas path parameters, such as pressures, temperatures, and speeds to establish the estimated surge margin. An example gas turbine engine surge margin assessment system includes a debris monitoring system configured to monitor debris moving through a portion of an engine, and a controller programmed to execute an engine deterioration model that establishes an estimated surge margin and loss in surge margin of the engine based on information from the debris monitoring system. | 11-18-2010 |
20110000183 | ASSEMBLY PROVIDING CONTAMINANT REMOVAL - An assembly for the removal of contaminants from a contact zone between respective contact surfaces | 01-06-2011 |
20110011054 | COMBUSTOR CASING - A combustor casing with an inner casing and an outer casing and a bimetallic element arranged on an inner side of the inner casing is provided. The inner casing includes a pre-chamber area, where combustion is initiated in a fuel rich state, with an upper end and a lower end, the upper end sized and configured to be connected to a burner head. The bimetallic element is located within the pre-chamber area. | 01-20-2011 |
20110067378 | SEPARATOR DEVICE - A separator device is provided for separating dirt particles from a flow of cooling air fed to airfoils of the turbine section of a gas turbine engine. In use the separator device extends across a conduit which bypasses the combustor of the engine to convey pressurised cooling air carrying dirt particles from the compressor section of the engine to openings which direct the air into the airfoils. The separator device is configured to direct a first portion of the impinging cooling air flow away from the openings and to allow a second portion of the impinging cooling air to continue to the openings. The first portion of cooling air has a higher concentration of the coarsest dirt particles carried by the cooling air than the second portion of cooling air. | 03-24-2011 |
20110126508 | FAN CASE HAVING PENETRATION RESISTANT BLANKET - A fan is disclosed herein. The fan includes a shaft rotatable about an axis. The fan also includes a blade engaged with the shaft for rotation about the axis. The fan also includes a case encircling the axis. The case is positioned radially outward of the blade and the shaft. The fan also includes a blanket mounted to the case. The case and the blanket are operable to cooperate with one another to prevent the blade from escaping the case upon the blade separating from the shaft. The blanket is at least partially impregnated with shear thickening fluid. | 06-02-2011 |
20110138769 | FAN CONTAINMENT CASE - A fan section of a gas turbine engine having an axially extending centerline is provided. The fan section includes a fan assembly, a fan containment case, and a plurality of structural exit guide vanes. The fan assembly includes a fan rotor hub centered on and rotatable about the centerline, and a plurality of fan blades that are attached to and extend radially out from the fan rotor hub. The fan containment case is disposed radially outside of and circumferentially around the fan assembly. The fan containment case includes a shell and an integral flange ring that extends around the circumference of the shell, a circumferentially extending blade outer air seal disposed between the fan blades and the shell. The structural exit guide vanes are mechanically attached to the fan containment case at a position aligned with the integral flange ring. | 06-16-2011 |
20110154801 | GAS TURBINE ENGINE CONTAINMENT DEVICE - A fan containment system for a gas turbine engine, and a method of making the same, is disclosed that in one embodiment includes casing that surrounds at least a portion of a plurality of fan blades. In one form, a pair of standoff rings is formed in an outer surface of the casing that are spaced apart from one another a predetermined distance running circumferentially about the inner nacelle ring. A containment ring is positioned around a radially outer surface of the standoff rings to form an interference fit between the two. | 06-30-2011 |
20110203251 | FIRESEAL - An elongate fireseal having two ends joined by a longitudinal axis. The fireseal comprises at least two portions having D-shaped cross section and adjacent portions share a common dividing wall. Each end of the fireseal is configured to interlock with a complementary opposite end of the same or a further fireseal. | 08-25-2011 |
20110296810 | LIFE MANAGEMENT SYSTEM AND METHOD FOR GAS TURBINE THERMAL BARRIER COATINGS - A method, system and computer program product for life management and monitoring of a high temperature gas turbine including components having a thermal barrier coating is disclosed. The method, system and computer program product uses design, monitoring and diagnostics, and inspection data to determine the cumulative damage and remaining useful life of gas turbine components and unit risk and classification probability to determine thermal barrier coating damage probability, remaining useful life, and inspection recommendations. | 12-08-2011 |
20110308229 | ROTATING CATCHER FOR IMPELLER CONTAINMENT - An impeller for use in a containment structure has a hub, a blade attaching to the hub for compressing air as the blade rotates with the hub, and an annulus disposed about the hub whereby the annulus reduces an effect of the hub breaking apart such that a weight of the containment structure is reduced. | 12-22-2011 |
20120023894 | SYSTEMS, METHODS, AND APPARATUS FOR MONITORING CORROSION OR CORROSIVE CONTAMINANTS ASSOCIATED WITH LIQUID FUEL - Certain embodiments of the invention may include systems, methods, and apparatus for monitoring corrosion or corrosive contaminants associated with liquid fuel. According to an example embodiment of the invention, a method is provided for monitoring and predicting corrosion. The method can include monitoring corrosion or corrosive contaminants associated with liquid fuel in a fuel supply system of a gas turbine, predicting, based at least in part on the monitoring, a cumulative level of corrosion of one or more components associated with a gas turbine, and outputting information associated with the monitoring. | 02-02-2012 |
20120031068 | COMPRESSED AIR PLENUM FOR A GAS TURBINE ENGINE - A compressed air supply system for routing compressed air from a compressor to at least one combustor of a gas turbine engine is disclosed. The compressed air supply system may be formed from one or more plenums having an upstream end in fluid communication with an inner chamber of the compressor in which air is compressed and having a downstream end in fluid communication with the at least one combustor. Channeling compressed air through the plenum reduces damage to other components by confining the compressed air within the plenum. An upstream end of the plenum may be sealed to at least a portion of the compressor, and a downstream end of the plenum may be sealed to at least a portion of one or more combustors. | 02-09-2012 |
20120102912 | LOW COST CONTAINMENT RING - A containment case for a turbine engine having a plurality of blades rotating therein has a first plurality of metallic layers each of the first plurality of layers being resistant to penetration of fragments therethrough and a second plurality of metallic layers, each of the second plurality of layers absorbing kinetic energy of fragments striking said second plurality of layers. | 05-03-2012 |
20120210694 | TURBO MACHINE SPOOL PARAMETER DETECTION - A turbo machine includes a spool. A microwave detection system is configured to detect a spool parameter associated with the spool. A controller is in communication with the microwave position sensing system and is programmed to determine a spool condition, such as shaft torque and/or shear in response to the spool parameter. | 08-23-2012 |
20120247081 | FUEL NOZZLE TO WITHSTAND A FLAMEHOLDING INCIDENT AND A METHOD OF FORMING THE SAME - A nozzle is provided and includes an outer annulus defined by an exterior wall and an interior wall and including air inlets through which air flows to a fuel mixing zone and a combustion zone, an inner annulus disposed within the interior wall and including a fuel volume into which fuel is fed to a distal end thereof, which is adjacent to and isolated from the combustion zone and an airflow line, disposed between the fuel volume and the interior wall, through which air flows to the combustion zone with the airflow line and the combustion zone isolated from the fuel volume, and a fuse configured to melt during a flameholding incident and to form a breach through which fuel flows from the fuel volume, bypassing the fuel mixing zone, to a fuel burning zone downstream from the fuel mixing zone. | 10-04-2012 |
20130067882 | BLEED AIR DUCT JOINT INSULATION MEANS - A bleed air duct joint insulation means is disclosed in which a leak vent comprises valve means. | 03-21-2013 |
20130104517 | COMPONENT AND METHOD OF FABRICATING THE SAME | 05-02-2013 |
20130111872 | ELECTRICAL HARNESSES - An aircraft gas turbine engine has first and second electrical harnesses formed from respective first and second flexible printed circuit boards which each provides a plurality of spaced conductive tracks. The conductive tracks carry signal types which either (i) provide engine control and can cause hazardous engine conditions in the event of their failure, (ii) detect or prevent hazardous conditions of the engine, or (iii) are not of type (i) and/or of type (ii). The first flexible printed circuit board provides all the conductive tracks which carry signals of type (i) or the first flexible printed circuit board provides all the conductive tracks which carry signals of type (ii). The second flexible printed circuit board provides all the remaining conductive tracks. The first electrical harness is fire-resistant for a period of five minutes without any exposure of its conductive tracks so that the conductive tracks can carry their signals. | 05-09-2013 |
20130133306 | Starter Control Valve Prediction System to Predict and Trend Starter Control Valve Failures in Gas Turbine Engines Using a Starter Control Valve Health Prognostic, Computer Readable Medium and Related Methods - Starter control valve failure prediction machines, systems, computer readable media, program products, and computer implemented methods to predict and trend starter control valve failures in gas turbine engines using a starter control valve health prognostic and to make predictions of starter control valve failures, are provided. A computer implemented method according to an embodiment of the present invention can include the steps of generating a continuous starter control valve deterioration trend function responsive to a plurality of health indices derived from gas turbine engine startup data downloaded from gas turbine engine sensors for a plurality of startups and analyzing the continuous starter control valve deterioration trend function to identify potential starter control valve failure points where the points on the starter control valve deterioration trend function correlate to a starter control valve health prognostic responsive to historic gas turbine engine startup data downloaded from gas turbine engine sensors. | 05-30-2013 |
20130186056 | GAS TURBINE ENGINE COMPRISING MEANS FOR AXIALLY RETAINING A FAN OF THE ENGINE - A gas turbine engine including: a casing in which is mounted at least one shaft for driving a fan solidly connected to a driving drum including blades to compress an airflow moving from upstream to downstream in the engine; and an axial retention mechanism, on standby, solidly connected to the casing and arranged to come into contact with the driving drum such as to prevent axial movement of the drum in event of breakage of the driving shaft. | 07-25-2013 |
20130227929 | SYSTEM AND DEVICE FOR MONITORING CONTAMINANTS IN A FLUID - This disclosure describes embodiments of a system and device for measuring corrosive components suspended in air flowing to a turbo-machine. The device comprises a fluid circuit with a detection module having a sensing element disposed in a manifold. The manifold surrounds the sensing element to prevent mixing of the flow of sample air in the manifold with air from the surrounding environment. In one example, the fluid circuit also comprises a fluid flow module with elements to monitor flow characteristics of the flow of sample air. Operation of the fluid flow module can effectuate changes in flow characteristics of the flow of sample air to optimize detection of the corrosive components. | 09-05-2013 |
20130247540 | INSPECTION DEVICE FOR AN INTERNAL COMBUSTION ENGINE - This invention relates to an internal combustion engine having a cavity for inspection, comprising: an inspection device mounted within a housing, the housing at least partially located within the cavity to be inspected and having a shutter which is actuable between a closed configuration and an open configuration; and an actuation mechanism for moving the shutter between the closed configuration and the open configuration. | 09-26-2013 |
20130255221 | METHOD OF CONTROLLING A TURBOMACHINE - A method of controlling a turbine engine, including: measuring a first temperature by a first temperature sensor; measuring a second temperature by a second temperature sensor; estimating a third temperature modeling the first temperature; and determining at least one control setpoint for at least one piece of variable-geometry equipment of the engine, as a function of the measured first temperature. The first sensor presents a time constant longer than a time constant of the second sensor. The method further detects ingestion of water or hail as a function of a drop in the measured second temperature; and when water or hail ingestion is detected, determines the control setpoint as a function of the estimated third temperature. | 10-03-2013 |
20130276425 | Systems and Methods for Detecting the Onset of Compressor Stall - Embodiments of the present application include a stall detection system for a gas turbine engine. The system may include a compressor and a number of variable stator vanes associated with the compressor. The variable stator vanes may form one or more variable stator vane stages. The system may also include one or more resolvers associated with one or more of the variable stator vanes. The resolvers may be configured to detect a flutter in an angle of the variable stator vanes. The flutter may be indicative of the onset of compressor stall. | 10-24-2013 |
20130318942 | FLAME DETECTION IN NO-FLAME REGION OF GAS TURBINE - A flame detector in photonic communication with a no-flame region of a combustor of a gas turbine may emit a signal when a photon is detected. A controller may be arranged to receive a signal from the flame detector and may determine whether a flame presence in the no-flame region is indicated responsive to the signal. | 12-05-2013 |
20130327011 | Method And Apparatus For A Fuel Nozzle Assembly For Use With A Combustor - A fuel nozzle assembly for use with a combustor is provided. The fuel nozzle assembly includes a fuel nozzle including a discharge end. A cap is coupled adjacent to the nozzle discharge end, wherein the cap includes an outer surface. At least one dampener mechanism is coupled to the cap outer surface to facilitate reducing vibrations induced to the fuel nozzle. | 12-12-2013 |
20140033675 | ASSEMBLY COMPRISING A PROTECTION DEVICE AND A TURBINE MACHINE ELEMENT FOR PROTECTING - An assembly including a protection device and an element of a turbine engine for protecting, for example, an oil tank including a magnetic particle detector, the protection device including a flexible protection blanket placed on and closed around the element for protecting and including eyelets that are engaged on fastener studs provided on the blanket or on the element for protecting. The protection device further includes at least one cable carrying an attachment mechanism for attaching to the fastener studs to prevent the studs being withdrawn from the eyelets in the blanket. | 02-06-2014 |
20140069077 | ELECTRICAL GROUNDING FOR BLADE SHEATH - A blade for use in a gas turbine engine has an airfoil including a leading edge and a trailing edge. A sheath is positioned at the leading edge and secured to the airfoil by a first adhesive formed of a first material. The sheath is formed of a second material that is distinct from said first material. The first material is less electrically conductive than the second material. A grounding element is in contact with the sheath. The grounding element is in contact with a portion of the airfoil formed of a third material that is more electrically conductive than the first material. The grounding element and the portion of the airfoil together form a ground path from the sheath into the airfoil. | 03-13-2014 |
20140109546 | GROUNDING FOR FAN BLADES ON AN UNDERBLADE SPACER - A fan rotor includes a rotor body with at least one slot receiving a fan blade. The fan blade has an outer surface, at least at some areas, formed of a first material and an airfoil extending from a dovetail. The dovetail is received in the slot. A spacer is positioned radially inwardly of the dovetail biasing the fan blade against the slot. The spacer includes a grounding element, which is in contact with a portion of the dovetail formed of a second material that is more electrically conductive than the first material. The grounding element is in contact with a rotating element that rotates with the rotor. The rotating element is formed of a third material. The first material is less electrically conductive than the third material. The grounding and rotating elements form a ground path from the portion of the dovetail into the rotor. | 04-24-2014 |
20140196434 | Shroud for Sealing Conduit Feed-Through - A system has a surface intended to separate two chambers within the system. The surface has an aperture for allowing passage of at least one communication conduit. A shroud is positioned on the surface at the aperture, and has at least two portions defining a central opening to allow the communication conduit to pass through the aperture and shroud. The two portions of shroud have mating clamp ears in contact with each other. Securement members tighten the clamp ears against each other to provide a seal at an end of the shroud remote from the surface. | 07-17-2014 |
20140208712 | COMPONENT HAVING A HEAT PROTECTION SYSTEM - A component having a heat protection system is provided. The heat protection system includes an intumescent coating which extends over a surface of the component. The heat protection system further includes a heat resistant wrapping which covers the coating on the component. The wrapping is expandable when the coating intumesces to maintain the wrapping's coverage of the coating. | 07-31-2014 |
20150027100 | SYSTEM FOR PERFORMING STAGING CONTROL OF A MULTI-STAGE COMBUSTOR - A control system is provided for performing staging control of a multi-stage combustor of a gas turbine engine. The fuel is fed to the combustor by a fuel supply system comprising: a plurality of fuel manifolds distributing fuel to respective stages of the combustor, a fuel metering valve operable to control the rate at which fuel passes to the fuel manifolds, and an actuating arrangement which splits the fuel flow from the fuel metering valve between the fuel manifolds. The control system includes a fuel pressure sensor arrangement which senses the fuel pressure at entry to the actuating arrangement, and/or in one or more of the fuel manifolds. The control system further includes a controller which repeatedly: calculates a fuel split between the fuel manifolds based on the sensed fuel pressure(s), and issues a command signal to the actuating arrangement to implement the calculated fuel pressure-based fuel split. | 01-29-2015 |
20150082769 | EXHAUST CASING COMPRISING A FLUID DISCHARGE DEVICE AND TURBINE ENGINE - The invention relates to a turbine engine exhaust casing ( | 03-26-2015 |
20150089921 | AUXILIARY POWER SUPPLY METHOD THROUGH AN AUXILIARY POWER UNIT AND CORRESPONDING ARCHITECTURE - An auxiliary power supply architecture includes one APU and a fuel supply basic circuit with a common fuel storage tank, a primary circulation conduct and secondary conducts for injecting such fuel into the combustion chambers of the APU unit through appropriate injectors. Such architecture also includes another independent fuel supply circuit to supply the APU unit with an emergency tank, a specific primary conduct for emergency fuel circulation and secondary conducts for injecting emergency fuel into the combustion chambers through appropriate injectors. | 04-02-2015 |
20150113937 | ENHANCED FIRE PROTECTION FOR FUEL MANIFOLD - One embodiment includes a fuel manifold segment for supplying fuel to a fuel injector. The fuel manifold segment contains a fuel line surrounded by a first firesleeve. A pigtail line connects to the fuel line. A connector on the pigtail line connects to a fuel injector inlet fitting. A second firesleeve surrounds the first firesleeve. A cuff surrounds the pigtail line, portion of first firesleeve, and portion of fuel line to which the pigtail line is connected. A boot then surrounds the connector. | 04-30-2015 |
20150308915 | FUEL LEAK DETECTION SYSTEM FOR USE IN A TURBINE ENCLOSURE - A fuel leak detection system for use in a turbine enclosure is provided. The system includes a ventilation duct extending through an interior cavity of the turbine enclosure such that an extended portion of the ventilation duct is positioned within a bottom portion of the turbine enclosure. The ventilation duct includes a plurality of openings configured to allow air from within the turbine enclosure to be drawn into the ventilation duct through the plurality of openings. The system also includes a sensor system coupled in flow communication with the air drawn into the ventilation duct, the sensor system configured to detect fuel in the air. | 10-29-2015 |
20150354454 | APPARATUS AND SYSTEM FOR COMPRESSOR CLEARANCE CONTROL - Various embodiments include apparatuses and systems for controlling compressor clearances. In one case, an apparatus includes: a material layer sized to fit a case of a gas turbine (GT) compressor in a GT system, the material layer including a heating element for applying heat to the case of the GT compressor; and a control system coupled with the material layer, the control system configured to: determine whether a shutdown sequence is occurring in the GT system; and actuate the heating element to apply heat to the case of the GT compressor in response to determining that the shutdown sequence is occurring. | 12-10-2015 |