Abstract: A premix pilot nozzle is disclosed herein. The premix pilot nozzle includes a nozzle body. The nozzle body includes a forward wall, an aft wall, an outer band that extends between the forward wall and the aft wall and a tip portion that extends axially downstream from the aft wall. The nozzle body further defines a fuel inlet plenum that extends coaxially within the nozzle body, a fuel distribution plenum that is defined within the nozzle body radially outwardly from and in fluid communication with the fuel inlet plenum, a plurality of premix passages that extend helically around the fuel inlet plenum within the fuel distribution plenum and a plurality of air passages annularly arranged around the plurality of premix passages. One or more premix passages of the plurality of premix passages are in fluid communication with the fuel distribution plenum.

Abstract: In one embodiment, a system is provided. The system includes a turbine control system, comprising a processor. The processor is configured to receive an input for transitioning between a normal load path (NLP) of a turbine system and a cold load path (CLP) of the turbine system. The processor is additionally configured to determine a carbon monoxide (CO) setpoint based on the input. The processor is further configured to apply a temperature control based on the CO setpoint, wherein the normal load path comprises higher emissions temperatures as compared to the cold load path.

Abstract: The premixed pilot nozzle includes axially elongated tubes defined within a plenum between an outer shroud and a first shroud disposed radially inward of the outer shroud. The tubes extend between tube inlets defined through a forward face and tube outlets defined through an aft face. A second shroud is disposed radially inward of the first shroud, thereby defining a fuel plenum between the first shroud and the second shroud, and the fuel plenum is in communication with a gaseous fuel supply. A fuel injection port, which is positioned between the tube inlet and the tube outlet of each tube, is in fluid communication with the fuel plenum. An air supply configured to fluidly communicate with the tube inlet of each tube. The second shroud defines a second plenum therein, the second plenum being coupled to a source of a non-combustible fluid.

Abstract: A gas turbine combustor includes: a head end comprising a primary fuel nozzle; a liner defining a primary combustion zone proximate the head end and a downstream secondary combustion zone; a forward casing radially outward of and surrounding at least a portion of the liner; and an axial fuel staging system. The axial fuel staging system includes a plurality of fuel injection assemblies. Each fuel injection assembly includes a thimble assembly mounted to the liner, and an injector unit attached to the forward casing. A thimble of the thimble assembly extends through a thimble aperture in the liner. The injector unit extends through the forward casing, such that a portion of the injector unit is disposed within the thimble, and a fuel line fitting is disposed outward of the forward casing. The injector unit introduces fuel into air flowing through the thimble for injection into the secondary combustion zone.

Abstract: A thimble assembly, which directs fluid flow through a combustor liner, includes a thimble boss and a thimble. The thimble boss is mounted an outer surface of the liner and surrounds a liner opening, thus defining a thimble boss passage. The thimble is disposed through the passage and the liner opening. The thimble wall extends from an inlet portion to an outlet of the thimble. The inlet portion has a greater diameter than the outlet and defines an inlet plane and a parallel intermediate plane. A terminal plane, parallel to the intermediate plane, includes an array of points most distant from a corresponding array of points defining the intermediate plane. The thimble wall has a non-uniform length, such that the outlet of the thimble is oriented at an oblique angle relative to the terminal plane. The thimble wall may have an arcuate shape defined as one-fourth of an ellipse.

Abstract: An injection assembly for a gas turbine combustor having a liner defining a combustion zone and a secondary combustion zone and a forward casing circumferentially surrounding at least a portion of the liner is provided. The injection assembly includes a thimble assembly and an injector unit. The thimble assembly, which is mounted to the liner, includes a thimble that extends through a thimble aperture in the liner. The injector unit, which is mounted to and extends through the forward casing, includes an injector blade that extends into the thimble. The injection assembly introduces a flow of fuel into a flow of air flowing through the thimble, such that fuel and air are injected into the secondary combustion zone in a direction transverse to a flow of combustion products from the primary combustion zone.

Abstract: Anti-angiogenic treatments, treatments of hyperpermeability disorders, treatments of neuropathic and neurodegenerative disorders, pain treatments, methods of reducing the risk of pre-eclampsia and compounds for use in such methods are described.

Abstract: The present invention relates to a pharmaceutical aqueous formulation comprising 1-(4-{[4-(dimethylamino)piperidin-1-yl]carbonyl}phenyl)-3-[4-(4,6-dimorpholin-4-yl-1,3,5-triazin-2-yl)phenyl]urea, or a pharmaceutically acceptable salt thereof, that is a clear solution. Such a formulation is particularly suitable for intravenous or parenteral administration to a patient.

Abstract: An optical selector arrangement (22), comprising: a first set of optical ports (30), having a first number of optical ports, the first number being greater than or equal to 2; a second set of optical ports (42), having a second number of optical ports, the second number being greater than the first number; the second set of optical ports being for communicating with the first set of optical ports, a selector interface (40) for the optical selector arrangement, the selector interface comprising the second set of optical ports (42), a part of the optical selector arrangement functioning as a selector (44), the selector being arranged to selectively optically couple the first set of optical ports (30) to a set of ports of the second set of optical ports (42) of the selector interface, the selector (44) being rotatable relative to the selector interface (40) to facilitate the selection by optically aligning the first set of optical ports (30) to the second set of optical ports (42) of the selector interface (40);

Abstract: The present invention relates to a pharmaceutical aqueous formulation comprising -(4-{[4-(dimethylamino)piperidin-1-yl]carbonyl}phenyl)-3-[4-(4,6-dimorpholin-4-yl-,3,5-triazin-2-yl)phenyl]urea, or a pharmaceutically acceptable salt thereof, that is a clear solution. Such a formulation is particularly suitable for intravenous or parenteral administration to a patient.

Abstract: This disclosure relates to systems and methods for tuning combustion dynamics in a combustor. In one embodiment of the disclosure, a method includes providing, via at least one sensor, combustion dynamics amplitude data associated with a combustor. Method may allow monitoring, by an equipment controller communicatively coupled to the at least one sensor, the combustion dynamics amplitude data. The method may allow detecting at least one change in acoustic pressure amplitude associated with combustion in the combustor. In response to detecting the change in the acoustic pressure amplitude, the method proceeds with determining a fuel split change to at least two fuel circuits configured to supply fuel to the combustor, and applying the fuel split change to the combustor.

Abstract: A system is provided. The system includes a combustor assembly that receives a fuel flow. The system includes a pressure sensor disposed within the combustor assembly that measures a pressure of the fuel flow from a fuel supply to a fuel nozzle of the combustor assembly. The system includes a controller communicatively coupled to the pressure sensor. The controller is configured to receive a pressure measurement from the pressure sensor. The pressure measurement is a current operating parameter of the combustor assembly. The controller is configured to determine a predicted fuel flow based at least in part on the pressure measurement, determine a fuel composition factor based on a comparison of the predicted fuel flow with a commanded fuel flow, and adjust control of the combustor assembly based on the fuel composition factor. The fuel composition factor is indicative of a change in a fuel composition of the fuel flow.

Abstract: A system includes a combustor assembly which receives a fuel-oxidant mixture. The system includes a control valve which controls a fuel flow into the combustor assembly. The system includes one or more sensors which measure one or more properties. The system includes a controller communicatively coupled to the one or more sensors and the control valve. The controller receives data from the one or more sensors indicative of operating conditions of the combustor assembly. The controller determines a predicted fuel flow for a first fuel line of a plurality of fuel lines based in part on the data received from the one or more sensors. The controller calculates a difference between a commanded fuel flow and the predicted fuel flow. The controller adjusts an operation of the control valve associated with a gas turbine engine when the difference is greater than a threshold.

Abstract: There is disclosed an acoustic transducer for communications within an operational bandwidth, the transducer comprising: A signal generator for generating a signal at a centre-frequency within the operational bandwidth; A piezoelectric element having a dielectric constant that varies with temperature; A driving electrode at the surface of the piezoelectric element; A matching network, having a natural frequency at a given temperature, and operable to transfer the signal from the signal generator to the piezoelectric element whilst mitigating electrical loss, the matching network being connected to the driving electrode; Wherein the matching network comprises a temperature compensating capacitor connected in parallel with the piezoelectric element, the temperature compensating capacitor being for counteracting temperature-induced changes to the dielectric constant of the piezoelectric element such that the electrical natural frequency of the transducer is substantially constant over a range of temperatures.

Abstract: An optical selector arrangement (22), comprising: a first set of optical ports (30), having a first number of optical ports, the first number being greater than or equal to 2; a second set of optical ports (42), having a second number of optical ports, the second number being greater than the first number; the second set of optical ports being for communicating with the first set of optical ports, a selector interface (40) for the optical selector arrangement, the selector interface comprising the second set of optical ports (42), a part of the optical selector arrangement functioning as a selector (44), the selector being arranged to selectively optically couple the first set of optical ports (30) to a set of ports of the second set of optical ports (42) of the selector interface, the selector (44) being rotatable relative to the selector interface (40) to facilitate the selection by optically aligning the first set of optical ports (30) to the second set of optical ports (42) of the selector interface (40);

Abstract: A premix pilot nozzle and fuel nozzle assembly are disclosed herein. The premix pilot nozzle includes a nozzle body having a forward wall axially spaced from an aft wall and an outer band that extends axially between the forward wall and the aft wall. An air tube extends coaxially within the nozzle body and defines a cooling air plenum within the nozzle body. A fuel tube extends coaxially within the nozzle body and circumferentially surrounds the air tube so as to define a fuel inlet plenum therebetween. A fuel distribution plenum is defined within the nozzle body and is in fluid communication with the fuel inlet plenum. The nozzle body further includes a plurality of premix tubes. Each premix tube extends helically around the fuel tube within the fuel distribution plenum. One or more of the premix tubes is in fluid communication with the fuel distribution plenum.

Abstract: A premix pilot nozzle is disclosed herein. The premix pilot nozzle includes a nozzle body. The nozzle body includes a forward wall, an aft wall, an outer band that extends between the forward wall and the aft wall and a tip portion that extends axially downstream from the aft wall. The nozzle body further defines a fuel inlet plenum that extends coaxially within the nozzle body, a fuel distribution plenum that is defined within the nozzle body radially outwardly from and in fluid communication with the fuel inlet plenum, a plurality of premix passages that extend helically around the fuel inlet plenum within the fuel distribution plenum and a plurality of air passages annularly arranged around the plurality of premix passages. One or more premix passages of the plurality of premix passages are in fluid communication with the fuel distribution plenum.

Abstract: The present invention relates to a pharmaceutical aqueous formulation comprising -(4-{[4-(dimethylamino)piperidin-1-yl]carbonyl}phenyl)-3-[4-(4,6-dimorpholin-4-yl-,3,5-triazin-2-yl)phenyl]urea, or a pharmaceutically acceptable salt thereof, that is a clear solution. Such a formulation is particularly suitable for intravenous or parenteral administration to a patient.

Abstract: A system, a method and a collapsible and/or folding apparatus may use a wire loop to cut an object. The apparatus may have a wire loop connected to pulleys on a carriage attached to a frame. The carriage may move relative to the frame to direct the wire loop through the object. The apparatus may have arms on the carriage that may be folded and/or a kicker frame pivotably connected to the frame that may be retracted to reduce the overall size of the apparatus.

Abstract: Signal processing apparatus located in and/or mounted on an entity (e.g. an aircraft), the signal processing apparatus comprising: a first module; a second module connected to the first module such that signals may be sent between those modules; one or more amplifiers configured to amplify signals sent between the modules; and one or more optical fibres. The first module is located at a first location in/on the entity. The second module and the one or more amplifiers are located at a second location in/on the entity. The first location and the second location are spatially separate, i.e. remote from one another. The optical fibre(s) couple together the first and the second locations such that a signal sent between those locations is sent via the optical fibre(s).