Abstract: A computer system receives, by a first application, a plurality of shared media items. After receiving the plurality of shared media items, the computer system receives, via one or more input devices, a request to search a media library of a second application that is different from the first application for media items in the media library that meet search criteria. In response to receiving the request to search the media library, the computer system concurrently displays, via a display generation component, two or more media items that meet the search criteria. The two or more media items include: one or more media items from the media library of the second application that meet the search criteria, and one or more of the shared media items that are not stored within the media library of the second application and that meet the search criteria.

Abstract: The present disclosure generally relates to navigating a collection of media items. In accordance with one embodiment, in response to receiving an input, a device displays a first view of a collection of media items, including concurrently displaying a representation of a first time period and a representation of a second time period. In accordance with a determination that a current time is associated with a first recurring temporal event: the representation of the first time period includes a first representative media item and the representation of the second time period includes a second representative media item. In accordance with a determination that the current time is associated with a second recurring temporal event, the representation of the first time period includes a third representative media item and the representation of the second time period includes a fourth representative media item.

Abstract: Described herein is a solution to address the intrinsic nonlinearity of analog signals and the restrictions this places on the signals dynamic range. The subject matter described herein produces linear electro-optic modulation over a dramatically wider range of the input signal amplitude. This is accomplished by a distributed multiwavelength design that “folds” the large dynamic range across multiple linear subranges, with each subrange being addressed using an optical wavelength. As a result, the subrange within the wide dynamic range of the input signal is captured by the linear portion of the transfer function of a single transfer function. Several physical implementations of this subject are presented herein. This innovation enables the efficient use of optical links for the transmission and processing of analog and multilevel signals, overcoming the limitations that were once hindering progress in this field.

Abstract: A system and method are provided for a device for use with a primary device and a remote control device, the primary device being configured to perform a function, the remote control device including an infrared (IR) transmitter and a wireless transceiver. The IR transmitter is configured to transmit an IR signal based on the primary device control code, and the transceiver is configured to receive a wireless instruction signal. The device comprises a memory and a processor. The processor is configured to execute instructions stored on the memory to cause the device to: obtain primary device data associated with the primary device; generate the wireless instruction signal based on the primary device data; and transmit the wireless instruction signal to cause the remote control device to transmit the IR signal to instruct the primary device to perform the function.

Abstract: A gas turbine combustor for producing hot gas by burning a fuel in compressed air comprising a combustor central axis and multiple main swirlers with respective swirler axes disposed about and parallel to the combustor central axis, each main swirler delivering an air fuel mixture flowing through it and about its swirler axis, wherein each swirler imparts rotation to the air fuel mixture flowing through it in a direction opposite that of adjacent swirlers. This combustor configuration reduces shear where the outer edges of adjacent flows meet, allowing for greater tuning of the combustion chamber and reduced NOx and CO emissions.

Abstract: The present invention relates to a burner system (1) comprising a pilot burner arrangement (2), a main burner arrangement (3) surrounding the pilot burner arrangement (2), a combustion chamber arranged downstream with respect to the pilot burner arrangement (2) and the main burner arrangement (3), and at least one resonator (17), wherein the main burner arrangement (3) defines a ring-shaped air supply (13) outwardly delimited by a burner cone (14) and provided with radially extending swirl vanes (15), wherein a resonator cavity (18) of the at least one resonator (17) is formed at the outside of the burner cone (14), wherein the resonator cavity (18) is provided with a plurality of resonator openings (20) defining a fluidic connection between the resonator cavity (18) and the combustion chamber.

Abstract: A burner (1) with a longitudinal burner axis (2) and a mixing channel (3, 4), formed in an annular manner around the longitudinal burner axis (2), for the mixing of fuel and air. Each mixing channel is bounded radially on the inside by a channel hub (5, 6) and radially on the outside by a channel outer wall (7, 8). A fuel concentration distribution in the mixing channel (3, 4) from the channel hub (5, 6) to the channel outer wall (7, 8) being adjustable by adjusting the introduction of fuel to provide an adjustable fuel concentration distribution at respective radial locations across each mixing claimed. Also a combustion system (20) with a burner (1) and to a method for operating a burner (1).

Abstract: A hot gas path system for a gas turbine including a stepped inlet ring at an intersection between a downstream end of a combustor basket and an upstream end of a transition is disclosed. The heat shield may be positioned downstream from a combustor basket and proximate to an intersection between the collar and the axially extending cylindrical wall. The stepped inlet ring may be coupled to the transition section and may extend upstream from the transition section. An upstream end of the stepped inlet ring may be positioned radially outward from the combustor basket such that at least a portion of the stepped inlet ring overlaps a portion of the combustor basket. A spring clip may be positioned between the combustor basket and the stepped inlet ring such that the spring clip seals at least a portion of a gap between the combustor basket and the stepped inlet ring.

Abstract: A method and system for controlling delivery of fuel to a dual stage nozzle in the combustor of a gas turbine. A liquid fuel is conveyed from a single stage fuel supply through a plurality of primary fuel supply lines to a first nozzle stage including a plurality of primary nozzles. A predetermined operating condition of the gas turbine is identified and a signal is produced in response to the identified operating condition. The signal effects actuation of valves located on secondary fuel supply lines extending from each of the primary fuel supply lines to supply fuel to respective secondary nozzles.

Abstract: A combustor-to-transition seal (301) includes a spring clip assembly (322, 422, 522) and a first spring metal ring (340, 441) or a ring assembly (440,540) that includes the first spring metal ring (441) and a second spring metal ring (442). Such combustor-to-transition seal (301) provides a first seal (321) and a second seal (331, 531) when at a junction of a combustor (108, 308, 508) and a transition (114, 314, 514). In an embodiment, the first spring metal ring (340) has a plurality of apertures (342) through the ring (340) that provide effusion cooling of the ring (340). The plurality of apertures (342) regulates a flow of cooling fluid to maintain an acceptable temperature of the ring (340). In an alternative embodiment, the second spring metal ring (442) has grooves (446) that regulate a flow of cooling fluid to maintain an acceptable temperature of the ring assembly (440).

Abstract: A fuel injector assembly for use in a turbine engine having a combustion section and a turbine section downstream from the combustion section. The fuel injector assembly includes a flow sleeve defining a pre-mixing passage of the combustion section and including a sleeve wall having a forward end proximate to a cover plate of the combustion section and an opposed aft end. An annular cavity in fluid communication with a source of fuel is formed in the sleeve wall adjacent the aft end. A fuel dispensing structure is associated with the cavity and includes at least one fuel distribution aperture for distributing fuel from the cavity to the pre-mixing passage.

Abstract: A combustor assembly in a gas turbine engine is provided. The combustor assembly may comprise a combustor device coupled to a main casing, a transition duct and a flow conditioner. The combustor device may comprise a liner having inlet and outlet portions and a burner assembly positioned adjacent to the liner inlet. The transition duct may comprise a conduit having inlet and outlet sections. The inlet section may be associated with the liner outlet portion. The flow conditioner may be associated with the main casing and the transition duct conduit for supporting the conduit inlet section.

Abstract: A gas turbine engine fuel heat shield configured to shield fuel from high temperatures of surrounding turbine components to prevent coking of the fuel is disclosed. The gas turbine engine fuel heat shield may be formed from a generally elongated member having a first collar at a first end and a second collar at a second end opposite to the first end. One or more recesses may be positioned in an outer surface of the generally elongated member between the first and second collars. A sleeve is positioned around the generally elongated member and radially outward of the recess to form one or more sealed chambers. The sleeve may be sealed to prevent fuel from entering the recess and coking. Such design, therefore, prevents the formation of carbon particles from the fuel that could clog the fuel injectors.

Abstract: An igniter assembly (10) of a gas turbine (12) is presented, including an igniter (14) disposed within an igniter housing (16). The igniter is extendable from the igniter housing through an opening (18) in a combustion liner (19) to an extended position, and is retractable from the extended position back through the opening to a retracted position (22). The igniter assembly further includes a compressible assembly (24) disposed between a base (26) of the igniter housing and the combustion liner to form a sealed interface (15) with a perimeter (28) of the opening (18). The compressible assembly is configured to restrict an air flow from passing between the igniter housing base and the perimeter of the opening. The compressible assembly is variable in length to accommodate a respective variation in a separation between the igniter housing base (26) and the opening (18).

Abstract: A hot gas path system for a gas turbine including a stepped inlet ring at an intersection between a downstream end of a combustor basket and an upstream end of a transition is disclosed. The heat shield may be positioned downstream from a combustor basket and proximate to an intersection between the collar and the axially extending cylindrical wall. The stepped inlet ring may be coupled to the transition section and may extend upstream from the transition section. An upstream end of the stepped inlet ring may be positioned radially outward from the combustor basket such that at least a portion of the stepped inlet ring overlaps a portion of the combustor basket. A spring clip may be positioned between the combustor basket and the stepped inlet ring such that the spring clip seals at least a portion of a gap between the combustor basket and the stepped inlet ring.

Abstract: A fuel delivery system for a turbine engine includes a fluid supply conduit. The conduit has an inner peripheral surface that defines a flow supply passage. A fuel strainer is received in the conduit. The strainer has a hollow, generally frusto-conical body with an outer peripheral surface. The strainer has a longitudinal axis. A plurality of holes extends through the body substantially radially to the longitudinal axis. The holes have an associated effective flow area. The outer peripheral surface of the body is radially spaced from the inner peripheral surface of the conduit along the length of the strainer such that a flow area is defined between the outer peripheral surface of the strainer body and the inner peripheral surface of the fluid supply conduit. The flow area is equal to or greater than the effective flow area of the strainer holes along the length of the strainer.

Abstract: A gas turbine engine fuel heat shield configured to shield fuel from high temperatures of surrounding turbine components to prevent coking of the fuel is disclosed. The gas turbine engine fuel heat shield may be formed from a generally elongated member having a first collar at a first end and a second collar at a second end opposite to the first end. One or more recesses may be positioned in an outer surface of the generally elongated member between the first and second collars. A sleeve is positioned around the generally elongated member and radially outward of the recess to form one or more sealed chambers. The sleeve may be sealed to prevent fuel from entering the recess and coking. Such design, therefore, prevents the formation of carbon particles from the fuel that could clog the fuel injectors.

Abstract: A support for the first row turbine vanes (12) in a gas turbine engine, the support including a support framework (18). The support framework (18) includes an outer vane carrier (34), and an inner vane carrier (36) connected to the outer vane carrier (34) by a plurality of struts (44, 46). The outer vane carrier (34) is mounted to an inner casing (16) of the engine and the struts (44, 46) support the inner vane carrier (36) in cantilevered relation to the outer vane carrier (34). An aft outer flange (94) of each first row vane (12) is supported on the outer vane carrier (34) and a forward inner flange (114) of the vane (12) is support on the inner vane carrier (36).

Abstract: A gas turbine combustor for producing hot gas by burning a fuel in compressed air comprising a combustor central axis and multiple main swirlers with respective swirler axes disposed about and parallel to the combustor central axis, each main swirler delivering an air fuel mixture flowing through it and about its swirler axis, wherein each swirler imparts rotation to the air fuel mixture flowing through it in a direction opposite that of adjacent swirlers. This combustor configuration reduces shear where the outer edges of adjacent flows meet, allowing for greater tuning of the combustion chamber and reduced NOx and CO emissions.

Abstract: A combustor assembly in a gas turbine engine is provided. The combustor assembly may comprise a combustor device coupled to a main casing, a transition duct and a flow conditioner. The combustor device may comprise a liner having inlet and outlet portions and a burner assembly positioned adjacent to the liner inlet. The transition duct may comprise a conduit having inlet and outlet sections. The inlet section may be associated with the liner outlet portion. The flow conditioner may be associated with the main casing and the transition duct conduit for supporting the conduit inlet section.