Abstract: A system is for sensing a shifting of a drive ring, a compressor, and a gas turbine. The system includes a compressor housing; at least one drive ring installable on the compressor housing and disposed on the compressor housing with a spacing, and the at least one drive ring being provided with at least one installation hole, extending along a radial direction of the at least one drive ring; and at least one sensor, located in the corresponding installation hole and used to sense the spacing between the at least one drive ring and the compressor housing in real time. In an embodiment, the system for sensing a shifting of a drive ring, the compressor, and the gas turbine has advantages of simple structures and relatively low costs.

Abstract: A system is for sensing a shifting of a drive ring, a compressor, and a gas turbine. The system includes a compressor housing; at least one drive ring installable on the compressor housing and disposed on the compressor housing with a spacing, and the at least one drive ring being provided with at least one installation hole, extending along a radial direction of the at least one drive ring; and at least one sensor, located in the corresponding installation hole and used to sense the spacing between the at least one drive ring and the compressor housing in real time. In an embodiment, the system for sensing a shifting of a drive ring, the compressor, and the gas turbine has advantages of simple structures and relatively low costs.

Abstract: The present disclosure provides a gas turbine combustor including a combustion structure (10) having a combustor liner (14) and a flow sleeve (12). The combustor liner (14) includes inner and outer surfaces (31, 30) and defines a combustion zone (15). The gas turbine combustor further includes a plurality of hollow airfoil-shaped structures (22) affixed to the combustor liner (14) and extending radially outwardly into an airflow space (18) defined radially between the flow sleeve (12) and the combustor liner (14). Each hollow structure (22) includes at least one metering tube (26) providing acoustic communication between the combustion zone (15) and the hollow structure (22). The metering tubes (26) are detachably coupled to the combustor liner (14) for permitting interchanging of the metering tube (26) with at least one additional metering tube having at least one different dimension to effect a change in an acoustic characteristic of the hollow structure (22).

Abstract: The present disclosure provides a gas turbine combustor including a combustion structure (10) having a combustor liner (14) and a flow sleeve (12). The combustor liner (14) includes inner and outer surfaces (31, 30) and defines a combustion zone (15). The gas turbine combustor further includes a plurality of hollow airfoil-shaped structures (22) affixed to the combustor liner (14) and extending radially outwardly into an airflow space (18) defined radially between the flow sleeve (12) and the combustor liner (14). Each hollow structure (22) includes at least one metering tube (26) providing acoustic communication between the combustion zone (15) and the hollow structure (22). The metering tubes (26) are detachably coupled to the combustor liner (14) for permitting interchanging of the metering tube (26) with at least one additional metering tube having at least one different dimension to effect a change in an acoustic characteristic of the hollow structure (22).

Abstract: A resonance chamber (42) has an outer wall (32) with coolant inlet holes (34A-C), an inner wall (36) with acoustic holes (38), and side walls (40A-C) between the inner and outer walls. A depression (33A-C) in the outer wall has a bottom portion (50) that is close to the inner wall compared to peaks (37A-C) of the outer wall. The coolant inlet holes may be positioned along the bottom portion of the depression and along a bottom portion of the side walls to direct coolant flows (44, 51) toward impingement locations (43) on the inner wall that are out of alignment with the acoustic holes. This improves impingement cooling efficiency. The peaks (37A-C) of the outer wall provide volume in the resonance chamber for a target resonance.

Abstract: An acoustically dampened gas turbine engine having a gas turbine engine combustor with an acoustic damping resonator system is disclosed. The acoustic damping resonator system may be formed from one or more resonators positioned within the gas turbine engine combustor at an outer housing forming a combustor basket and extending circumferentially within the combustor. The resonator may be positioned in a head region of the combustor basket. In one embodiment, the resonator may be positioned in close proximity to an intersection between the outer housing and an upstream wall defining at least a portion of the combustor. The acoustic damping resonator system may mitigate longitudinal mode dynamics thereby increasing an engine operating envelope and decreasing emissions.

Abstract: A combustor assembly in a gas turbine engine includes a liner defining a combustion zone, at least one fuel injector for providing fuel, and a flow sleeve. An inner surface of the flow sleeve defines an outer boundary for an air flow passageway. Upon the air reaching a head end of the combustor assembly at an end of the air flow passageway the air turns 180 degrees to flow into the combustion zone where it is burned with the fuel. The combustor assembly further includes an inlet assembly positioned radially between the liner and the flow sleeve. The inlet assembly defines an inlet to the air flow passageway and includes a plurality of overlapping conduits that are arranged such that the air entering the air flow passageway passes through radial spaces between adjacent conduits.

Abstract: A combustor for a gas turbine engine includes a pilot fuel injector and a plurality of circumferentially located main injectors for injecting fuel and air into a combustion chamber defined by a liner wall of a combustor basket. A combustion zone is located in the combustion chamber where the fuel and air are ignited to produce hot combustion gases. A plurality of vortex generators are located in circumferentially spaced relation on the liner wall and comprise structures extending radially inward into the combustion chamber to create vortices at predetermined circumferential locations downstream from where the fuel and air are ignited to effect a reduction in emissions of the combustion gases.

Abstract: An acoustically dampened gas turbine engine having a gas turbine engine combustor with an acoustic damping resonator system is disclosed. The acoustic damping resonator system may be formed from one or more resonators positioned within the gas turbine engine combustor at an outer housing forming a combustor basket and extending circumferentially within the combustor. The resonator may be positioned in a head region of the combustor basket. In one embodiment, the resonator may be positioned in close proximity to an intersection between the outer housing and an upstream wall defining at least a portion of the combustor. The acoustic damping resonator system may mitigate longitudinal mode dynamics thereby increasing an engine operating envelope and decreasing emissions.

Abstract: A combustor assembly in a gas turbine engine includes a liner defining a combustion zone, at least one fuel injector for providing fuel, and a flow sleeve. An inner surface of the flow sleeve defines an outer boundary for an air flow passageway. Upon the air reaching a head end of the combustor assembly at an end of the air flow passageway the air turns 180 degrees to flow into the combustion zone where it is burned with the fuel. The combustor assembly further includes an inlet assembly positioned radially between the liner and the flow sleeve. The inlet assembly defines an inlet to the air flow passageway and includes a plurality of overlapping conduits that are arranged such that the air entering the air flow passageway passes through radial spaces between adjacent conduits.

Abstract: A resonance chamber (42) has an outer wall (32) with coolant inlet holes (34A-C), an inner wall (36) with acoustic holes (38), and side walls (40A-C) between the inner and outer walls. A depression (33A-C) in the outer wall has a bottom portion (50) that is close to the inner wall compared to peaks (37A-C) of the outer wall. The coolant inlet holes may be positioned along the bottom portion of the depression and along a bottom portion of the side walls to direct coolant flows (44, 51) toward impingement locations (43) on the inner wall that are out of alignment with the acoustic holes. This improves impingement cooling efficiency. The peaks (37A-C) of the outer wall provide volume in the resonance chamber for a target resonance.

Abstract: Methods for determining whether a test agent inhibits a 17?-HSD3, the methods comprising: obtaining a recombinant host cell that expresses the 17?-HSD3; obtaining a reaction mixture comprising the 17?-HSD3, androstenedione, and the test agent; measuring the amount of testosterone in the reaction mixture by a scintillation proximity assay (SPA) using SPA beads conjugated with a testosterone-specific antibody, wherein when the amount of testosterone is lower in the presence of a test agent than in the absence of the test agent, the test agent is identified as an inhibitor of the 17?-HSD3.

Abstract: Methods for determining whether a test agent inhibits a 17?-HSD3, said methods comprising: obtaining a recombinant host cell that expresses said 17?-HSD3; obtaining a reaction mixture comprising said 17?-HSD3, androstenedione, and said test agent; measuring the amount of testosterone in said reaction mixture by a scintillation proximity assay (SPA) using SPA beads conjugated with a testosterone-specific antibody, wherein when the amount of testosterone is lower in the presence of a test agent than in the absence of the test agent, the test agent is identified as an inhibitor of said 17?-HSD3.

Abstract: A circuit for controlling a read operation for a magnetic random access memory (MRAM) comprising an array of magnetic tunnel junctions (MTJ) having conducting row and column lines attached thereto. The circuitry comprises a current supply for providing a read current, and a row selector for selecting a row containing a junction to be read and applying the read current to that row with the respective row line. An unselected row switch switches to at least some of the row lines not connected to the MTJ to be read, and a voltage source applies, via the unselected row switch, a voltage to each of the unselected row lines that is substantially identical in level to the voltage on the selected row line. A column selector selects the column line connected to the array containing the MTJ to be read, and a voltage detector for detecting the voltage across the MTJ to be read via the selected column and row lines.

Abstract: A circuit for controlling a read operation for a magnetic random access memory (MRAM) comprising an array of magnetic tunnel junctions (MTJ) having conducting row and column lines attached thereto. The circuitry comprises a current supply for providing a read current, and a row selector for selecting a row containing a junction to be read and applying the read current to that row with the respective row line. An unselected row switch switches to at least some of the row lines not connected to the MTJ to be read, and a voltage source applies, via the unselected row switch, a voltage to each of the unselected row lines that is substantially identical in level to the voltage on the selected row line. A column selector selects the column line connected to the array containing the MTJ to be read, and a voltage detector for detecting the voltage across the MTJ to be read via the selected column and row lines.