Siemens Aktiengesellschaft

Danning You

Juan Enrique Portillo Bilbao

Rajesh Rajaram

Anthony L Schiavo

Bernd Prade

Werner Krebs

Kevin J Spence

Biao Sun

John M Crane

Chao Ren

Kevin M Spence

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.

System for sensing shifting of drive ring, compressor and gas turbine

The present disclosure provides a gas turbine combustor including a combustion structure () having a combustor liner () and a flow sleeve (). The combustor liner () includes inner and outer surfaces () and defines a combustion zone (). The gas turbine combustor further includes a plurality of hollow airfoil-shaped structures () affixed to the combustor liner () and extending radially outwardly into an airflow space () defined radially between the flow sleeve () and the combustor liner (). Each hollow structure () includes at least one metering tube () providing acoustic communication between the combustion zone () and the hollow structure (). The metering tubes () are detachably coupled to the combustor liner () for permitting interchanging of the metering tube () 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 ().

Resonators with interchangeable metering tubes for gas turbine engines

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.

Acoustic damping system for a combustor of a gas turbine engine

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.

Flow sleeve inlet assembly in a gas turbine engine

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Shanghai, China

Danning You