Siemens Westinghouse Power Corporation

Siemens Power Generation, Inc.

Richard D Holm

Thomas E Lippert

William Richard Ryan

Zal N Sanjana

Ronald T Harrold

Nancy H Ulerich

Dennis M Bachovchin

Satish B Gadde

Phillip W Gravett

Brian D Ottinger

Eric V Carelli

Thomas J Gordon

Lawrence Lee Ross

Nicholas D'Amico

Chris Harrison

Aspects of the invention related to a system for providing advance notice of impending contact between a stationary component and a rotating component in a turbine engine. For example, the system can be used to warn of potential contact between a seal holder and a rotor disk in the compressor section of the engine. In one embodiment, a pad or other component can be provided on the stationary seal holder. If the seal holder and the rotor disk approach each other during operation, the pad can contact the rotor disk prior to actual contact between the seal holder and the rotor disk. An optical and/or an acoustic signal can be generated by such contact. The signals can be detected remotely from the point of contact by a signal detection device, thereby avoiding the need to pass wires through the compressor section.

Warning system for turbine component contact

A pressure sensor () for a harsh environment such as the combustion chamber () of a gas turbine engine (). The pressure sensor includes an acoustic waveguide () having a sensing portion () exposed to the combustion gas in the combustion chamber. Modulations in an acoustic signal passing through the acoustic waveguide are sensed and correlated to pressure fluctuations in the combustion gas. The sensing portion of the waveguide includes a core acoustic waveguide element () covered by a coating material (). The coating material not only protects the core from the harsh environment, but it also improves the efficiency of the transfer of energy from the combustion gas into the waveguide because it provides a stepped transition from the acoustic impedance of the gas to the acoustic impedance of the core material. The protective coating may have a plurality of layers () and/or it may include a graded material () having an acoustic impedance value that varies across its depth.

Apparatus for sensing pressure fluctuations in a hostile environment

A gas turbine engine ( ) wherein combustion conditions are controlled as a function of the humidity of the ambient air ( ) in order to ensure stable, emission-compliant performance over a range of ambient conditions. The pilot fuel fraction supplied to a dual mode combustor ( ) may be controlled to be responsive to the relative humidity or the specific humidity of the ambient air. Humidity may be measured directly or it may be calculated as a function of other temperature and pressure measurements. A fuel system ( ) is controlled by a controller ( ) having as inputs the signals from one or more of a relative humidity sensor ( ), a barometric pressure sensor ( ), a wet bulb temperature sensor ( ) and a dry bulb temperature sensor ( ).

Humidity compensation for combustion control in a gas turbine engine

A combustion turbine with a secondary combustor is provided. The secondary combustor is disposed within the turbine assembly of the combustion turbine. The secondary combustor assembly is structured to maintain the working gas at a working temperature within the turbine assembly. The secondary combustor assembly re-heats the working gas by injecting a combustible gas into the working gas. The secondary combustor assembly includes a plurality of openings disposed among the vanes and/or blades in the turbine assembly which are coupled to a combustible gas source. As the combustible gas is injected into the working gas, the combustible gas will auto-ignite. That is, the combustible gas will combust without the need for an igniter or pre-existing flame. Combustion of the combustible gas in the turbine assembly re-heats the working gas.

Reheat combustor for gas combustion turbine

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Pittsburgh, PA, United States of America

Richard D Holm