Siemens Aktiengesellschaft

John M Crane

Anthony L Schiavo

Bernd Prade

Werner Krebs

Jens Kleinfeld

Muzaffer Sutcu

Danning You

Mouna Lamnaouer

Kagan Özkan

A transition duct assembly has a plurality of transition ducts (). Each transition duct has a tubular main body and has a flange portion provided at a downstream end of tubular main body (). There is a gap between neighboring flanges. A plurality of seals seal the gaps between the flange portions () of neighboring transition ducts (). Each seal () is received in two opposing receiving channels () formed in side edges () of neighboring flange portions (). Each seal is a one-piece and bent elongate spring steel strip.

Transition duct assembly

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

A combustor in a gas turbine includes a liner having an interior volume defining a main combustion zone, a fuel injection system for delivering fuel into the main combustion zone, and a flow sleeve that defines, with the liner, a passageway for air to flow on its way to be mixed with fuel from the fuel injection system, wherein the mixture is burned in the main combustion zone to create hot combustion gases. The combustor further includes a flow conditioner including at least one panel having a configuration such that air is able to pass through the panel(s) on its way to the passageway, wherein at least a substantial portion of the air that enters the passageway for being burned in the main combustion zone passes through the panel(s).

Flow conditioner in a combustor of a gas turbine engine

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Oviedo, FL, United States of America

John M Crane