General Electric Company

General Electric Technology Gmbh

Ansaldo Energia Switzerland Ag

Ansaldo Energia IP UK Limited

Pirmin Schiessel

Adnan Eroglu

Jaan Hellat

Bruno Schuermans

Ennio Pasqualotto

Norbert Walter Emberger

Piotr Siewert

Martin Zajadatz

Hellat Jaan

Andreas Jan Schesny

Zdenko Papa

Rainer Conzelmann

Daniel Haeny

Luca Tentorio

Thomas Christen

Rajeshwor Dhital

Torsten Lüddecke

An annular combustor includes an inner liner shell and an outer liner shell defining an interior volume through which combustion gases flow in a gas flow direction from a forward end to an aft end. A cooling shroud is attached radially outward of the inner liner shell, forming a cooling passage between the inner liner shell and the cooling shroud. The cooling passage directs air in an air flow direction opposite to the gas flow direction. The cooling shroud is assembled from circumferentially adjoined cooling shroud segments, and the distance between the cooling shroud segments and the inner liner shell is greater at the forward end than at the aft end. Fastening elements are distributed across an axial length of the cooling shroud segments in circumferentially staggered rows. Each forwardmost fastening element is disposed immediately adjacent to a curved portion at the forward end of each respective cooling shroud segment to reduce vibration.

Inner cooling shroud for transition zone of annular combustor liner

A combustor arrangement includes a combustion chamber with a front panel, and a premix burner of the multi-cone type, which is connected to the front panel through an elongated mixing zone in an axially moveable fashion by a sealed sliding joint. A wide range of axial variation of the burner with a minimized influence of the leakage air flow on the oxidation process within the flame is achieved by positioning the sealed sliding joint upstream of the mixing zone.

Combustor arrangement with slidable multi-cone premix burner

The burner of a gas turbine includes two or more part cone shells arranged offset with respect to one another and defining a cone shaped chamber with longitudinal tangential slots for feeding air therein. A lance carrying a liquid fuel nozzle arranged centrally in the cone shaped chamber is also provided. A portion of the nozzle facing the cone shaped chamber is divergent in shape. A diffuser angle (&#x3b1;) between the wall of the nozzle and a longitudinal axis of the cone shaped chamber is less than 5&#xb0;. A diverging portion of the nozzle has a diffuser length to nozzle diameter ratio comprised between 2-6. The nozzle diameter is the smaller diameter of the diverging portion.

Burner of a gas turbine

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Ehrendingen, Switzerland

Pirmin Schiessel