Alstom Technology Limited

Elisabetta Carrea

Peter Jansohn

Urs Benz

Timothy Albert Griffin

Bogdan Trbojevic

Stevica Furdek

Anna Maria Olsson

A method of dismantling a turbomachine includes opening a turbomachine casing in the region of a combustion chamber, releasing a top half shell from a bottom half shell, axially displacing the top half shell and thereafter removing the top half shell in essentially the radial direction, rotationally fixedly connecting an auxiliary tool to the rotor of the turbomachine, connecting the auxiliary tool to the bottom half shell via axially displaceable adapter slides arranged on said auxiliary tool, axially displacing the bottom half shell to release the bottom half shell from axial connecting contours, rotating the bottom half shell with the rotor by approximately 180&#xb0; until the bottom half shell assumes essentially the position of the removed top half shell, and releasing the bottom half shell and removal of said bottom half shell.

Method of dismantling a portion of a turbomachine

In a method for the combustion of a fuel, a fuel or a premixed combustible mixture is introduced into a combustion space as a combustible fluid open jet. The velocity of the open jet is selected in such a way that it is impossible for a stable flame front to form, i.e. is in any event greater than the flame front velocity, and that, on account of a jet pump effect, flue gas is mixed into the combustible fluid jet from the combustion chamber in a jet-induced recirculation internally within the combustion chamber. The admixed flue gas dilutes and heats the combustible fluid. The heating causes the spontaneous ignition temperature to be exceeded, and a low-pollutant volumetric flame is formed in a highly dilute atmosphere.

Method for combustion of a fuel

A combustion chamberfor a gas turbine that operates in a highly diluted mode of combustion has a substantially toroidal plenum. At least one combustion fluid injector is located at the periphery of the plenum. The shape of the plenum and the disposition of the combustion fuel injectors are such that a vortex flowis established in the combustion chamber in use. Gasses are entrained in the vortex which provides high enough levels of flue gas re-circulation to allow for the onset of highly diluted combustion.

Combustion chamber for a gas turbine

A gas turbine adapted to operate in a highly diluted mode comprises a compressoradapted to compress oxidant; a combustion chamberadapted to accept the compressed oxidantand provide an exit means for flue gas; a turbine; and a flue gas re-circulation meansadapted to re-circulate the flue gasfrom the combustion chamberand mix the said flue gas with the compressed oxidantfrom the compressorin order to provide a highly diluted mode of combustion with a flue gas re-circulation rate of from 100% to 200%.

Gas turbine having exhaust recirculation

A combustion chamberfor a gas turbine that operates in a highly diluted mode of combustion has a substantially toroidal plenumAt least one combustion fluid injector is located at the periphery of the plenum. The shape of the plenum and the disposition of the combustion fuel injectors are such that a vortex flowis established in the combustion chamber in use. Gasses are entrained in the vortex which provides high enough levels of flue gas re-circulation to allow for the onset of highly diluted combustion.

Method of using a combustion chamber for a gas turbine

A combustion chamberfor a gas turbine operates in a highly diluted mode of combustion has a substantially toroidal plenum. At least one combustion fluid injector is located at the periphery of the plenum. The shape of the plenum and the disposition of the combustion fuel injectors are such that a vortex flowis established in the combustion chamber in use. Gasses are entrained in the vortex which provides high enough levels of the gas re-circulation to allow for the onset of highly diluted combustion.

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Zurich, Switzerland

Elisabetta Carrea