Alstom Technology Limited

General Electric Technology Gmbh

Ansaldo Energia Switzerland Ag

Ansaldo Energia IP UK Limited

Thiemo Meeuwissen

Stanka Kokanovic

Susanne Renate Schell

Ghislain Singla

Sebastian Lipari

Theodoros Ferreira-Providakis

Adnan Eroglu

Richard Carroni

Peter Flohr

Rudolf Lachner

Ourania-Nektaria Margari

Jürg Käser

Teresa Marchione

Felipe Bolaños-Chaverri

Peter Althaus

Nektaria-Ourania Margari

Theodoros Providakis

The invention relates to a method for controlling a gas turbine group including, a first combustion chamber, a first turbine connected, a second combustion chamber, a second turbine, and a load. The method includes: measuring a temperature TAT1 at an outlet of the first turbine; determining a ratio S1R of a fuel mass flow feeding a pilot flame of the first combustion chamber to a total fuel mass flow feeding the first combustion chamber based upon the measured temperature TAT1 in accordance with a predetermined mapping table between ratio S1R and temperature TAT1; adopting the larger one between the determined ratio S1R and a predetermined booster ratio S1R to be used in the controlling fuel flow feeding the first combustion chamber of the gas turbine group. Pulsation behavior of the gas turbine group may be improved. High pulsation during fast de-loading of the gas turbine group is substantially is decreased, avoiding potential damage to the parts of the gas turbine group.

Method for controlling a gas turbine group

In a method for the low-CO emissions part load operation of a gas turbine with sequential combustion, the opening of the row of variable compressor inlet guide vanes is controlled depending on the temperatures of the operative burners of the second combustor and simultaneously the number of operative burners is kept at a minimum. This leads to low CO emissions at partial load of the gas turbine.

Gas turbine with improved part load emissions behavior

In a method for switching over a gas turbine plant from gaseous fuel () to liquid fuel () and vice-versa, in which the gas turbine plant includes a first combustor and a second combustor fed with the flue gases of the first combustor, the first and second combustors are sequentially switched over while the other combustor maintains its operating conditions.

Method for switching over a gas turbine plant from gaseous fuel to liquid fuel and vice-versa

A method is provided for switching over a gas turbine burner operation from liquid fuel to gas fuel and vice-versa, with the burner comprising nozzles for feeding a premixed gas fuel, nozzles for injecting a pilot gas fuel and nozzles for injecting a liquid fuel. According to the method, while the liquid fuel and the premix gas fuel are regulated to switch over from liquid fuel to gas fuel operation or vice-versa, the pilot gas fuel is controlled at a substantially constant flow rate.

Method for switching over a gas turbine burner operation from liquid to gas fuel and vice-versa

A gas turbine plant has a compressor (), a first combustion chamber () followed by a high pressure turbine (), a second combustion chamber () and a low pressure turbine (). In the first combustion chamber () a first gaseous fuel () is injected and combusted, generating first hot gases () that are at least partly expanded in the high pressure turbine (), and in the second combustion chamber () a second fuel () is injected in the at least partly expanded hot gases generated in the first combustion chamber () and combusted, generating second hot gases () that are expanded in the low pressure turbine (). In the first combustion chamber () water is also injected to increase the gas turbine plant power output. In the first combustion chamber () a water flow rate is injected compatible with a predetermined flame stability limit. In the second combustion chamber () the flame temperature is regulated to burn the non-combusted products generated in the first combustion chamber () to bring their amount below a predetermined emission limit, without exceeding a predetermined NOemission limit.

Method for operating a gas turbine plant

A reheat combustor for a gas turbine engine includes a fuel/gas mixer for mixing fuel, air and combustion gases produced by a primary combustor and expanded through a high pressure turbine. Fuel injectors inject fuel into the mixer together with spent cooling air previously used for convectively cooling the reheat combustor. The fuel mixture is burnt in an annular reheat combustion chamber prior to expansion through low pressure turbine inlet guide vanes. The fuel/gas mixer and optionally the combustion chamber define cooling paths through which cooling air flows to convectively cool their walls. The fuel injectors are also convectively cooled by the cooling air after it has passed through the fuel/gas mixer cooling paths. The low pressure turbine inlet guide vanes may also define convective cooling paths in series with the combustion chamber cooling paths.

Gas turbine reheat combustor including a fuel injector for delivering fuel into a gas mixture together with cooling air previously used for convectively cooling the reheat combustor

A device and a method for flame stabilization in a burner (), includes a burner housing at least partially enclosing a burner volume, into which may be introduced via at least one fuel line, fuel, and via at least one air feed means, air, forming an air/fuel mixture spreading in a preferred flow direction, which may be ignited in a combustion chamber () connecting downstream of the burner housing to form a stationary flame (). Upstream of the flame (), a catalyst arrangement () is provided through which an air/pilot fuel mixture (), separate from the air/fuel mixture, is flowable. The catalyst arrangement () has at least two catalyst stages which are located one behind the other in the through-flow direction, of which the catalyst stage () located upstream, the so-called POX-catalyst, is flow-washable by the air/pilot fuel mixture () with an air/pilot fuel mixture ratio &#x3bb;&#x3c;1, by which catalyst stage () the air/pilot fuel mixture () is partially oxidized, and of which catalyst stages the downstream catalyst stage (), the so-called FOX-catalyst, is flow-washable by a leaned air/pilot fuel mixture () with a mixture ratio &#x3bb;&#x3e;1, by which the leaned air/pilot fuel mixture is completely oxidized forming an inert hot gas flow ().

Device and method for flame stabilization in a burner

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Ennetbaden, Switzerland

Thiemo Meeuwissen