Alstom Technology Limited

Asea Brown Boveri Ag

Alstom

Marcel Stalder

Franz Joos

Dieter Rebhan

Urs Benz

Jaan Hellat

Majed Toqan

Hans Peter Knoepfel

Pirmin Schiessel

Daniel Burri

Thomas Kueenzi

Guenter Sybon

G&uuml;nter Sybon

A gas turbine uses a first fuel at full load and an improved emission behavior is achieved by operating the gas turbine () at partial load with a second fuel, which has a richer mix of higher-value hydrocarbons (C2+) with 2 and more carbon atoms per molecule like ethane (CH) and propane (CH).

Gas turbine system for injecting a mixture of high value hydrocarbons plural distinct fuels into the gas turbine combustion chamber

A method for operating a gas turbine uses a first fuel at full load. An improved emission behavior is achieved by operating the gas turbine () at partial load with a second fuel, which has a richer mix of higher-value hydrocarbons (C2+) with 2 and more carbon atoms per molecule like ethane (CH) and propane (CH).

Method for operating a gas turbine and gas turbine system for carrying out the method

In a method for igniting the combustion chamber of a gas turbine unit, a safely working ignition and a long lifetime of the ignition device () is achieved by discharging a compressed gas with a supercritical pressure ratio through a nozzle () and heating it up to a temperature sufficient to ignite hydrocarbons by interacting with a resonance tube () arranged behind said nozzle (), and using said heated-up gas to directly or indirectly ignite a fuel/air mixture introduced into said combustion chamber.

Method for igniting the combustion chamber of a gas turbine unit and an ignition device for carrying out the method

A burner () for heat generation, in particular in a gas turbine, is disclosed as well as a method for the stabilization of the flame of a burner (). The burner () comprises inlet openings () for a combustion air stream, at least a swirl generator () for the combustion air stream and one or more first fuel supplies () with first fuel outlet openings () for injection of fuel into the combustion air stream. At least one resonance tube () with an open () and an essentially closed end () is arranged in or at the burner (), whose closed end () is positioned in the region of a flame front () which forms during operation of the burner () on the side of the burner (). An outlet opening () of a supply () for a compressible medium is arranged at the open end () of the resonance tube (). By injection of the compressible medium into the resonance tube () when flame pulsation occur, the compressible medium periodically enters and leaves the resonance tube () through the open end (), by which the closed end () of the resonance tube () heats up. This heating up stabilizes the flame.

Burner

In a thermal turbomachine with a housing, a combustion chamber, an ignition device, a fuel supply, and an air supply, the ignition device includes an ignition space and an igniter arranged in the ignition space. The fuel supply and the air supply open into the ignition space. The ignition space is connected to the combustion chamber, and the ignition device is arranged outside the housing of the thermal turbomachine. A process is shown for the ignition of the thermal turbomachine outside the housing.

Thermal turbomachine and process for igniting the thermal turbomachine

In a method for igniting a thermal turbomachine, the turbomachine containing a combustion chamber ( ), an ignition device ( ), a fuel supply ( ) and an air supply ( ), and the ignition device ( ) consisting of an ignition space ( ) and of an ignitor ( ) arranged in the ignition space ( ), the fuel supply ( ) and the air supply ( ) discharging into the ignition space ( ), and the ignition space ( ) being connected to the combustion chamber ( ) via a flame tube ( ), prior to the ignition of the combustion chamber ( ), an overall fuel/air mixture ratio &PHgr; &equals;1/&lgr; greater than 1, with &lgr; being the overall air ratio, is set in the flame tube ( ) of the ignition device ( ).

Method for igniting a thermal turbomachine

A method for running up a gas turbine plant ( ) is disclosed. In the method, a fuel ( ) is injected into the combustion chamber ( ) via a plurality of pilot burners ( ) and premix burners ( ). During the start-up and in a lower load range, the combustion chamber ( ) is operated in the pilot mode, and, at a specific time point, the combustion chamber ( ) is changed over from the pilot mode to the premix mode. The changeover time point from the pilot mode to the premix mode depends on a variable changeover temperature (T ), and this changeover temperature (T ) is determined from pulsations occurring in the flame of the combustion chamber ( ).

Method for running up a gas turbine plant

A combustion chamber includes a mixing zone and a combustion zone within which self-ignition of a fuel and air mixture can occur. Fuel and support air are injected laterally at the sidewall of the mixing zone into hot gases passing through the mixing zone. The operating range of the combustion chamber can be increased while noxious substances are reduced by injecting differently controlled fuel/support air mixture jets into different target spaces within the mixing zone.

Method for operating a combustion chamber

A damping device for reducing the vibration amplitude of acoustic waves and a burner for operating an internal combustion engine, the burner having a mixing region, in which an air flow and a fuel flow are mixed with one another to form an air/fuel mixture, and a combustion chamber, which in the direction of flow of the fuel/air mixture is arranged downstream of the mixing region, in which the fuel/air mixture can be ignited. A Helmholtz resonator directly connected to the mixing region of the burner such that acoustic waves formed in the burner are suppressed in the Helmholtz resonator and are not reflected back into the burner.

Damping device for reducing the vibration amplitude of acoustic waves for a burner

In an ignition appliance for a heat generator, the supply lines for air (,) and fuel gas (,) are led directly into a flame tube (,). The igniter (,) is arranged in an ignition space (,) remote from the flame tube (,) and connected to the flame tube (,). The ignition space (,) is connected to the air supply passage (,) and the gas supply passage (,) via connecting ducts (,). If the supply passages for air and fuel gas (,) are dimensioned so as to be sufficiently large, the pressure drop between the inside of the ignition space (,) and the feed lines (,) is small. The fuel/air ratio present at the igniter (,) is therefore essentially determined only by the ratio of the cross sections of the connecting ducts (,). The flow relationships in the ignition space (,) are likewise substantially decoupled from the air and fuel gas flows supplied overall to the ignition appliance. In consequence, good conditions for a reliable ignition can be set over a wide operating range of the ignition appliance.

Ignition appliance for a heat generator

The invention is directed to a method of operating a burner. The method includes feeding an auxiliary gas into a liquid fuel upstream of an injection orifice during the ignition and during part load of the burner, and interrupting the feeding of the auxiliary gases within high load ranges of the burner.

Method of operating a burner

In an airblast atomizer nozzle (2) for the operation of a burner (1) operated with liquid and gaseous fuels (4, 6) the intermediate wall (18) between the inner (14) and outer (13) air duct is held via inner and outer support elements (21) which have a sliding fit (28) and which can be designed as swirl vanes. The atomizer edges (19) of the airblast nozzle (2) are angled in the direction of the nozzle axis (11). The nozzle is distinguished by small dimensions, a low pressure loss and a negligible tendency to coking.

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Klingnau, Switzerland

Marcel Stalder