Alstom Technology Limited

Other

Alstom

Ansaldo Energia Switzerland Ag

Ansaldo Energia IP UK Limited

Yamane, Ryan Sadao

Gregory, Brent Allan

Regele, Jonathan David

Toqan, Majed

Cps-holding Limited

Majed Toqan

Brent Gregory

Ryan Sadao Yamane

Jonathan David Regele

Peter Flohr

Adnan Eroglu

Bruno Schuermans

Srivats Srinivasachar

Vassilios Burdis

Timothy Albert Griffin

Hans Wettstein

Martin Zajadatz

Marcel Stalder

Shin Gyoo Kang

Gianfranco Ludovico Guidati

Ken-Yves Haffner

Alexander Ni

Enrico Malfa

Valter Bellucci

Jörg Pross

Christian Joerg Motz

Prabhat Naredi

Frank Steege

Reinhard Schurian

Krzysztof Kietlinski

Naji Amira

Stefan Tschirren

Brent Allan Gregory

A method includes providing a furnace including a radiant heating zone having metal heating coils and burners, concurrently applying a combustion media, having a combustibility, and a diluent to the burners, the burners burning the combustion media producing flames heating the radiant heating zone, and the diluent reducing the combustibility of the combustion media for reducing heat generated by the flames for reducing heat degradation of the metal heating coils.

Furnaces and methods of reducing heat degrading of metal heating coils of furnaces

A combustion device used in gas turbine engines to produce propulsion or rotate a shaft for power generation includes a can-annular combustor with a system of fuel and air inlet passages and nozzles that results in an optimal combustion environment of premixed fuel and air. The fuel-air inlets are placed at various longitudinal locations and circumferentially distributed, and direct the flow tangentially or nearly tangent to the can liner. The combustion device provides effective mixing of fuel and air, creates an environment for combustion that reduces pollutant emissions, reduces the need for costly pollution control devices, enhances ignition and flame stability, reduces piloting issues, and improves vibration reduction.

Can-annular combustor with premixed tangential fuel-air nozzles for use on gas turbine engines

A combustion device used in gas turbine engines that produces propulsion or rotates a shaft for power generation includes an annular combustor with a system of fuel and air inlet passages and nozzles that results in a flameless combustor, such that there is not an anchored flame as in typical gas turbine combustors. The fuel and air inlets are placed at various longitudinal locations and circumferentially spaced, and take on several different configurations where some nozzles inject only air and others inject a rich fuel-air mixture. The combustion device provides an optimal mixing of fuel and air as well as creates an environment for combustion that reduces pollutant emissions reducing the need for costly pollution control devices, and enhances ignition and flame stability, reduces piloting issues and improves vibration reduction.

Tangential and flameless annular combustor for use on gas turbine engines

A combustion device used in gas turbine engines to produce propulsion or rotate a shaft for power generation includes an annular combustor with a system of fuel and air inlet passages and nozzles that results in a staged combustion of premixed fuel and air. The fuel and air inlets are placed at various longitudinal locations circumferentially, and can take on different configurations where all nozzles inject a fuel-air mixture or some may inject only air. The combustion device provides an optimal mixing of fuel and air, creates an environment for combustion that reduces pollutant emissions reducing the need for costly pollution control devices, enhances ignition and flame stability, reduces piloting issues, allows increased fuel flexibility, decreases the required size of the first stage nozzle guide vane (NGV), and improves vibration reduction.

Tangential annular combustor with premixed fuel and air for use on gas turbine engines

A combustion device used in gas turbine engines includes an annular combustor that contains the combustion process of air and fuel and then guides the hot gas products to a first stage turbine subsection of a gas turbine engine. The annular combustor has an inner/outer shell having corrugated surfaces that extend radially outward and inward across an entire hot gas stream inside the annular combustor. The corrugations twist about the engine centerline in a longitudinal direction of travel of the engine. The resulting flow path accelerates and turns the hot gas stream to conditions suitable for introduction into the first stage turbine blades, which eliminate the need for first stage turbine vanes. The annular combustor is configured with a system of fuel and air inlet passages and nozzles that results in a staged combustion of premixed fuel and air.

Tangential combustor with vaneless turbine for use on gas turbine engines

A combustion device used in gas turbine engines to produce propulsion or rotate a shaft for power generation includes a can-annular combustor with a system of fuel and air inlet passages and nozzles that results in an optimal combustion environment of fuel and air. Fuel, air and/or fuel-air inlets are placed at various longitudinal locations and circumferentially distributed, and direct the flow tangentially or nearly tangent to the can liner. The combustion device provides an optimal mixing of fuel and air, creates an environment for combustion that reduces pollutant emissions, reduces the need for costly pollution control devices, enhances ignition and flame stability, reduces piloting issues, and improves vibration reduction.

Can-annular combustor with staged and tangential fuel-air nozzles for use on gas turbine engines

A gas turbine installation (), in particular in a power plant for generating electricity, includes a turboset () having a turbine (), a compressor () and a combustion chamber () arranged in a gas path () connecting the compressor () to the turbine (), and a flue gas recirculation device (), which passes combustion flue gas from the turbine () from a flue gas path () connected to the turbine () via a recirculation path () to a fresh gas path () connected to the compressor (). To improve the efficiency of the gas turbine installation (), a control device () controls a volumetric flow and/or a temperature of the recirculated combustion flue gases in such a way that a fresh gas/flue gas mixture which enters the compressor () is at a predetermined desired temperature.

Gas turbine installation

The invention relates to a burner for premix-type combustion having a cavity which has at least one tangential air inlet slot for the supply of a combustion air flow, a device for the injection of fuel into the cavity which is provided in the region of a burner axis, and a device for the injection of premix fuel into the air inlet slots which is provided centrally in the inflow region of the combustion air flow. The device for the injection of premix fuel into the air inlet slots has at least one fuel supply, the fuel outlet openings of which are arranged in such a way that the premix fuel is introduced into the combustion air flow on both sides of the at least one fuel supply related to a cross-sectional plane at right angles to the burner axis.

Burner for premix-type combustion

A combustion chamber (), in particular in a gas turbine, has at least two burners (A-H) that are connected to a fuel supply () via controllable fuel valves (' and). Each burner (A to H) is assigned at least one optical measuring device () for detecting chemiluminescent radiation, and the combustion chamber () is assigned a pressure sensor () for detecting a combustion chamber pressure. The optical measuring device () and the pressure sensor () are connected to a computing and control device, which calculates a correlation value from the incoming measured values. A high correlation value signifies that the associated burner is prone to pulsation. The computing and control device () is designed in such a way that it determines the burner or a burner group with the highest correlation and controls the associated fuel valve(s) in such a way that more fuel is fed to the respective burner or the respective burner group, and the pulsation tendency thereof is thereby reduced.

Combustion chamber

What are described are a multiple burner arrangement and a method for operating such a multiple burner arrangement with a multiplicity of individual burners which are designed as premix burners and which serve for firing a combustion chamber of a thermal engine and each have a swirl space into which combustion supply air and fuel can be introduced so as to form a swirl flow, the swirl flow forming downstream of the premix burner, within the combustion chamber, a backflow zone in which a burner flame is formed.

Multiple burner arrangement for operating a combustion chamber, and method for operating the multiple burner arrangement

A burner () for a combustion chamber of a gas turbine, especially in a power plant, includes an oxidizer feed device () for feeding a gaseous oxidizer into a mixer chamber () of the burner (), a gaseous fuel feed device () for feeding a gaseous fuel into the mixer chamber (), and a liquid fuel feed device () for feeding a liquid fuel into the mixer chamber (). In order to improve the operation of the burner () with liquid fuel, the liquid fuel feed device () has a main feed line () which feeds liquid fuel to a plurality of injection orifices (). Some of these injection orifices (), with regard to a main outflow direction () of the burner (), which has an oxidizer-fuel mixture, which flows from the mixer chamber (), at an outlet opening () of the mixer chamber (), are arranged in series. Some or all of these injection orifices () are designed so that a main injection direction () of the respective injection orifice () has a radial component which extends radially to the main outflow direction ().

Premix burner for a gas turbine combustion chamber

In a combustor () for a gas turbine, the combustor () includes a burner system () and a fuel supply system (). The burner system () includes at least two burner groups (A, B) each with at least one burner (). The fuel supply system () includes a main line (), which is connected to a fuel source (), and also an auxiliary line () for each burner group (A, B). Each auxiliary line () is connected to each burner () of the associated burner group (A, B) and is connected to the main line () by a controllable distribution valve (). A sensing system () measures pressure pulsation values and/or emission values for each burner group (A, B). A control system (), in dependence upon the pulsation values and/or the emission values, controls the distribution valves () so that in each burner group (A, B) the pulsation values and/or the emission values assume and/or fall below predetermined threshold values.

Combustor for a gas turbine

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 method of producing cement clinker and electricity, cement raw mix and hydrocarbon are fed in a circulating fluidized bed boiler ( ). Therein cement raw mix is calcined and steam is produced. Gas and solids out of the fluidized bed enter a cyclone ( ), the solids being separated therein and returned to the bed. Part of those solids are first cooled down in a solids heat exchanger ( ) producing steam. Fly ash consisting predominantly of lime and gas escaping the cyclone are passed through a heat exchanger ( ) and a filter ( ). Hot bed material is discharged from the circulating fluidized bed and is ground with additives, then blended with lime being separated in the filter ( ), then supplied to a rotary kiln ( ), wherein the solids are clinkered. The produced steam is fed to a steam turbine island ( ).

Method of producing cement clinker and electricity

A method of producing a calcined raw meal and of producing additional steam in an existing steam generator comprises the following steps: pulverized raw meal, hydrocarbon, primary air and secondary air are fed to a calciner system ( ), wherein the raw meal is calcined in a temperature range between 850&deg; C. and 950&deg; C., the calcined raw meal is separated from the calciner flue gases at the exit of the calciner system, the calcined raw meal is directed through a cooler ( ), in which it exchanges its heat with the secondary air, the calciner exhaust gases are directed in the gas path of the backpass of the steam generator ( ) at an appropriate temperature window and are used for steam production. The raw meal consists mainly of limestone (CaCO ) and the calcined material is mainly lime (CaO). The fuel feed ( ) to the steam generator ( ) is reduced during introduction of the exhaust gases into its backpass.

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Abu Dhabi, United Arab Emirates

Majed Toqan