Bbc Brown, Boveri & Company, Limited

Asea Brown Boveri Inc.

Bbc Brown Boveri Ag

Abb Research Ltd.

Abb Management Ag

Jakob Keller

Thomas Sattelmayer

Jakob J Keller

Rolf Althaus

Cornel Fuglistaller

Marcel Escudier

Thomas Duerig

Daniel Styner

Robert E Breidenthal

Peter Senior

Baldur Eliasson

Michael Hirth

Jurgen Haumann

Jean Hellat

In the combustion chamber of a gas turbine, at least one premixing burner (110) is arranged in a dome (51) communicating with a plenum (50). Said premixing burner (110) is fastened on the outlet side to a front plate (52) limiting the combustion space (58) of the combustion chamber. The premixing burner procures the combustion air from the dome. The fuel injected via nozzles is intensively intermixed with the combustion air within a premixing space of the burner prior to ignition. There is provided a jet injector (53) which opens into the dome (51) and of which the central nozzle (54) is connected to the combustion space (58) via an orifice (55) in the front plate (52) and of which the annular space (56) surrounding the central nozzle is loaded with a propellant.

Combustion chamber with premixing burner and jet propellent exhaust gas

A premixing burner includes a pilot burner formed from two half conical shells and a plurality of main burners arranged around the pilot burner. Each of the main burners is formed with an cylindrical outer wall to contain a main flow. Each of the main burners includes a plurality of vortex generators arranged inside the cylindrical wall about a circumference. In addition, a venturi nozzle is disposed in each of the main burners downstream of the vortex generators. A fuel lance for each of the main burners injects one or both of a gaseous and liquid fuel into the burner as a secondary flow, and an outlet of the lance is positioned to inject the secondary flow in the region of the venturi nozzle having a maximum constriction.

Premixing burner

In a secondary burner for a gas turbine combustion chamber, a fuel feed (2, 3) arranged in a combustion chamber wall (1) is surrounded by an annular air duct (4). The air duct (4) communicates, by means of at least one supply tube (5), with a through-flow Helmholtz resonator (6). The outlet from the Helmholtz resonator damping tube (7), which is configured as an annular duct, is located in the region of the burner mouth (8) in the secondary combustion space (9).

Secondary burner having a through-flow helmholtz resonator

A combination of pre-mixing burners and catalytic supported and preferably gas-operated burners is disposed in a combustion chamber for gas turbines, wherein the main combustion is performed by the pre-mixing burners. The pre-mixing burners and the catalytic burners are embodied to be interchangeable. The catalytic burners are provided with an exhaust gas return, wherein the exhaust gas is preferably taken from the combustion chamber. The inlet for the combustion air for the catalytic burners is embodied as a jet pump, which aspirates the exhaust gas from the combustion chamber.

Combustion chamber of a gas turbine having premixing and catalytic

In a gas turbine combustion chamber which surrounds the rotor as an annulus and therefore has the shape of an annular combustion chamber, the front wall (10) is equipped with a number of burners whose ends occupy a uniform plane. These burners form a double ring (10b, 10c) on the front wall (10). In each ring, the same direction of rotation is present in the burners and this is opposite to the adjacent ring. In addition, two burners at a time are alternately displaced outwards and inwards in each ring in order to achieve a favorable flow field for combustion. The number of burners on the front wall (10) is divided into a larger quantity of piloting burners (A1, A2 ) and a smaller quantity of piloted burners (B1, B2).

Gas turbine annular combustion chamber having radially displaced groups

A device for mixing two gaseous components, particularly in the context of a burner in which it is desired to mix the two gaseous components prior to combustion. The device includes a tangential inlet flow duct which opens into an inlet flow gap. A first gaseous component flows in through this inlet flow gap, and a second gaseous component flows through inlet flow nozzles provided in the region of the inlet flow gap. The arrangement achieves particularly intimate mixing, such that an improved burner is provided. Ramps are disposed in the region of the inlet flow duct, with the ramps including an end having a separation edge in the inlet flow gap. The inlet flow nozzles are arranged in the region around the separation edge such that mixing is promoted by longitudinal vortices occurring in the region.

Device for mixing two gaseous components and burner in which this device

This gas turbine arrangement has an at least two-stage gas turbine (1) with a main combustion chamber (10) and a compressor (5). An energy exchanger (8) which interacts with the separate combustion chamber (14) is installed upstream of the gas turbine (1). The efficiency of the gas turbine arrangement is to be increased by simple means. In order to achieve this, the separate combustion chamber (14) is designed as an afterburner chamber for a part of the gases generated in the main combustion chamber (10). In addition, means for the additional injection of a liquid or vapor medium are provided in the region of the combustion chamber (14). The volume flow in the energy exchanger (8) and hence the efficiency of the gas turbine arrangement are increased by this injection.

Gas turbine arrangement

This gas turbine arrangement has a gas turbine which can be divided into a high-pressure part and a basic part and has a compressor (1) and at least one energy exchanger (7). In addition, it has a combustion-chamber arrangement and a separate combustion chamber (18) connected upstream of the energy exchanger (7). The intention is to provide a gas turbine arrangement in which an increased efficiency is achieved by simple means and which can be regulated more simply. This is achieved by providing at least two combustion chambers (9, 10) for the combustion-chamber arrangement. The first (9) of the combustion chambers cooperates with the high-pressure part of the gas turbine arrangement. The second (10) of the combustion chambers cooperates, via the interposed energy exchanger (7) having the upstream combustion chamber (18), with the basic part.

A series of premix burners of different sizes are arranged at the inlet flow end of a combustion chamber, preferably of the form of an annular combustion chamber. The large premix burners, which are the main burners of the combustion chamber, and the small premix burners, which are the pilot burners of the combustion chamber, emerge into a front wall of the combustion chamber, these premix burners being arranged alternately relative to one another and at a constant distance apart. The main burners emerge directly into the front wall to the combustion space and the pilot burners have, downstream of their burner length, a precombustion chamber extending as far as the front wall. Both the evaporation of a liquid fuel and the burn-out of liquid or gaseous fuels in the low part-load range of the machine can be decisively improved in this precombustion chamber.

Combustion chamber of a gas turbine including pilot burners having

In a method for preparing the working gas in a gas turbine installation, the air prepared by a compressor (1) is mixed, downstream of the compression, with a fuel (4) and then fed to a pressure wave machine (5). This fuel/air mixture fills the revolving rotor cells (11) of this same pressure wave machine (5) in a continuous process. The mixture caught in the rotor cells (11) is then brought to ignition at constant volume. The working gas thus obtained then serves for acting upon a gas turbine (7, 9) placed downstream of the pressure wave machine (5).

Method for preparing the working gas in a gas turbine installation

In premixing-type combustion of liquid fuel in a burner without a premixing section, a conical column (5) of liquid fuel is formed in the interior (14) of the burner, which column widens in the direction of flow and is surrounded by a rotating stream (15) of combustion air which flows tangentially into the burner. Ignition of the mixture takes place at the burner outlet, a backflow zone (6) forming in the region of the burner outlet. The burner itself consists of at least two hollow part-cone bodies (1, 2) which are superposed on one another and have a cone angle increasing in the direction of flow. The part-cone bodies (1, 2) are mutually offset, so that tangential air inlet slots (19, 20) are formed. A nozzle (3) placed at the burner head ensures injection of the liquid fuel (12) into the interior (14) of the burner.

Apparatus for premixing-type combustion of liquid fuel

A burner with a conical shape opening in the flow direction is composed of two partial-conical bodies, which are positioned one upon the other and whose centerlines in the longitudinal direction extend offset relative to one another. Because of this offset, a tangential inlet slot to an internal space of the burner is formed in each case over the length of the burner. The fuel supply takes place centrally via a nozzle and tangentially in the region of the inlet slots via, in each case, a fuel line, which is provided with fuel openings which there undertake the injection of the fuel. A duct is formed above each inlet slot and this is equipped with an injector. A further fuel is introduced through this injector. The air/fuel mixture with fuel from the injector and/or fuel from the fuel line flows generally as an air/fuel mixture through the tangential inlet slots into the internal space of the burner. If needed, further mixing with the fuel from the nozzle takes place there.

Burner

In a combustion chamber (A) of the form of an annular combustion chamber, a row of large and small premixed burners (B, C) are arranged along the annular front wall (10). The large premixed burners (B), which are the main burners of the combustion chamber (A), and the small premixed burners (C), which are the pilot burners of the combustion chamber (A), follow each other alternately and regularly along the front wall (10) where they also emerge into the combustion space of the combustion chamber (A). A plurality of air nozzles (D), whose injection is directed into the combustion space of the combustion chamber (A), are placed between the large premixed burners (B) and the small premixed burners (C).

Combustion chamber of a gas turbine

In a premixing burner, which consists of two hollow partial conical bodies (1, 2), which are positioned on one another and have a cone inclination increasing in the direction of flow, the fuel feed takes place via central fuel nozzle (3) and/or via a plurality of fuel nozzles (17), which are placed along the inflow of the combustion air (15) into the interior (14) of the burner. The combustion air (15) itself is a mixture of fresh air and exhaust gas. The fresh air is led up via a first flow funnel (23a, 23b ) and exhaust gas recirculation takes place via a second flow funnel (22a, 22b). These two gases mix with one another before flowing tangentially into the interior (14). An optimum, homogenous fuel concentration over the cross-section arises in the region of the return flow zone (6).

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Killwangen, Switzerland

Jakob J Keller