Abb Research Ltd.

Abb Management Ag

Asea Brown Boveri Inc.

Abb Alstom Power (switzerland) Ltd.

Asea Brown Boveri Ag

Klaus Dobbeling

Hans Peter Knopfel

Thomas Sattelmayer

Christian Steinbach

Wolfgang Polifke

Adnan Eroglu

Thomas Ruck

Timothy Albert Griffin

Dieter Winkler

Peter Senior

Bettina Paikert

Peter Jansohn

Jurgen Haumann

Lothar Reh

Andreas Pfeiffer

Martin Valk

Armin Heger

Yunhong Wang

Thomas Sattelamayer

Johannes Santner

Donald Frank Walker

Christian Paschereit

In an annular combustion chamber for a gas turbine, a combustion-chamber dome (14) is arranged upstream of an air-cooled combustion chamber (10). A first portion of an air flow (46) which comes from the compressor is admixed as combustion air to the combustion operation and cooling ducts (22; 24) feed a second portion of the air flow (46) coming from the compressor as cooling air into the combustion chamber (10). In this case, the cooling ducts (22; 24), which run at least in sections along the combustion chamber (10), have an entry (23; 25) into the combustion-chamber dome (14). The cooling ducts (22; 24) are designed for damping combustion-chamber oscillations in such a way that the acoustic impedance at the entry (23; 25) of the cooling ducts (22; 24) into the combustion-chamber dome (14) is minimized.

Arrangement for damping combustion-chamber oscillations

In a burner for operating a heat generator, which burner essentially comprises a swirl generator (100), a transition piece (200) arranged downstream of the swirl generator, and a mixing tube (20), transition piece (200) and mixing tube (20) form the mixing section of the burner, this mixing section being arranged upstream of a combustion space (30). In the region of the tangential combustion-air-directing inflow ducts (101b-104b), fuel-directing ducts (121-124), the cross section of flow of which is designed for a low-calorific fuel (116), extend along the swirl generator (100). The fuel-directing ducts (121-124) end at a distance upstream of the transition of the tangential inflow ducts (101b-104b) into an interior space of the swirl generator (100), whereby partial mixing between the two media (115, 117) takes place before the mixture flows into the interior space (118). In addition, this setting-back provides sufficient space for other fuel-directing lines (111-114) in this region.

Burner for operating a heat generator

In a burner for a heat generator, having a swirl generator (100) arranged upstream of the combustion zone (30), fuel injection is connected with the combustion air (115), swirled in the swirl generator, in such a way that the injection angle of the fuel jet (105) belonging to the fuel nozzle (104) corresponds approximately to the setting angle of the sectional bodies forming the swirl generator relative to the axis (60) of the burner.

Burner for a heat generator

The object of the invention is to produce a method, for operating a gas turbine installation combustion chamber with liquid fuel, by means of which the NO.sub.X figures obtained when liquid fuel is employed are similar to those for gaseous fuels. The size of the burner is then also reduced. It is also an object of the invention to provide a corresponding appliance for carrying out the method. This is achieved in accordance with the invention in that the liquid fuel (38) is evaporated in at least two steps in a separate evaporative reactor (12). In this arrangement, the liquid fuel (38) is first atomized to a fuel vapor/liquid fuel mixture (61) by direct heat exchange with a first heat exchange medium (21) and is instantaneously evaporated in this process. The evaporation of the remaining residue of the liquid fuel (38) then takes place by indirect heat exchange with a second heat exchange medium (51). For this purpose, an evaporative reactor (12) is arranged vertically upstream of the combustion chamber (2) and is connected to it, which evaporative reactor (12) accommodates, at its inlet end, a dual-fluid nozzle (22) connected both to a liquid fuel line (19) and to a supply line (20) for a first heat exchange medium (21).

Method and appliance for operating a gas turbine installation combustion

In a method of operating a burner of a heat generator, in which the burner essentially includes a swirl generator for a combustion-air flow, a mechanism for injecting at least one fuel into the combustion-air flow, and a number of transition passages for passing a flow formed in the swirl generator into a mixing tube arranged downstream of the transition passages, a predetermined quantity of a second fuel having a good ignition quality is injected into the reaction zone in order to stabilize the combustion in the combustion space.

Method of operating a burner of a heat generator

The invention relates to a two-stage pressure atomizer nozzle with a nozzle body (30) having a mixing chamber (39) which is connected to an outside space via a nozzle outlet bore (33), and with a first feed duct (42) with a feed bore (41) for a liquid (37) to be atomized, through which feed bore said liquid (37) can be fed, free of swirling and under pressure, at least one further feed duct (36) for a portion of the liquid (37) to be atomized or for a second liquid (37') to be atomized opening into the chamber (39), through which feed duct said liquid (37, 37') can be fed under pressure and with swirling. The feed bore (41) of the first feed duct (42) lies on one axis (34) with the nozzle outlet bore (33). It is defined in that the outlet-side diameter (d.sub.a) of the nozzle outlet bore (33) is at most as large as the diameter (d.sub.z) of the feed bore (41) and the length (L) of the nozzle outlet bore (33) is at least twice to at most ten times the outlet-side diameter (d.sub.a) of the nozzle outlet bore (33).

Pressure atomizer nozzle

In a burner for operating a combustion chamber, which burner essentially comprises a swirl generator (100), a transition piece (200) arranged downstream of the swirl generator, and a mixing tube (20), transition piece (200) and mixing tube (20) forming the mixing section of the burner and being arranged upstream of a combustion space (30). The swirl generator (100) itself comprises at least two hollow, conical sectional bodies (140, 141, 142, 143) which are nested one inside the other in the direction of flow, the respective center axes of these sectional bodies running mutually offset in such a way that the adjacent walls of the sectional bodies form inlet ducts (120), tangential in their longitudinal extent, for a combustion-air flow (115). In the region where the combustion-air flow (115) flows into the swirl generator (100), fuel injectors (116, 116a) are arranged on both sides along the inflow edges, which fuel injectors act offset with respect to one another, in such a way that the inflow cross section of the duct (120) is integrally covered with fuel, with the result that a maximized premixing is achieved.

In the case of a ceramic liner for combustion spaces, comprising at least one wall element (3), made of refractory structural ceramic and having at least one through-opening (6), and a fastening element (4), consisting of refractory structural ceramic, per opening (6), the fastening element (4) is resiliently fastened by its foot in a metallic holding device (5) fastened on the metallic supporting wall (1). The head (20) of the fastening element (4) rests in the opening (6) in the wall element (3). The wall element (3) is designed in the form of a box, having a base (25) which runs parallel to the metallic wall (1), having an inside wall (23) which surrounds the opening (6) in an annular manner and is supported directly or indirectly on the metallic supporting wall (1), and having outside walls (24) which extend up to the metallic supporting wall (1) without touching the latter.

Ceramic liner

In a burner for operating a combustion chamber, which burner essentially comprises a swirl generator (100) and a mixing section (220) arranged downstream of the swirl generator, this mixing section acting upstream of a combustion chamber (30), the swirl flow induced by the swirl generator (100) is directed via transition passages (201) into the mixing section (220). At the outlet of a mixing tube (20) belonging to the mixing section (220), the burner front (70) of the mixing tube (20) is provided with at least one torus-like notch (71) on the combustion-chamber side. Thus the stability of the backflow zone (50) can be intensified, which has a positive effect on the combustion from all aspects.

Burner for operating a combustion chamber

In the case of a method for operating a gas turbine group, the gas turbine group essentially consists of a compressor (1), a combustion chamber (5), a turbine (2) and a generator (3). Fuel is mixed in a premixer (18) of the combustion chamber (5), prior to the combustion, with air compressed in the compressor (1), and subsequently burned in a combustion space (19). Compressed air, fed via an air line element (15) , is mixed with fuel fed via a fuel line element (16) and delivered to a reactor (10) having a catalytic coating. The air/fuel mixture is converted in the reactor (10) into a synthesis gas comprising hydrogen, carbon monoxide, residual air and residual fuel and this synthesis gas is injected into the zones of the combustion chamber (5) where the flame is stabilized.

Method for operating a gas turbine group with catalytic gas generator

A pressure atomizer nozzle comprises a nozzle body (30) in which is formed a turbulence and/or swirl chamber (39) and having a nozzle bore (33). At least one first feed channel (41, 41a) for the liquid (37) to be atomized connects to the chamber as a first feed stage for feeding said liquid (37) under pressure. At least one second feed channel (38) connects to the chamber as a second feed stage for feeding part of the liquid (37) to be atomized or for feeding a second liquid (37') to be atomized. The second feed channel feeds liquid into the chamber under pressure and with a swirl. The two stage pressure atomizer nozzle allows, for example, simple adaptation of the fuel spray cone angle to the respective operating conditions of a gas turbine burner.

In a burner of the double-cone design for burning liquid (12) and gaseous fuels (16), the at least two sectional cone bodies (1, 2) overlap at least partly, the overlap angle (.delta.) increasing in the direction of flow of the burner, and the distance between the fuel injectors (15) and the air-inlet plane (21) into the burner increasing simultaneously with the increase in the overlap angle (.delta.). As a result, the air-inlet plane (21) and the fuel-injection plane (22) no longer coincide. Improved premixing of the gaseous fuel (16) with the combustion air is achieved by the invention, which leads to lower NOx emissions of the burner and to lower thermal loading of the burner front.

Burner

In a method of operating a plant with staged combustion, the first combustion stage (1a) is operated with a fuel/air mixture (3) whose air coefficient is larger than the overall air coefficient of the combustion system. The hot combustion gases (5) from the first combustion stage (1a) are mixed with an additional fuel/air mixture (4) whose air coefficient is smaller than the overall air coefficient of the combustion system, before the further combustion in the second stage (2a) takes place. Since hot-gas backmixing is no longer required in the second stage (2a) for the flame stabilization, this combined mixture burns without the formation of further NOx emissions.

Method of operating a plant with staged combustion

In a combustion chamber of a gas-turbine group which essentially comprises a mixing section (2) for premixing an air/fuel mixture (16) and a downstream combustion space (3), a jump (5) in cross section is provided at the transition between the two said flow sections (2/3). This jump (5) in cross section induces the cross section of flow of the combustion space (3) and at the same time forms outer recirculation zones (10) in the combustion space (3). Flow passages (4) branch off in the end phase of the mixing section (2), which flow passages (4) then lead into the outer recirculation zones (10). A portion (9) of the air/fuel mixture flows out of the mixing section (2) through these flow passages (4) and into the outer recirculation zones (10), the portion being enriched here with an additional fuel (6). This fuel (6) is introduced via a circular line (19) provided with bores (18). The branched off mixture (9) constitutes a self-igniting pilot flame in the outer recirculation zones (10), which pilot flame substantially stabilizes the flame front (20).

Combustion chamber

In a gas-turbine annular combustion chamber (4) which is arranged downstream of a compressor (1) and is equipped on its front plate with at least one row of premix burners (5) arranged in an annular form, in each case a combustion-air duct (15) designed as a diffuser leads directly downstream of the compressor outlet from the guide vanes (9) of the last compressor row to each burner (5), at the downstream end of which combustion-air duct (15) at least one longitudinal-vortex generator (16) is located, at least one fuel injection means (17) being provided in or downstream of the longitudinal-vortex generator (16). A mixing duct (19) which ends in the combustion chamber (4) and has a constant height (H) and a length (L) which corresponds approximately to twice the value of the hydraulic duct diameter (D) is arranged downstream of the fuel injection means (17). The overall size of the gas turbine in the region of the combustion chamber (4) can thereby be substantially reduced. In addition, the pressure loss between compressor outlet and turbine inlet is reduced.

Growing community of inventors

Windisch, Switzerland

Klaus Dobbeling