EP1062461A1

EP1062461A1 - Combustion chamber and method for operating a combustion chamber

Info

Publication number: EP1062461A1
Application number: EP99913091A
Authority: EP
Inventors: Gerwig Poeschl; Heinrich Pütz; Stefan Hoffmann
Original assignee: Siemens AG
Current assignee: Siemens AG
Priority date: 1998-03-10
Filing date: 1999-02-25
Publication date: 2000-12-27
Anticipated expiration: 2019-02-25
Also published as: JP4365027B2; DE59907940D1; WO1999046540A1; EP1062461B1; JP2002506193A

Abstract

The invention relates to a combustion chamber (1), comprising an inner lining (5) made up of a number of heat shielding elements (6). At least one heat-shielding element (5) which acts as a burner is a burner-heat shielding element (22) upstream of which a supply (30) of fuel (36) and a supply (26) of combustion air (38) are connected.

Description

1 description

Combustion chamber and method for operating a combustion chamber

The invention relates to a combustion chamber with a combustion chamber wall and with an inner lining formed from a multiplicity of heat shield elements, and to a method for operating a combustion chamber.

EP 0 597 137 B1 describes an annular combustion chamber for a gas turbine. The combustion chamber is divided into a primary zone and a secondary zone. The primary zone and the secondary zone each have a flow-limiting wall, which are cooled independently of one another by cooling air. The wall of the secondary zone is double-walled. It connects to the wall of the primary zone, which is formed by a segment support for segments of a refractory lining. The cooling air first flows through the double-walled wall of the secondary zone, then flows through the segment carrier and the segments of the

Primary zone and is finally fed to a burner for combustion.

EP 0 576 697 B1 describes a combustion chamber of a gas turbine in which, in addition to classic burner types, catalytic burners are also used. Premix burners are used as classic burner types, with which the main combustion is carried out. The combination of these burner types results in a simpler regulation in the event of changing load states of the gas turbine.

In the article "Options for Low Emissions" by Richard J. Antos, Low NO _x Gas Turbines, May 1996, page 43, a gas turbine with a two-stage combustion is described. In a primary zone, a first stage of combustion takes place with the aid of a premix burner, which is stabilized by a diffusion burner. To the combustion chamber for the primary 2 zone is followed by a larger combustion chamber for a secondary zone, in which a second stage of combustion takes place. For this purpose, a premixed fuel-air mixture is fed through a number of openings m into the combustion chamber wall at the entrance to the secondary zone. The fuel-air mixture ignites in the hot exhaust gas, which enters the secondary zone from the primary zone. This results in the second stage of combustion.

The object of the invention is to provide a combustion chamber which enables the supply of fuel and combustion air in a particularly simple construction. Another object of the invention is to provide a method for operating a combustion chamber by means of which a staged combustion is made possible in a particularly simple manner.

According to the invention, the task aimed at specifying a combustion chamber is achieved by a combustion chamber with a combustion chamber wall and with an inner lining formed from a multiplicity of heat shield elements, at least one heat shield element functioning as a burner being a burner heat shield element st to which a fuel supply for supplying fuel and a combustion air supply for the supply of combustion air are connected upstream.

In a combustion chamber of this type, combustion is made possible in a structurally particularly simple manner in that a heat shield element, which is part of the fireproof inner lining of the combustion chamber, is used as the burner. Such a burner heat shield element is supplied with fuel and combustion air and either discharged into the combustion chamber or burned directly in or on the heat shield element.

A premixing chamber, into which the fuel and the combustion air can be introduced, is preferably connected upstream of the burner heat shield element. Fuel and combustion air are only fed into the premixing room, where there is a fuel-air mixture 3 is formed. This fuel-air mixture is then fed to the burner heat shield element. This results in a homogeneous fuel-air mixture that is favorable for combustion.

The combustion chamber has an outer side, along which a fuel line preferably extends, from which fuel can be admitted into the premixing chamber. Such a fuel line could e.g. in the case of an annular combustion chamber, an annular line running around the combustion chamber wall in the circumferential direction of the annular combustion chamber, from which e.g. fuel can also be supplied in a simple manner for a plurality of burner heat shield elements which are arranged along this circumferential direction.

A combustible gas stream can preferably be passed through the combustion chamber along an expansion direction from an inlet side to an outlet side, at least one burner being provided for a first stage of combustion, and wherein a second stage of combustion can be generated by the burner heat shield element downstream of the first stage is.

A second stage of a two-stage combustion is implemented in a simple manner via the burner heat shield element. Of course, further stages of combustion can also be provided. Due to the two-stage or multi-stage combustion, a reaction zone of the combustion is distributed over a larger volume. This results in a lower tendency to form combustion vibrations in the combustion chamber. Such combustion vibrations can cause considerable damage to the combustion chamber. Furthermore, for a two-stage or a multi-stage combustion, there is particularly good controllability for adapting to different power outputs, ie load conditions, for example for a gas turbine operated under different loads. If a gas turbine is driven by the exhaust gas from the combustion chamber, then depending on the load 4 Gas-fuel ratio required for the gas turbine. The use of at least two burners results in a wide parameter range for controlling the combustion. In addition, if necessary, for example, the fuel supply to the burner heat shield element can be omitted, so that only air flows into the combustion chamber through the burner heat shield element. Furthermore, the use of the burner heat shield element results in an improved cooling capacity for cooling the inner lining of the combustion chamber, since a comparatively large amount of cooling combustion air can be fed to the burner heat shield element. Finally, another advantage is that the air mass flow through the first stage burner can be reduced. This has the particular consequence that the burner can be made smaller. This has the advantage, for example, that the burner can be removed in a simpler manner from a housing surrounding it.

The burner heat shield element extends along the

Direction of expansion from a first end to a second end, wherein the premixing chamber is preferably located between the combustion chamber wall and the burner heat shield element, and an outlet opening is provided in the region of the second end, which connects the premixing chamber to the combustion chamber. The arrangement of the premixing chamber and the outlet opening arranged downstream result in a flow-related connection of the premixing chamber to the combustion chamber, which is distinguished by a particularly low flow resistance.

Cooling air can preferably be supplied to the burner heat shield element, the cooling air being simultaneously usable as combustion air. The heat shield elements are frequently cooled in that cooling air is led from the outside of the combustion chamber wall, for example through bores to the rear of the heat shield elements. By using this cooling air supply 5 guidance as combustion air supply results in a particularly simple supply of combustion air to the burner heat shield element.

The burner heat shield element preferably has a material provided with numerous cavities, the fuel and the combustion air being able to be supplied in such a way that combustion can be generated within this material. Such a burner heat shield element represents a so-called pore burner. Fuel and combustion air are therefore burned in the cavities or pores, the material heating up. On the one hand, this leads to a good stabilization of the combustion. On the other hand, the pore structure has a strong damping effect on combustion vibrations. These two properties of a pore burner mean that combustion in a pore burner produces almost no combustion oscillation. Furthermore, the material, which heats up strongly during combustion, radiates a considerable amount of heat. As a result, the flame temperature of the combustion within the material is comparatively low. This in turn means that fewer nitrogen oxides are formed. The advantage of the lower flame temperature can also be used to supply more fuel to the burner heat shield element and therefore less fuel to the burner of a first stage. This reduces the formation of such combustion vibrations, which can be caused by the burner of the first stage.

The material is preferably a foamed ceramic, in particular zirconium oxide or silicon carbide. Such materials are e.g. B. can be produced in that the ceramic is introduced into a foam-forming support material and, after foaming and curing has taken place, the support material is etched away, so that a porous ceramic remains. 6 The combustion chamber is preferably designed as an annular combustion chamber forming an annular space, a plurality of heat shield elements being designed as burner heat shield elements along a circumferential direction of the annular space. Most of the heat shield elements arranged along a circumferential direction are preferably designed as burner heat shield elements. This results in a uniform distribution of the second stage of combustion over the circumference of the annular combustion chamber.

The combustion chamber is preferably used in a gas turbine, in particular in a stationary gas turbine. The gas turbine preferably has an output greater than 60 MW.

According to the invention, the object of specifying a method is achieved by a method for operating a combustion chamber with a combustion chamber wall and with an inner lining formed from a multiplicity of heat shield elements, at least one of the heat shield elements being supplied with fuel and combustion air for combustion in the combustion chamber.

The advantages of such a method result from the above explanations regarding the advantages of the combustion chamber.

The fuel and the combustion air are preferably first mixed, then fed to the heat shield element, then discharged into the combustion chamber and burned there. The fuel and the combustion air are more preferably burned within a porous structure of the heat shield element.

A first stage of a combustion preferably takes place first, with a second stage of the combustion then taking place via the heat shield element. 7 The method is further preferably carried out in a combustion chamber, in particular in an annular combustion chamber, of a gas turbine.

The invention is explained in more detail by way of example with reference to the drawing. Show it:

1 shows a longitudinal section through an annular combustion chamber of a gas turbine,

2 shows an enlarged section of an annular combustion chamber with a burner heat shield element,

3 shows a burner heat shield element and

4 shows a burner heat shield element made of a porous material.

The same reference symbols have the same meaning in the different figures.

Figure 1 shows a longitudinal section through an annular combustion chamber 1 for a gas turbine. The annular combustion chamber 1 is rotationally symmetrical about an axis 2. For the sake of clarity, only one half of the longitudinal section is shown. The annular combustion chamber 1 has a combustion chamber wall 3. The combustion chamber wall 3 encloses an annular space 4. The inner wall of the combustion chamber wall 3 is lined with an inner lining 5. The inner lining 5 is formed by a multiplicity of heat shield elements 6. Such heat shield elements 6 consist, for example, of refractory ceramic. A burner system 7 opens into the annular combustion chamber 1. This is formed by a diffusion burner 8 and a premix burner 9, which surrounds the diffusion burner 8 in the form of an annular channel. The burner system 7 is arranged on an end 11 of the annular combustion chamber 1 on the burner side. At an end 11 opposite the burner side Above the turbine-side end 13 is a gas turbine 15 shown schematically.

When using such an annular combustion chamber 1 in a gas turbine system, not shown here, fuel 17A is supplied to the pilot burner 8. Combustion air 18A is also supplied to the pilot burner 8. The fuel 17A and the combustion air 18A are burned via a diffusion operation of the pilot burner 8 in the annular space 4 of the annular combustion chamber 1. A mixture of fuel 17B and combustion air 18B ignites at the flame of this combustion stabilized on the pilot burner 8 and is fed to the premix burner 9. The exhaust gas 20 generated by the combustion emerges from the turbine-side end 13 of the annular combustion chamber 1 and drives the gas turbine 15. The following explains how the conventional single-stage combustion shown here can be supplemented in a particularly simple manner by a second stage of combustion using a burner heat shield element.

FIG. 2 shows a section of a longitudinal section corresponding to FIG. 1 through an annular combustion chamber 1. One of the heat shield elements 6 is designed as a burner heat shield element 22. Like each of the heat shield elements 6, the burner heat shield element 22 is screwed onto the combustion chamber wall 3 with a screw 24. 22 through holes 26 are provided in the combustion chamber wall 3 behind the burner heat shield element. On the outside 28 of the Brennka merwand 3, a fuel line 30 is also provided. A through bore 32 of the combustion chamber wall 3 leads from the fuel line 30 to a premixing chamber 34, which is formed by the burner heat shield element 22 abutting the combustion chamber wall 3. The through holes 26 also open into the premixing chamber 34. The burner heat shield element 22 extends from a first end 23 to a second end 25. 9 The burner heat shield element 22 is now used in the following manner for a second stage of combustion in the annular combustion chamber 1:

Fuel 36, preferably natural gas, is fed to the premixing chamber 34 via the fuel line 30 via the bore 32. Furthermore, combustion air 38 is fed to the premixing chamber 34 via the through holes 26. In the premixing chamber 34, the natural gas 36 mixes with the combustion air 38. At the second end 25, an outlet opening 40 is provided, which discharges the natural gas-air mixture 42 into the annular combustion chamber 1. The natural gas-air mixture 42 ignites in the hot annular combustion chamber 1. This forms a second stage of combustion. With this second stage, the reaction zone of the combustion taking place in the annular combustion chamber 1 is enlarged. This leads to a reduced tendency to form combustion vibrations. The considerable combustion air flow 38 also leads to a high cooling capacity for the burner heat shield element 22 and also for the further heat shield elements 6 located downstream of the burner heat shield element 22.

FIG. 3 again shows an enlarged and schematic illustration of a burner heat shield element 22 arranged on the burner chamber wall 3. The corresponding explanations apply as for FIG. 2.

A burner heat shield element 22, which is arranged on a combustion chamber wall 3, is shown schematically in a longitudinal section in FIG. The burner heat shield element 22 is formed from a porous material 44. It is fastened to the combustion chamber wall 3 with clips 46. On the outside 28 of the combustion chamber wall 3 facing away from the burner heat shield element 22, a wall 48 is provided opposite the burner heat shield element 22 which surrounds the premixing chamber 34. A fuel line 30 is integrated into the wall 48. Openings 50 are also provided in the wall 48. 10 seen. The premixing chamber 34 is connected in terms of flow technology to the burner heat shield element 22 through perforations 26 in the combustion chamber wall 3.

Combustion air 38 enters the premixing chamber 34 via the openings 50. Fuel, preferably natural gas, also arrives in the premixing chamber 34 from the fuel line 30. The fuel-air mixture 42 passes from the premixing chamber 34 into the burner heat shield via the perforations 26. element 22. The fuel-air mixture 42 penetrates into the porous material 44. The heat in a combustion chamber (not shown) ignites the fuel-air mixture 42 and burns within the pores of the porous material 44. The porous material 44 heats up. This leads to a particularly stable combustion. In addition, a combustion oscillation is suppressed by the pore structure of the porous material 44. Furthermore, the porous material 44 radiates heat. As a result, the flame temperature of the combustion within the porous material 44 is comparatively low. This in turn means that fewer nitrogen oxides are formed.

Claims

11 claims

1. Combustion chamber (1) with a combustion chamber wall (3) surrounding the combustion chamber wall (3) and with an inner lining (5) formed from a multiplicity of heat shield elements (6), characterized in that at least one heat shield element (5) functioning as a burner is a burner Is heat shield element (22), upstream of which a fuel supply (30) for fuel (36) and a combustion air supply (26) for combustion air (38).

2. Combustion chamber (1) according to claim 1, d a d u r c h g e k e n n e e c h n t that the burner heat shield element (22) is connected upstream of a premixing chamber (34) into which the fuel (36) and the combustion air (38) can be introduced.

3. Combustion chamber (1) according to claim 2, so that the combustion chamber wall (3) has an outer side (28) along which the fuel feed (30) extends.

4. Combustion chamber (1) according to one of the preceding claims, through which a fuel gas flow (20) from an inlet side (11) to an outlet side (13) can be guided along an expansion direction, at least one burner (8) for a first stage Combustion is provided, characterized in that a second stage of the combustion can be generated by the burner heat shield element (22) downstream of the first stage.

5. combustion chamber (1) according to claim 2 and 4, characterized in that the premixing chamber (34) is arranged between the combustion chamber wall (3) and the burner heat shield element (22), the burner heat shield element (22) extending along the direction of expansion a first end (23) to a second end (25) 12 stretches and in the region of the second end (25) an outlet opening (40) connects the premixing chamber (34) to the combustion chamber (4).

6. Combustion chamber (1) according to one of the preceding claims, characterized in that the burner heat shield element (22) has a material (44) which is provided with numerous cavities (45) and which is designed such that combustion within this material (44) can be generated.

7. combustion chamber (1) according to claim 6, d a d u r c h g e k e n n z e i c h n e t that the material (44) is metal, in which the cavities (45) are introduced mechanically, in particular by drilling.

8. Combustion chamber (1) according to claim 6, that the material (44) is a porous ceramic, in particular zirconium oxide or silicon carbide.

9. combustion chamber (1), in particular annular combustion chamber, according to one of the preceding claims, in which the combustion chamber (4) is annular, characterized in that a plurality of heat shield elements (6) as burner heat shield elements (6) along a circumferential direction of the annular space. 22) are formed.

10. Use of a combustion chamber (1) according to one of the preceding claims for a gas turbine, in particular for a stationary gas turbine with an output greater than 60 MW.

11. A method of operating a combustion chamber (1) with a combustion chamber wall (3) and with an inner lining (5) formed from a plurality of heat shield elements (6, 22), characterized in that at least 13 one of the heat shield elements (6, 22) fuel (36) and combustion air (38) for combustion in the combustion chamber (1) are supplied.

12. The method according to claim 11, so that the fuel (36) and the combustion air (38) are first mixed, then fed to the heat shield element (22), then discharged into the combustion chamber (1) and burned there.

13. The method according to claim 11, that the fuel (36) and the combustion air (38) are burned within a porous material (44) of the heat shield element (22).

14. The method according to any one of claims 11 to 13, that a first stage of a combustion takes place and then a second stage of the combustion takes place via the heat shield element (22).

15. Implementation of the method according to one of claims 11 to 14 in a combustion chamber (1), in particular in an annular combustion chamber, of a gas turbine.