GAS TURBINE

Abstract

In a gas turbine, a plurality of burners, which are arranged concentrically to the rotational axis in a regular arrangement, each directing hot gas through an associated combustion chamber outlet into a turbine, at the inlet of which a second plurality of stator blades are arranged in a ring, uniformly spaced apart around the rotational axis. Cooling openings are provided, which are distributed over the circumference, through which cooling air is injected into the hot gas flow at the combustion chamber outlet. An improvement of the flow conditions in the hot gas is achieved by the cooling openings being divided into first cooling opening groups and second cooling opening groups. The arrangement of the first cooling opening groups corresponds to the arrangement of the stator blades, and in that the arrangement of the second cooling opening groups corresponds to the regular arrangement of the burners.

Description

FIELD OF INVENTION

The present invention relates to the field of gas turbine technology.

BACKGROUND

Gas turbines in their stationary form have had their permanent place in power generation for a long time. In this case, it concerns high performance machines, the efficiency of which is constantly being further improved. An example of the stage of development which has been achieved are the type GT24/26 gas turbines of the Assignee of the present application, which are equipped with 2-stage sequential combustion, and which are described for example in the article by F. Joos et al., “Field experience with the sequential combustion system of the GT24/GT26 gas turbine family”, ABB review 5, p. 12-20 (1998). Inducted air is compressed in a compressor and fed to a first burner arrangement where it is used for the combustion of an injected fuel. This first burner arrangement comprises premix burners which among specialists have also been known as EV burners or possibly AEV burners. Such burners follow for example from EP-0321809 A1 and EP-0704657 A1 respectively, wherein these printed publications and also further publications which are related to this technology form an integrating element of this application. The hot gas which is created as a result of this combustion is first of all partially expanded in a high-pressure turbine and then introduced into a second burner arrangement (known among specialists as SEV burners), where the portion of unused air is used for a second combustion. The hot gas from the SEV burners is then expanded in a low-pressure turbine. The exhaust gases are then finally used for example for steam generation in a heat recovery steam generator.

On the outlet side of the SEV burner, the hot gas flow impinges upon the first row of stator blades of the low-pressure turbine. This configuration is described for example in U.S. Pat. No. 6,751,962 or in EP-A2-1 505 254, the contents of which are incorporated by reference as if fully set forth, and is reproduced in a detail in FIG. 1 of the present description. In the gas turbine 10 of FIG. 1, the hot gas 12, which discharges from the combustion chamber outlet 11, impinges upon the leading edge of the stator blades 15 of the first stator blade ring which is arranged at the inlet of the turbine. The combustion chamber outlet 11 is bounded at the side by means of a delimiting element 19. Between the end of the delimiting element 19 and the first stator blade row 15 there is a gap 16 which is sealed to the outside by means of an annular seal 17. By means of purging openings 18 in the seal 17 and leakages, purging air enters the gap 16 and prevents ingress of hot gas. Cooling air is also injected through cooling openings 20, 21 in the delimiting element, as is described in the aforementioned U.S. Pat. No. 6,751,962.

As a result of the fast flowing hot gas, various effects occur at the transition to the turbine. For one thing, a rearwards directed bow wave 13 is created at the leading edge of the stator blades 15, which is superimposed upon the pressure drops from the suction side 24a, 24b, 24c, 24d to the pressure side 25a, 25b, 25c, 25d. On the other hand, as a result of the complex flow conditions in the burners or combustion chambers with swirl elements which in most cases exist therein, a characteristic pressure distribution is created at the combustion chamber outlet 11, which can be referred to as a burner wave 14.

The unequal distribution of pressure at the combustion chamber outlet 11 in practice can be of the same order of magnitude as the pressure changes which ensue as a result of the bow wave 13 on the stator blades 15. The superimposition of the two effects (bow wave 13 and burner wave 14) can therefore lead to a situation in which the amplitude of the bow wave is effectively doubled and so hot gas escapes from the hot gas passage. These flow conditions, both in gas turbines with one combustion chamber or in gas turbines with sequential combustion, that is to say via 2 combustion chambers (EV, or AEV, and SEV), occur in each case at the transition from the burners to the turbine.

SUMMARY

The present disclosure is directed to a gas turbine including a plurality of burners, which are arranged concentrically to a rotational axis in a regular arrangement, in each case direct hot gas through an associated combustion chamber outlet into a turbine. At an inlet of which a plurality of stator blades are arranged in a ring, being uniformly spaced apart around the rotational axis. Cooling openings are also provided which are distributed over the circumference and through which cooling air can be injected into the hot gas flow at the combustion chamber outlet. The cooling openings, with regard to the passage which is formed by the hot gas flow, are arranged in the region of an inner encompassing and/or outer encompassing gap and are divided into first cooling opening groups and/or second cooling opening groups. The arrangement of the first cooling opening groups corresponds to the arrangement of the stator blades, and the arrangement of the second cooling opening groups corresponds to the regular arrangement of the burners.

The disclosure is also directed to a method for operating a gas turbine having a plurality of burners, which are arranged concentrically to a rotational axis in a regular arrangement. The burners have an associated combustion chamber outlet via which hot gas is injected for impinging upon a turbine. At an inlet of the turbine a plurality of stator blades are operated and arranged in a ring, uniformly spaced apart around the rotational axis, and in which gas turbine cooling openings take effect, and are distributed over the circumference and through which cooling air is injected into the hot gas flow. The method includes providing at least one inner encompassing gap in the region of the stator blades, or upstream of the stator blades, for preventing a hot gas penetration through this gap. The method also includes orienting outer encompassing cooling openings towards the hot gas flow, to take effect. The cooling openings are divided into first cooling opening groups and/or second cooling opening groups, the arrangement of the first cooling opening groups corresponds to the arrangement of the stator blades and the arrangement of the second cooling opening groups corresponds to the regular arrangement of the burners.

BRIEF DESCRIPTION OF THE DRAWINGS

The invention shall subsequently be explained in more detail based on exemplary embodiments in conjunction with the drawing. All elements which are not necessary for the direct understanding of the invention are omitted. The flow direction of the different media are indicated by arrows. Like elements in the different figures are provided with the same designations. In the drawings:

FIG. 1 shows in a detail a transition between the combustion chamber outlets and the first stator blade row of a gas turbine, as is suitable for realization of the invention; and

FIG. 2 shows in a schematic view the different periodicity of stator blades and burners, according to which the arrangement of the cooling opening groups is oriented according to the invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

Introduction to the Embodiments

It is the object of the invention to design the gas turbine so that the unfavorable effects of the bow wave and of the burner wave at the transition between combustion chamber outlet and turbine inlet are avoided.

The object is achieved by the entirety of the features of claim 1. It is preferable for the discovered solution that the cooling openings are divided into first cooling opening groups and second cooling opening groups, that the arrangement of the first cooling opening groups corresponds to the arrangement of the stator blades, and that the arrangement of the second cooling opening groups corresponds to the regular arrangement of the burners.

This solution is based therefore on the following considerations:

• • The flows at the combustion chamber outlet are unequal on account of the configuration of the burners with their flow vortices, local effects of wall cooling, and leakage air.
  • An unequal distribution of the purging and leakage air in the gap between combustion chamber outlet and turbine inlet results from this.
  • If the cooling openings are arranged at the places where the highest pressure occurs in the flow, these effects can be compensated.

The invention refers to the interface of burners and turbine in gas turbines with 1 or 2 burner arrangements or combustion chambers.

The number of burners which are especially used in the said combustion chambers is often disparate to the number of stator blades, especially being fewer than the number of stator blades.

According to another development of the invention, the burners are arranged in the second stage of a gas turbine with two-stage or sequential combustion.

In a further development, the cooling openings of the first cooling opening groups have a non-defined position with regard to the leading edges of the stator blades, typically slightly on the pressure side of the leading edge, and the cooling openings of the second cooling opening groups are oriented transversely to the hot gas flow.

In an especially preferred development of the invention, an encompassing gap is provided between the combustion chamber outlets and the first stator blade row of the turbine, which is purged with purging air through purging openings which are arranged in a distributed manner on the circumference, the purging openings are divided into groups, the arrangement of which corresponds to the arrangement of the stator blades and/or to the regular arrangement of the burners.

Advantageous and expedient further developments of the solution to the problem according to the invention are found in the dependent claims.

DETAILED DESCRIPTION

In FIG. 2, in a schematic view, the different periodicity of stator blades 15a, b, c, d and burners 22a, b, c is reproduced, according to which the arrangement of cooling openings 18, 20 and 21 is oriented according to the invention.

For this, as follows from FIG. 2, the cooling openings 20 according to FIG. 1, which are oriented towards the stator blades 15, are divided into cooling opening groups 20a, b, c and d, which form a cooling opening row A which is distributed over the circumference. Furthermore, as is easily seen in FIG. 2, a cooling opening group 20a, b, c, d is associated with each stator blade 15a, b, c, d, wherein the periodicity of the cooling opening groups 20a, b, c, d is equal to the periodicity of the stator blades 15a, b, c, d. In particular, the cooling opening groups 20a, b, c, d are associated with the leading edges of the stator blades 15a, b, c, d, along which the bow wave 13 is created, as is shown in FIG. 1. The cooling openings are typically arranged slightly on the pressure side of the leading edges in order to also compensate the pressure difference from pressure to suction side.

The cooling openings 21, which inject cooling air transversely into the combustion chamber outlet 11, are also combined to form cooling opening groups, of which only the one cooling opening group 21′ is shown in FIG. 2 and one cooling opening row B is indicated. The periodicity of the cooling openings 21′ is equal to the periodicity of the burners 22a, b, c. In the example of FIG. 2, the cooling opening groups 21′ are arranged directly in the middle of the combustion chamber outlets and are therefore oriented towards the burner lances 23a, b which lie in the middle. Other arrangements of equal periodicity are conceivable and oriented according to the concrete flow conditions at the combustion chamber outlet.

Depending upon flow conditions, the cooling air openings 20, 21 can be provided not only cumulatively but can also be used alternatively to each other, or can be arranged in an alternating manner. The same considerations, cumulative, alternative or alternating, also apply with regard to the purging openings 18.

As a result of the orientation of the two cooling opening groups 20a, b, c, d and 21′ in the cooling opening rows A and B towards the stator blades 15a, b, c, d or towards the burners 22a, b, c, the increasing, undesirable effects of the bow waves 13 and burner waves 12 can be weakened or rendered harmless in a simple manner.

An additional possibility of influencing is created if comparable periodicities of opening groups, which can be selectively oriented according to the periodicity of the stator blades 15a, b, c, d or of the burners 22a, b, c, or of both, are introduced for the purging openings 18 which are associated with the gap 16. As a result of this, unequal distributions in the gap region, which result from the superimposition of bow waves 13 and burner waves 12, can be directly compensated.

Finally, a type of construction which is not shown in more detail in the described figures is briefly commented upon. With regard to FIG. 1, constructions inside the hot gas flow passage are possible in which there is not only an inner encompassing gap 16 in the circumferential direction but there is also an outer encompassing gap on the outer encompassing side of this hot gas flow passage, which largely fulfills the same attributes. In such a case, provision is also made in the region of this outer encompassing gap for first and/or second cooling opening groups (20, 21) which fulfill the same final purpose as in the region of the gap 16 which is shown.

LIST OF DESIGNATIONS

10 Gas turbine

11 Combustion chamber outlet

12 Hot gas

13 Bow wave (stator blade)

14 Burner wave

15; 15a,b,c,d Stator blade

16 Gap (encompassing)

17 Seal (annular)

18 Purging opening

19 Delimiting element

20; Cooling opening

20 a,b,c,d Cooling opening group

21 Cooling opening

21′ Cooling opening group

22 a,b,c Burner

23 a,b Burner lance

24 a,b,c,d Suction side of the stator blade

25 a,b,c,d Pressure side of the stator blade

Claims

1. A gas turbine (10), comprising a plurality of burners (22a, b, c), which are arranged concentrically to a rotational axis in a regular arrangement, each directing hot gas (12) through an associated combustion chamber outlet (11) into a turbine, at an inlet of which a plurality of stator blades (15; 15a, b, c, d) are arranged in a ring, being uniformly spaced apart around the rotational axis, and in which gas turbine provision is made for cooling openings (20; 21) which are distributed over the circumference and through which cooling air can be injected into the hot gas flow at the combustion chamber outlet (11), the cooling openings (20; 21), with regard to the passage which is formed by the hot gas flow (12), are arranged in the region of an inner encompassing and/or outer encompassing gap (16) and are divided into first cooling opening groups (20a, b, c, d) and/or second cooling opening groups (21′), the arrangement of the first cooling opening groups (20a, b, c, d) corresponds to the arrangement of the stator blades (15; 15a, b, c, d), and the arrangement of the second cooling opening groups (21′) corresponds to the regular arrangement of the burners (22a, b, c).

2. The gas turbine as claimed in claim 1, wherein the inner encompassing and/or outer encompassing gaps are located in the region of, or upstream of, the stator blades.

3. The gas turbine as claimed in claim 1, wherein the burners (22a, b, c) are uniformly spaced apart.

4. The gas turbine as claimed in claim 1, wherein the number of burners (22a, b, c) is disparate to the number of stator blades (15; 15a, b, c, d).

5. The gas turbine as claimed in claim 4, wherein the number of burners (22a, b, c) is fewer than the number of stator blades (15; 15a, b, c, d).

6. The gas turbine as claimed in claim 1, wherein the burners (22a, b, c) are arranged in the second stage of a gas turbine (10) with two-stage or sequential combustion.

7. The gas turbine as claimed in claim 1, wherein the cooling openings (20) of the first cooling opening groups (20a, b, c, d) are oriented towards the leading edges of the stator blades (15; 15a, b, c, d), and the cooling openings (21) of the second cooling opening groups (21′) are oriented transversely to the hot gas flow (12).

8. The gas turbine as claimed in claim 1, further comprising an encompassing gap (16) between the combustion chamber outlets (11) and a first stator blade row (15; 15a, b, c, d) of the turbine, which is purged with purging air through purging openings (18) which are arranged in a distributed manner on the circumference, the purging openings (18) are divided into groups, the arrangement of which corresponds to the arrangement of the stator blades (15; 15a, b, c, d) and/or to the regular arrangement of the burners (22a, b, c).

9. The gas turbine as claimed claim 8, wherein the purging openings (18) are provided cumulatively, alternatively or in an alternating manner in relation to the cooling openings (20, 21).

10. A method for operating a gas turbine having a plurality of burners (22a, b, c), which are arranged concentrically to a rotational axis in a regular arrangement, the burners having an associated combustion chamber outlet (11) via which hot gas (12) is injected for impinging upon a turbine, at an inlet of the turbine a plurality of stator blades (15; 15a, b, c, d) are operated and arranged in a ring, being uniformly spaced apart around the rotational axis, and in which gas turbine cooling openings (20; 21) take effect, and are distributed over the circumference and through which cooling air is injected into the hot gas flow (12), the method comprising providing at least one inner encompassing gap (16) in the region of the stator blades, or upstream of the stator blades, for preventing a hot gas penetration (13, 14) through this gap (16),orienting outer encompassing cooling openings (20; 21) towards the hot gas flow (12), take effect,dividing the cooling openings (20; 21) into first cooling opening groups (20a, b, c, d) and/or second cooling opening groups (21′), the arrangement of the first cooling opening groups (20a, b, c, d) corresponds to the arrangement of the stator blades (15; 15a, b, c, d) and the arrangement of the second cooling opening groups (21′) corresponds to the regular arrangement of the burners (22a, b, c).

11. The method as claimed in claim 10, further comprising providing at least one outer encompassing gap in the region of the stator blades, or upstream of the stator blades, for preventing a hot gas penetration through the at least one outer encompassing gap, the outer encompassing cooling openings, which are oriented towards the hot gas flow (12), take effect, the cooling openings are divided into first cooling opening groups and/or second cooling opening groups, the arrangement of the first cooling opening groups corresponds to the arrangement of the stator blades (15; 15a, b, c, d), and the arrangement of the second cooling opening groups (21′) corresponds to the regular arrangement of the burners.