WO2014019754A1

WO2014019754A1 - Combustion chamber cooling

Info

Publication number: WO2014019754A1
Application number: PCT/EP2013/062148
Authority: WO
Inventors: Olga Deiss; Thomas Grieb; Matthias Hase; Jens Kleinfeld; Bernd Prade
Original assignee: Siemens Aktiengesellschaft
Priority date: 2012-08-02
Filing date: 2013-06-12
Publication date: 2014-02-06
Also published as: EP2864705B1; EP2864705A1; RU2015106899A; CN104471316B; DE102012213637A1; US20150167978A1; CN104471316A

Abstract

The invention relates to a gas turbine combustion chamber (8), comprising an inner wall (2) having cooling air bores (17) and an outer wall (9) that is located at a distance from the inner wall (2), wherein the outer wall (9) likewise comprises cooling air bores (16) and is formed by a plurality of wall elements (11) that are arranged in the circumferential direction of the gas turbine combustion chamber (8) essentially next to each other, which wall elements are arranged on the inner wall (2) by means of a locating bearing (24) on a narrow side (21) and by means of a floating bearing (25) on an opposite narrow side (21), such that a hollow space (10) is formed between the two walls (2, 9).

Description

description

Title of the invention / Title of the invention

Burning Kammer cooling

The present invention relates to a gas turbine combustor.

Combustion chambers, in particular for gas turbines, are generally provided in their interior with a flow guide body, which is referred to as a liner. Via one or more burners provided in the combustion chamber, a combustible fluid mixture is supplied, which ignites in the combustion chamber of the combustion chamber and is passed through the liner in the direction of the outlet opening. Since the walls of the combustion chamber are exposed to high thermal loads due to the combustion taking place inside the combustion chamber, these parts of the combustion chamber must be cooled. A thermal barrier coating (ther ^¬ mal barrier coating) on the inside of the liner is usually not sufficient. Cooling is achieved, for example, by gaps ^¬ spaces through which a coolant is passed, which cools the combustion chamber convectively.

Due to temperature changes occurring during operation, thermal expansions occur on the components.

At the same time, the liner represents the transition to the turbine chamber and, for this reason, is conically shaped. The Küh ^¬ lung system must absorb the axial and radial thermal expansion of the liner with cone and ensure that even under changing conditions only a certain, defined amount of air ^¬ flows along the cone.

Figure 1 shows a gas turbine combustor with convective cooling of the liner cone with an outer shell. The object of the invention is to provide a gas turbine combustor with improved cooling.

According to the invention this object is achieved by the gas turbine combustion chamber according to claim 1. Advantageous developments of the wide Erbil ^¬ invention are defined in the dependent claims. In a gas turbine combustor comprising an inner wall with cooling air holes and an outer wall spaced from the inner wall, the outer wall also has cooling air bores and is formed of a plurality of wall elements substantially juxtaposed in the circumferential direction of the gas turbine combustor and having a fixed bearing on a narrow side and are arranged with a movable bearing on an opposite narrow side on the inner wall, so that a cavity is formed between the two walls, the cooling of the liner cone can take place via an ef ^¬ fective baffle cooling. In addition, the relative expansion of the wall element, which acts as a baffle plate, to the main body, ie the inner wall of the gas turbine, due to different temperatures of the body (about 900-1000 ° C) and the baffle plates (about 500-600 ° C) zugelas ^¬ sen.

In an advantageous embodiment, the wall elements are arranged on the burner side with a fixed bearing and the turbine side with ei ^¬ nem movable bearing on the inner wall.

It is expedient here for the inner wall to have the shape of a hollow truncated cone and the wall elements to have the shape of hollow truncated segments.

For better compensation of the thermal expansion in the radial direction adjacent wall elements are arranged overlapping. In an advantageous embodiment, the loose bearing for easier assembly of ring segments, which have a groove for receiving a respective narrow side of the wall elements. Conveniently, the fixed bearing consists of Ringsegmen ^¬ th.

For storage cooling, at least one of the bearings has cooling air holes.

For avoiding gaping of adjacent wall elements, it is advantageous if brackets are provided in the region of an overlap of two wall elements each. It may be useful if the brackets are mounted on the inner wall.

In order to allow also to the supports different thermal expansions tension-free as possible, the Wandele- elements have openings for the supports, wherein the opening are ^¬ diameter greater than the diameter of the holders in this area.

In order to prevent that the wall elements of the outer wall up due to thermal deformation of the cone of the inner wall touch spacer elements (pins) between the inner and externa ^¬ ßerer wall arranged. These spacer elements are zweckmäßi ^¬ gerweise a central region of each wall element in relation to, that is disposed at the center among the wall elements, on the inner wall, for example welded.

An embodiment of the ge ^¬ formed by the inner and the outer wall of the cavity as an acoustic damper (resonator) is particularly advantageous because the number of otherwise-required resonators can be reduced. This reduces ei ^¬ nerseits costs and saves the other hand, air that would be required for flushing or cooling of these resonators otherwise.

The advantages of the proposed solution are in the improved cooling of the liner cone by effectively Prallküh ^¬ lung as well as in the prevention of the thermal stress resulting from the floating bearing. In addition, due to the hollow space formed between the liner cone and the sheets, raum, which also acts as a resonator, damped medium to high-frequency oscillations.

The invention will be explained in more detail by way of example with reference to the drawings. Shown schematically and not to scale:

1 shows a gas turbine combustion chamber with a burner liner according to the prior art with external envelope for convective cooling, FIG.

FIG. 2 shows a gas turbine combustor according to the invention with wall elements for impingement cooling,

FIG. 3 shows a wall element with cooling-air bores and openings for fastening,

FIG. 4 a detail of a fixed bearing ring segment,

5 shows a section through a burner liner of a gas turbine combustor according to the invention with a fixed bearing, FIG.

FIG. 6 shows a section through a burner liner of a gas turbine combustion chamber according to the invention with floating bearing,

7 shows a plan view of a ring segment of the movable bearing, FIG. 8 shows a gas turbine combustion chamber according to the invention without wall elements,

9 shows a bolt for holding the wall elements against gape,

FIG. 10 shows a bolt in the installed state with conversion elements and

Figure 11 overlapping wall elements.

1 shows schematically and exemplarily a Gasturbi ^¬ nenbrennkammer 1 according to the prior art with an inner wall 2 (Brenner liner), which surrounds the combustion chamber 3 and the combustion chamber side has a heat shielding layer 4, and an inner wall 2 surrounding envelope 5 between which cooling air 6 for convective cooling of the inner wall 2 is performed. In the transition from the combustion chamber 3 to the turbine chamber (not shown) are the gas turbine combustor 1 and thus the inner

Wall 2 and the burner liner 2 conically shaped. This area is therefore also referred to as liner cone 7. Figure 2 shows a gas turbine combustor 8 according to the invention with an inner wall 2 and an outer wall 9 spaced therefrom, forming a cavity 10 (see Figures 5 and 6). The outer wall 9 is formed by a sheet metal construction, consisting of 8 wall elements 11, which can compensate for thermal expansions of the liner cone 7. A deviating from the embodiment of Figure 2 number of wall ^¬ elements 11 is possible. The wall elements 11 are welded on the burner-facing side 12 of the liner cone 7, ie to the truncated cone base, with the inner wall 2 and floating on the turbinenzugewand ^¬ th page 13 of the liner cone 7, ie the Kegelstumpfdeckflä ^¬ che out. A reverse solution is also possible.

In this case, two rows of sheets 14, 15 are installed offset one above the other. For baffle cooling of the inner cone-shaped wall 2, the wall elements 11 have cooling air bores 16. Corresponding cooling air bores 17 are provided in the inner wall 2 (see FIGS 8 and 10), so that the air used for the impingement cooling can flow into the combustion chamber 3.

Figure 3 shows a wall element 11 with cooling air holes 16. During operation may arise between superimposed elements 11 will walk ^¬ column uncontrolled un ^¬ ter succeed through the air, the sheet metal construction. However, these gaps are avoided by holders 18 (see Figures 10 to 11). The wall elements 11 have for this purpose on two opposite narrow sides 19 openings 20, whose diameter is larger than the support diameter in this area, to ensure enough clearance for thermal expansion here. The two other narrow sides 21 together with the ring segments 22, 23 shown in FIGS. 4 to 7 form a fixed bearing and a movable bearing 24, 25.

Figure 4 shows a section of a fixed bearing 24, insbeson ^¬ particular a ring segment 22 of a fixed bearing 24. If the Ring segment 22 welded to the inner wall 2 (see Figure 5), a cavity 26 is formed, which can be cooled via cooling air holes 27. Figure 5 shows a section through a fixed bearing 24 of a gas turbine combustor 8 according to the invention with a arranged on the burner liner 2 and connected thereto at the welds 28 ring segment 22 for the fixed bearing 24 and offset in the axial direction of the combustion chamber 8 arranged wall elements 11. Die Wandelemente 11 are connected to the Ringseg ^¬ ment 22 at the welds 29. For assembly reasons, adjacent wall elements 11 in the axial direction ver ^¬ sets with the ring segments 22 welded. Figure 6 shows a section through a floating bearing 25 of a gas turbine combustor 8 according to the invention with a arranged on the burner liner 2 and connected thereto at the welds 30 ring segment 23 for the floating bearing 25. The ring segment 23 of the movable bearing 25 includes a groove 31 for receiving a Narrow side 21 of the wall elements 11 and lies directly on the inner wall 2, so that no cooling air holes in the ring segment 23 are necessary.

Figure 7 shows a ring segment 23 for the floating bearing 25. The groove 31 for the floating support of the wall elements 11 in the ring ^¬ segment 23 extends according to the overlapping arrangement of the wall elements 11 at different radii with overlapping areas 32nd Figure 8 shows a gas turbine combustor 8 after the This sees both bolts 33 as parts of the brackets 18 against gape and other spacers or pins 34 angeord ^¬ net on the inner wall 2, which prevent the wall elements 11, the cone of the inner wall 2 due to thermal deformation touch. The pins 34 are typically welded in the middle under the wall ^¬ elements 11 on the inner wall 2. FIG. 9 shows a bolt 33 with a further mold element for easier mounting on the inner wall 2. The bolt 33 is part of a holder 18, as used against gaps between two adjacent wall elements 11.

FIG. 10 shows such a holder 18 in the installed state. It is welded to the inner wall 2 and, where appropriate, ^¬ on the inner wall 2 in a provided recess 35 is arranged. In the area of the openings 21 of the wall elements 11, the bolt 33 of the holder 18 has a smaller diameter than the openings 21 itself, so that sufficient space for thermal expansions is present. The wall elements 11 are secured with a welded perforated disc 36, so that substantially only axial displacements of the wall elements 11 and displacements in the circumferential direction of the gas turbine combustor 8, but no radial movements are possible. FIG. 11 shows a plan view of the region of the holder 18. Although a gas turbine combustion chamber with a conical liner is described in the exemplary embodiments, the invention is not limited to a conical geometry. Furthermore, the function of the device according to the invention is not limited to a cooling effect to be achieved, but can also be used as a resonance absorber.

Claims

claims

A gas turbine combustor (8) comprising an inner wall (2) with cooling air holes (17) and an outer wall (9) spaced from the inner wall (2), characterized in that the outer wall (9) also has cooling air holes (16) and of a plurality in the circumferential direction of the gas turbine combustor (8) substantially juxtaposed wall elements (11) is formed with a fixed bearing (24) on a narrow side (21) and with a movable bearing (25) on an opposite narrow side (21) on the inner wall (2) are arranged so that between the two walls (2, 9), a cavity (10) is formed.

2. Gas turbine combustor (8) according to claim 1, wherein the

Wall elements (11) burner side with a fixed bearing (24) and the turbine side with a movable bearing (25) on the inner wall (2) are arranged.

3. gas turbine combustion chamber (8) according to claim 1 or 2, wherein the inner wall (2) the shape of a hollow truncated cone and the wall elements (11) have the shape of hollow truncated cone segments ^¬ .

4. Gas turbine combustor (8) according to one of the preceding claims, wherein adjacent wall elements (11) are arranged overlapping.

5. gas turbine combustion chamber (8) according to any one of the preceding claims, wherein the movable bearing (25) of ring segments (23) be ^¬ having a groove (31) for receiving a respective narrow side (21) of the wall elements (11).

6. gas turbine combustor (8) according to any one of the preceding claims, wherein the fixed bearing (24) consists of ring segments (22).

7. gas turbine combustor (8) according to any one of the preceding claims, wherein at least one of the bearings (24, 25) cooling air holes (27).

8. gas turbine combustion chamber (8) according to one of the preceding claims, wherein in the region of an overlap (32) of two wall elements (11) brackets (18) are provided against a gap of the two wall elements (11).

A gas turbine combustor (8) according to claim 8, wherein the brackets (18) are mounted on the inner wall (2).

10. gas turbine combustor (8) according to any one of claims 8 or 9, wherein the wall elements (11) have openings (20) for the holders (18) and the opening diameters are greater than the diameter of the holders (18) in this area.

11. Gas turbine combustor (8) according to one of the preceding claims, wherein spacer elements (34) between the inner (2) and outer wall (9) are arranged.

12. Gas turbine combustor (8) according to claim 11, wherein the spacer elements (34) are a net area of the respective wall element (11) opposite to the inner wall (2).

13. Gas turbine combustor (8) according to any one of the preceding claims, wherein between the inner (2) and the outer wall (9) formed cavity (10) is performed as an acoustic damper ^¬ .