EP1429077A1 - Gas turbine - Google Patents

Abstract

The gas turbine has an annular combustion chamber between an annular outer combustion chamber wall on one side and an annular combustion chamber inner wall (28) on the other, which is composed of a number of wall elements fixed to a bearing structure. The bearing structure is composed of components (30) of the wall meeting at horizontal joint points (31), angled to the inner wall surface and joined by screw joints (32).

Description

The invention relates to a gas turbine with a Annular combustion chamber, the combustion chamber of an annular outer wall on the one hand and an annular one arranged therein Inner wall on the other hand is limited.

Gas turbines are used to drive generators in many areas or used by work machines. The Energy content of a fuel to generate a rotational movement a turbine shaft. The fuel will burned in a number of burners, one of them Air compressor compressed air is supplied. Through the Combustion of the fuel becomes a high pressure one Working medium generated at a high temperature. This Working medium is placed in a burner downstream of the respective burner Turbine unit guided where it is working relaxed. Each burner can have a separate combustion chamber be assigned, the one flowing out of the combustion chambers Working medium merged before or in the turbine unit can be. Alternatively, the gas turbine can also be in a so-called annular combustion chamber design to be carried out in the a plurality, especially all, of the burners in a common, usually annular, combustion chamber open.

When designing such gas turbines in addition to achievable performance usually a particularly high efficiency a design goal. An increase in efficiency can basically be used for thermodynamic reasons by increasing the outlet temperature, with which the working medium from the combustion chamber and into the Turbine unit flows. Therefore temperatures of around Desired 1200 ° C to 1500 ° C for such gas turbines and also achieved.

At such high temperatures of the working medium, however the components and parts exposed to this medium exposed to high thermal loads. To still at high Reliability a comparatively long lifespan It is usually necessary to ensure the affected components a design with particularly heat-resistant materials and cooling the affected components, such as the Combustion chamber and the turbine unit, necessary. especially the Combustion chamber and the moving parts of the turbine unit are subject however due to the thermal load and a general wear and tear due to the flow of the working medium increased wear, so gas turbines are serviced regularly must be replaced so that damaged components or can be repaired.

The combustion chamber in the direction of flow of the working medium subsequent turbine unit usually comprises a turbine shaft with a number of rotatable ones Blades is connected to the ring-shaped rows of blades form. The turbine unit further comprises a number of fixed guide vanes, which are also ring-shaped forming vane rows on the inner casing the turbine are attached. The blades serve thereby to drive the turbine shaft by pulse transmission of the working medium flowing through the turbine unit while the guide vanes for the flow guidance of the working medium between two in the flow direction of the working medium seen successive rows of blades or blade rings serve.

Since the rotational movement of the turbine shaft is usually to Drive of the air compressor upstream of the combustion chamber is used, it is extended beyond the turbine unit, so that in the area upstream of the turbine Annular combustion chamber, the turbine shaft toroidal from the annular Combustion chamber is surrounded.

The combustion chamber is on the one hand of an annular outer wall and an annular inner wall disposed therein on the other hand limited. The inner wall of the combustion chamber is there usually from two or more individual parts on their side facing the turbine shaft are screwed.

However, this structure of the annular combustion chamber has some disadvantages on, because the inner wall of the combustion chamber for maintenance is not accessible. So for maintenance work on the inner wall the upper parts of the compressor and turbine blade carriers be dismantled so that the turbine shaft with the inner wall of the combustion chamber can thus be removed to allow access to said inner wall. The assembly work are therefore very labor and time consuming. By the comparatively long downtime of the gas turbine in addition to the gas turbine assembly costs, downtime costs, the comparatively very high total costs maintenance and repair work on the gas turbine to lead.

The invention is therefore based on the object of a gas turbine of the type mentioned above, in which the inner wall the combustion chamber can be removed comparatively quickly and easily is.

This object is achieved by the inner wall the combustion chamber from a number of to one Support structure of the inner wall fastened wall elements formed is, the support structure of a number of on a horizontal Joint formed abutting sections is sloping in the area of the parting line over a number of screw connections aligned with the inner wall surface are connected.

The change elements in particular form the hot gas wetted Surface of the combustion chamber, the changing elements expediently on the actual supporting structure of the inner wall are attached. This support structure includes in particular also an upper and a lower half that over the screw connections aligned at an angle to the part joining plane are interconnected.

The invention is based on the consideration that the attachment of the various wall elements of the combustion chamber inner wall be accessible to each other from the combustion chamber should and the combustion chamber inner wall also from this to be dismantled. At the same time, the different Portions of the inner wall of the combustion chamber Load-bearing structure that meet at their horizontal parting line, be connected to each other by a fastening, which are joined together by a vertical force on the joint combines. These two functions are supported by the Screw connections aligned at an angle to the inner wall surface met, in addition to accessibility from the combustion chamber a sufficiently large vertical force component for connection of the two supporting structure halves.

To the by the diagonally aligned to the inner wall surface Horizontal force component resulting from the screw connection two connected by the screw connection Everyone is able to compensate for parts of the supporting structure Screw connection is expediently assigned a feather key. The feather key prevents the screwed together Wall elements on the horizontal parting line the horizontal force component of the screw connection to each other move. The feather key advantageously runs for this along the horizontal parting line and is in each case Grooves of the adjoining wall elements are precisely fitted, so that they don't move against each other can, and preferably only those for attachment the vertical force component of the screw connection Screw connection occurs on the horizontal parting line.

Around the combustion chamber interior and thus the screw connections Keeping the inner wall of the combustion chamber accessible is the outer wall the annular combustion chamber advantageously carried out in two parts and a lower part cooperating with an upper part educated. The upper part is expedient screwed to the lower part so that the combustion chamber outer wall can be removed. In this way of building the The combustion chamber outer wall is the combustion chamber interior and therefore the screw connections of the combustion chamber inner wall elements are also accessible.

To the combustion chamber wall from thermal loads on the working medium To protect is the inside and outside wall of the Combustion chamber expediently with one of a number of Provide heat shield elements formed lining. This are preferably with particularly heat-resistant protective layers Mistake.

The heat shield elements are advantageously via a system with tongue and groove on the inner wall and on the outer wall attached to the combustion chamber. Heat shield elements are on their edges preferably shaped in such a way that they pass through form a double bend towards the combustion chamber, which are in a recess in the combustion chamber wall, which forms the groove, anchor it and fasten it with it. The recess in the combustion chamber wall is expedient summarized for adjacent heat shield elements, so that adjacent heat shield elements on their butt against each other due to the bend and so a seal for the combustion chamber and the inside represent flowing working medium.

The advantages achieved with the invention are in particular in that through the joint of the combustion chamber walls a comparatively simple and quick installation the combustion chamber walls is possible. In particular the possibility to remove the inner wall of the combustion chamber faster and better maintenance of these combustion chamber parts. A time consuming removal of the further Runner and guide blades located in the turbine unit can through the access from the combustion chamber interior therefore eliminated, making maintenance work comparatively are simple and time-saving.

Fig. 1

einen Halbschnitt durch eine Gasturbine,

Fig. 2

einen Schnitt durch eine Ringbrennkammer,

Fig. 3

eine Seitenansicht der Ringbrennkammer,

Fig. 4

im Schnitt eine Schraubverbindung der Wandelemente der Brennkammerinnenwand, und

Fig. 5

im Schnitt einen Ausschnitt der Brennkammerinnenwand.

An embodiment is explained in more detail with reference to a drawing. In it show:

Fig. 1

a half-section through a gas turbine,

Fig. 2

a section through an annular combustion chamber,

Fig. 3

a side view of the annular combustion chamber,

Fig. 4

on average a screw connection of the wall elements of the combustion chamber inner wall, and

Fig. 5

in section a section of the combustion chamber inner wall.

The same parts have the same reference symbols in all the figures Mistake.

The gas turbine 1 according to FIG. 1 has a compressor 2 for Combustion air, a combustion chamber 4 and a turbine 6 for Drive the compressor 2 and a generator, not shown or a work machine. To do this are the turbine 6 and the compressor 2 on a common, also called Turbine rotor designated turbine shaft 8 arranged with which also connects the generator or the working machine is, and which is rotatably mounted about its central axis 9. The Combustion chamber 4 designed in the manner of an annular combustion chamber is with a number of burners 10 for burning one liquid or gaseous fuel.

The turbine 6 has a number of with the turbine shaft 8 connected, rotatable blades 12. The blades 12 are arranged in a ring shape on the turbine shaft 8 and thus form a number of rows of blades. Farther The turbine 6 comprises a number of fixed guide vanes 14, which is also ring-shaped with the formation of Guide vane rows attached to an inner housing 16 of the turbine 6 are. The blades 12 serve to drive the turbine shaft 8 by transfer of momentum from the turbine 6 working medium flowing through M. The guide vanes 14 serve in contrast to the flow of the working medium M between seen two in the flow direction of the working medium M. successive rows of blades or blade rings. A successive pair from a wreath of Guide vanes 14 or a row of guide vanes and from one Wreath of blades 12 or a row of blades is also referred to as the turbine stage.

Each guide vane 14 has one which is also referred to as a blade root Platform 18, which is used to fix the respective guide vane 14 on the inner housing 16 of the turbine 6 as a wall element is arranged. The platform 18 is a thermal comparison heavily loaded component that the outer boundary a heating gas channel for the one flowing through the turbine 6 Working medium M forms. Each blade 12 is analog Way over a platform 20 also referred to as a blade root attached to the turbine shaft 8.

Between the spaced platforms 18 of the guide vanes 14 of two adjacent rows of guide vanes is a respective guide ring 21 on the inner housing 16 of the Turbine 6 arranged. The outer surface of each guide ring 21 is also hot, flowing through the turbine 6 Working medium M exposed and in the radial direction from the outer end 22 of the blade opposite to it 12 spaced by a gap. The one between neighboring Guide rings 21 arranged guide vane rows serve in particular as cover elements that cover the inner wall 16 or other housing installation parts before a thermal Overuse by the flowing through the turbine 6 protects hot working medium M.

The combustion chamber 4 is so-called in the exemplary embodiment Annular combustion chamber designed in which a variety of in Arranged circumferentially around the turbine shaft 8 Burners 10 open into a common combustion chamber space. To is the combustion chamber 4 in its entirety as an annular Designed structure that positioned around the turbine shaft 8 is.

To further clarify the design of the combustion chamber 4 2, the combustion chamber 4 is shown in section, the continues like a torus around the turbine shaft 8. How can be seen in the illustration, the combustion chamber 4 has a Beginning or inflow section, in the end of the Outlet of the respectively assigned burner 10 opens. In the direction of flow seen of the working medium M then narrows the cross-section of the combustion chamber 4, the adjoining Flow profile of the working medium M in this Space area is taken into account. On the output side, the Combustion chamber 4 has a curvature in longitudinal section through which the outflow of the working medium M from the combustion chamber 4 in one for a particularly high impulse and energy transfer to the first row of moving blades as seen on the flow side is favored.

As can be seen in the illustration according to FIG. 3, the Combustion chamber 24 of combustion chamber 4, on the one hand, from the annular one Combustion chamber outer wall 26 and, on the other hand, from one therein arranged annular combustion chamber inner wall 28 limited. The combustion chamber 4 is designed for the combustion chamber inner wall 28 for example for maintenance work on special can be easily removed without the turbine shaft 8 and the upper part of the directly adjoining the combustion chamber 4 To remove guide vanes 14 of the turbine 6. For this purpose, the combustion chamber inner wall 28 consists of a number of wall elements on two sections 30 one Support structure are attached, the sections 30 under Formation of an essentially horizontal parting line 31 are joined to the combustion chamber inner wall 28.

The combustion chamber 4 is designed in particular for the wall elements and the sections 30 of the combustion chamber inner wall carrying these 28 to be able to disassemble from the combustion chamber 24. For this purpose, as shown in section in FIG. the sections 30 on the horizontal formed by them Partition 31 with oblique to the inner surface of the combustion chamber inner wall 28 extending screw connections 32 connected. each Screw connection 32 essentially comprises one obliquely to the surface formed by the combustion chamber inner wall 28 guided screw 33 with one in one of the wall elements 30 incorporated thread 34 cooperates.

So that the sections 30 by the due to the oblique Combustion chamber inner wall 28 extending screws 33 do not shift horizontal force components against each other, a key 35 is assigned to the screw connection 32. This runs in a position close to the respective screw connection 32 along the horizontal parting line 31 of the sections 30 and is in grooves of the sections 30 of Combustion chamber inner wall 28 fitted.

In order to facilitate access to the combustion chamber 24 of the combustion chamber 4, the combustion chamber outer wall 26 consists of an upper part 36 and a lower part 38, as can be seen in FIG. 3. The The upper part 36 and the lower part 38 are in contrast to the Connection of sections 30 of combustion chamber inner wall 28 supporting structure with perpendicular to the partial joining plane Provide screw connections as there are no problems here in terms of accessibility.

To achieve a comparatively high efficiency the combustion chamber 4 for a comparatively high temperature of the working medium M from about 1200 ° C to 1300 ° C. This also applies to these operating parameters, which are unfavorable for the materials to enable a comparatively long operating time are, as shown in Figure 5, the combustion chamber outer wall 26 and the combustion chamber inner wall 28 each their side facing the working medium M with one Heat shield elements 40 provided lining. each The heat shield element 40 is the one facing the working medium M. Side with a particularly heat-resistant protective layer fitted.

As an example in FIG. 5 for the combustion chamber inner wall 28 is shown, the heat shield elements 40 are via a system fixed with tongue and groove on the combustion chamber inner wall 28. For this purpose, heat shield elements 40 are of such a type on their edges shaped that by a double bend towards the combustion chamber form an anchor that is in a recess the combustion chamber inner wall 28, which forms the groove, anchor it and fix it with it. As also in the FIG. 5 shows neighboring heat shield elements 40 attached to combined grooves so that they are mutually touch and so the combustion chamber 24 of the combustion chamber 4th caulk.

Claims (5)

Gas turbine (1) with an annular combustion chamber (4), the combustion chamber (24) from an annular combustion chamber outer wall (26) on the one hand and an annular combustion chamber inner wall arranged therein (28) on the other hand, the Combustion chamber inner wall (28) from a number of on one Support structure of the combustion chamber inner wall (28) fastened wall elements is formed, and wherein the support structure of a Number of abutting on a horizontal parting line Parts (30) is formed in the area of the parting line over a number of oriented obliquely to the inner wall surface Screw connections (32) are interconnected. Gas turbine (1) according to claim 1, wherein the or each Screw connection (32) each assigned a key (34) is. Gas turbine (1) according to claim 1 or 2, wherein the combustion chamber outer wall (26) of the annular combustion chamber (4) in two parts and one cooperating with an upper part (36) Lower part (38) is formed. Gas turbine (1) according to one of claims 1 to 3, in which the combustion chamber inner wall (28) and / or the combustion chamber outer wall (26) with one of a number of heat shield elements (40) formed lining are provided. Gas turbine (1) according to claim 4, wherein the heat shield elements (40) via a tongue and groove system on the inner wall of the combustion chamber (28) or attached to the combustion chamber outer wall (26) are.

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