EP1840337A1 - Tongue and groove connection between two components of a turbine - Google Patents

Abstract

The turbine has turbine components (30,36), where a component is connected with another component by a groove and spring connector. A gap (38) is form4d between a groove (34) and a spring (32) of the connector, where the gap is filed with a filling material (40). The connector connects a vane with a carrier or with an end piece. Several shafts are connected to a rotor blade and guide vanes are fixed in an annular form to the interior housing of the turbine.

Description

The invention relates to a turbine with a number of turbine components, in which a first turbine component is connected via a tongue and groove connection with a second turbine component.

Turbines, in particular gas turbines, are used in many areas to drive generators or work machines. In this case, the energy content of a fuel is used to generate a rotational movement of a turbine shaft. For this purpose, the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor. The working medium produced in the combustion chamber by the combustion of the fuel, which is under high pressure and at high temperature, is guided via a turbine unit arranged downstream of the combustion chamber, where it relaxes to perform work.

To generate the rotational movement of the turbine shaft, a number of rotor blades, which are usually combined to form groups of blades or rows of blades, are arranged thereon and drive the turbine shaft via a momentum transfer from the working medium. To guide the working fluid in the turbine unit also usually connected between adjacent blade rows are connected to the turbine housing Leitschaufelreihen.

When designing such gas turbines, it is usually necessary to ensure that the working medium in the turbine unit passes through the blade rows in their working area and does not flow around them laterally. To ensure this, a number of turbine components usually form a flow channel for the working fluid in which it is guided and in which the blades are suitably arranged. The flow channel is usually formed by the blade platforms of the guide vanes and by seen in the flow direction of the working medium behind the rows of guide vanes arranged transition pieces, so-called guide rings.

The turbine components forming this flow channel for the working medium, that is to say in particular guide rings or their segments, as well as guide blade carriers or platforms, are usually connected to one another via tongue-and-groove connections. In this case, an integrally formed on one of the turbine components mounting lip engages in an associated groove in the second turbine component. Such connection techniques are usually chosen to keep Abströmverluste and leaks as low as possible and thus to lead the working fluid in the flow channel particularly effective through the blade rows. For this purpose, such groove-and-tongue connections between individual turbine components are usually designed with particularly high accuracy of fit and with particularly low tolerances, so that due to the high accuracy of fit unwanted leakage losses can be kept particularly low.

However, such high accuracy of fit and low tolerances require increased effort in the manufacture and assembly of the corresponding components. In addition, as a result of the usual operating and operating conditions in gas turbines usually thermal elongations in the individual turbine components, so that in the actual operating state even with very high accuracy of the manufactured components unwanted gap formation and concomitant leakage losses can occur.

The invention is therefore based on the object of specifying a turbine of the type mentioned above, in which the leakage losses can be kept particularly low with particularly low assembly and manufacturing costs during operation of the turbine.

This object is achieved according to the invention in that a groove formed between groove and tongue is filled with a filling material in the tongue-and-groove joint connecting the first and the second turbine components.

The invention is based on the consideration that, for particularly low leakage losses, a particularly high tightness between the mutually connected turbine components should be ensured. The possibilities for this, however, are limited in the utilization of manufacturing accuracies and the like, in particular because of systemic effects due to thermal stress additional gap formations could occur. In order to be able to compensate for this appropriately, the turbine components should therefore have a suitably selected sealing element or sealing material in the region of their connection. This can be achieved by a suitable filling material is provided in the region of a gap formed between tongue and groove, which can deform plastically, for example, during assembly of the two components and in the production of tongue and groove connection and thus manufacturing inaccuracies of the actual component parts suitable compensates. In the sense of a one-time equalizing joining, it is therefore possible to produce a particularly intimate and, in particular, tight connection between the two turbine components.

In order to be able to exploit the desired plastic deformation and thus the increased sealing effect of the filling material particularly favorably, a softer material than the material of the turbine components is advantageously selected as the filling material. With such a choice of material can be achieved in the assembly of the turbine components targeted plastic deformation exclusively in the filling material, so that on the one hand a high sealing effect is achieved, on the other hand, the function-defining contouring and dimensioning of the actual turbine components can be maintained unchanged. advantageously, is as filler a solder material, in particular an AMDRY material, which may be suitably cohesively attached to one of the two turbine components.

Advantageously, the turbine is designed as a gas turbine. The tongue-and-groove connection provided with the filling material is preferably used in turbine components which are used in the region of the flow space for the working medium. Particularly advantageously, the tongue-and-groove connection with the filling material connects a guide vane to a guide vane carrier or a vane to an end piece of a combustion chamber wall or a guide ring segment with its holder.

The advantages achieved by the invention are, in particular, that a particularly high density of the interconnected turbine components can be achieved by the introduction of the filling material in the gap formed between the tongue and groove of the tongue and groove joint. In addition, the turbine components can be manufactured with comparatively generously dimensioned manufacturing tolerances, since fit inaccuracies and the like can be compensated appropriately in the installed state via the filling material anyway.

FIG 1

einen Längsschnitt durch eine Gasturbine,

FIG 2

im Ausschnitt eine mit einer ersten Turbinenkomponente verbundene zweite Turbinenkomponente, und

FIG 3

ebenfalls im Ausschnitt zwei miteinander verbundene Turbinenkomponenten.

An embodiment of the invention will be explained in more detail with reference to a drawing. Show:

FIG. 1

a longitudinal section through a gas turbine,

FIG. 2

in section a second turbine component connected to a first turbine component, and

FIG. 3

also in the clipping two interconnected turbine components.

Identical parts are provided with the same reference numerals in all figures.

The gas turbine 1 according to FIG. 1 has a compressor 2 for combustion air, a combustion chamber 4 and a turbine 6 for driving the compressor 2 and a generator or a working machine (not shown). For this purpose, the turbine 6 and the compressor 2 are arranged on a common, also called turbine rotor turbine shaft 8, with which the generator or the working machine is connected, and which is rotatably mounted about its central axis 9.

The combustion chamber 4 is equipped with a number of burners 10 for the combustion of a liquid or gaseous fuel. It is also provided on its inner wall with heat shield elements not shown.

The turbine 6 has a number of rotatable blades 12 connected to the turbine shaft 8. The blades 12 are arranged in a ring on the turbine shaft 8 and thus form a number of blade rows. Furthermore, the turbine 6 comprises a number of fixed vanes 14, which are also fixed in a ring shape to form an airfoil on an inner casing 16 of the turbine 6. The blades 12 are used to drive the turbine shaft 8 by momentum transfer from a turbine 6 flowing through the working medium M. The vanes 14, however, serve to guide the flow of the working medium M between two seen in the flow direction of the working medium M consecutive blade rows or blade rings. A successive pair of a ring of vanes 14 or a row of vanes and a ring of vanes 12 or a blade row is also referred to as a turbine stage.

Each vane 14 has a platform 18, which is arranged to fix the respective vane 14 on the inner housing 16 of the turbine 6 as a wall element. The platform 18 is a thermally comparatively heavily loaded component which defines the outer boundary of a hot gas channel for the turbine 6 flowing through the working medium M forms. Each blade 12 is attached to the turbine shaft 8 in an analogous manner via a platform 20, also referred to as a blade root.

Between the spaced-apart platforms 18 of the guide vanes 14 of two adjacent rows of guide vanes is in each case a guide ring 21 on the inner housing 16 of the turbine 6 is arranged. The inner surface of each guide ring 21 is also exposed to the hot working medium M flowing through the turbine 6 and spaced radially from the outer end 22 of the blades 12 of a blade row opposite it through a gap 24. The arranged between adjacent rows of guide vanes 21 serve as a by their thermal expansion, the gap 24 between the respective guide ring 21 and associated blade row regulating components and on the other as cover that the inner housing 16 or other housing-mounting components from thermal overload by the Turbine 6 through flowing hot working medium M protect.

Several of the turbine components forming the turbine 6, in particular the turbine components arranged in the region of the hot gas duct, are connected to the respectively adjacent turbine components via a tongue-and-groove connection. In order to achieve a high density, in particular to avoid leakage losses in such compounds with comparatively low assembly and manufacturing costs, some of these tongue-and-groove joints are made with a specifically selected filling material prepared, as shown by way of example in Fig. 2 is. There, a first turbine component 30 is shown, which has an integrally formed, in a longitudinal direction extending mounting lip to form a spring 32. The spring 32 engages in an associated groove 34 of a second turbine component 36 for producing the tongue-and-groove connection. For producing a particularly tight tongue-and-groove connection with particularly low assembly and manufacturing costs, which allows in particular the manufacture of the turbine components 30,36 with comparatively large tolerance ranges, the gap 38 formed between the groove 34 and the spring 32 is filled with a filling material 40. In particular, a material which is softer than the material of the actual turbine components 30, 36 is selected as filler material 40.

When mounting the turbine components 30,36, the spring 32 is inserted or introduced into the groove 34. To produce the particularly dense connection, the filling material 40 is suitably shaped beforehand, for example in the form of a thickly applied coating either on the spring 32 or in the groove 34 or else in the manner of a suitably chosen starting body, such as a long-drawn wire or the like , introduced into the region between the groove 34 and the spring 32. During the subsequent insertion of the spring 32 into the groove 34 or the first occurrence of thermal expansion, the filling material 40 is suitably deformed and thus fills the gap 38 almost completely. Production inaccuracies and the like are thereby compensated, so that a tight connection between the turbine components 30,36 arises. In particular, a soldering material or the like is considered as filling material 40, which is attached to one of the two turbine components 30, 36, for example, in a materially bonded manner.

In a particularly favorable manner, such a connection between a stator blade 16 and the guide vane carrier associated therewith, ie in the region of the Leitschaufelverhakung, or between the guide vane 16 of the first turbine stage and an output of the combustion chamber 4 (so-called transition piece) or between a segment of a guide ring 21 and its holder used. In FIG. 3 this is shown using the example of a vane ring segment, wherein the vane 16 forms the first turbine component 30, which is connected via molded springs 32 with adjacent second turbine components 36.

Claims (4)

A turbine (6) having a number of turbine components, wherein a first turbine component (30) is connected via a tongue and groove connection with a second turbine component (36), wherein between groove (34) and spring (32) of the Groove-and-spring connection formed gap (38) with a filling material (40) is filled. Turbine (6) according to claim 1, in which a softer material than the material of the turbine components (30, 36) is selected as filling material (40). A turbine (6) according to claim 1 or 2, wherein the tongue and groove joint connects a vane (16) to a vane support or a vane (16) to an end of a combustion chamber wall or a guide ring segment to its support. Turbine (6) according to one of claims 1 to 3, wherein the filling material (40) is materially connected to one of the two turbine components (30, 36).

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