1. Field of the Invention
The invention relates to a turbomachine, in particular a gas turbine.
2. Description of the Related Art
It is well known from practice that turbomachines, such as for example gas turbines, have a plurality of stator-side assemblies and a plurality of rotor-side assemblies. The stator-side assemblies of a turbomachine include a stator-side housing, a plurality of stator-side guide vanes being fastened to the stator-side housing via a plurality of stator-side guide vane supports, with formation of axially spaced guide vane rings. Thus, the stator-side guide vane supports are fastened to the housing, the guide vanes being fastened to the guide vane supports and via the guide vane supports to the housing. The rotor-side assemblies of a turbomachine include the rotor-side moving blades, which are fastened to a rotor base body.
In turbomachines known from practice, each guide vane support is connected, via its own separate flange connection, to a corresponding flange of the housing. Particularly when turbomachines are to be provided in a compact design, a close axial and radial layering of the flanges is then required for this. Moreover, the machining of the flanges is expensive.
Starting with this as the starting point, an object of the present invention is to provide a novel turbomachine.
This object is achieved by a turbomachine in which, in each case, at least two guide vane supports are jointly fastened to and centered on a flange of the housing.
According to an aspect of the present invention, it is proposed that in each case at least two guide vane supports are jointly fastened to and centered on a flange of the stator-side housing of the turbomachine. As a result, the number of required flanges of the housing can be reduced. As a result, the expenditure for machining the housing is reduced. Furthermore, the number of elements required for fastening and centering the guide vane supports can be reduced. When a turbomachine is to be provided in a compact design, constructional space advantages result from the reduced number of flanges of the housing.
Preferably, the guide vane supports are fastened to the respective flange of the housing with the aid of a plurality of connecting elements which extend through flanges of the guide vane supports, which are jointly fastened to and centered on the same flange of the housing, and into the flange of the housing. The connecting elements serve as fastening elements in order to jointly fasten a plurality of guide vane supports on a flange of the housing.
According to an advantageous development, a centering of a first guide vane support on the respective flange of the housing in the axial direction of the turbomachine takes place as a result of a flange of the first guide vane support coming to bear with a first flange surface against a flange surface of the flange of the housing, a centering of a second guide vane support on the same flange of the housing in the axial direction of the turbomachine taking place as a result of a flange of the second guide vane support coming to bear with a flange surface against a second flange surface of the flange of the first guide vane support. As a result, a simple and effective centering of a plurality of guide vane supports jointly on one flange of the housing is possible.
According to a further advantageous development, a centering of a first guide vane support on the respective flange of the housing in the radial direction and the circumferential direction of the turbomachine takes place as a result of at least three first centering elements extending through a flange of the first guide vane support into the flange of the housing, a centering of a second guide vane support on the same flange of the housing in the radial direction and the circumferential direction of the turbomachine taking place as a result of at least three second centering elements extending through a flange of the second guide vane support and the flange of the first guide vane support into the flange of the housing. As a result, a simple radial centering and circumferential centering of a plurality of guide vane supports jointly on one flange of the housing is possible.
Preferably, in the first centering elements and in the second centering elements there are made bore-like cutouts, through which the connecting elements extend. This allows a particularly compact design of the turbomachine.
Preferably, the first centering elements and the second centering elements are in each case uniformly distributed in the circumferential direction. The uniform distribution of the centering elements in the circumferential direction and preferably of the connecting elements in the circumferential direction is preferred for the uniform take-up of forces and moments.
Other objects and features of the present invention will become apparent from the following detailed description considered in conjunction with the accompanying drawings. It is to be understood, however, that the drawings are designed solely for purposes of illustration and not as a definition of the limits of the invention, for which reference should be made to the appended claims. It should be further understood that the drawings are not necessarily drawn to scale and that, unless otherwise indicated, they are merely intended to conceptually illustrate the structures and procedures described herein.
Preferred developments of the invention will become apparent from the following description. An exemplary embodiment of the invention is explained in more detail with the aid of the drawings, without being restricted thereto. In the drawings:
The present invention relates to a turbomachine 1, in particular a gas turbine.
Of the stator-side assemblies of the turbomachine 1, in
In addition to the guide vane supports 21, 18 and guide vanes 5, 19 shown in
The turbomachine 1 has, in addition to the stator-side assemblies, rotor-side assemblies, not shown in
In the context of the present invention, in each case at least two guide vane supports are jointly fastened to and centered on a flange of the housing 2. Thus, in
Serving to fasten the guide vane supports 21, 18 jointly to the flange 22 of the housing 2 are a plurality of connecting elements 17, which extend through flanges 9, 23 of the guide vane supports 21, 18. According to
A centering of a first guide vane support 21 on the flange 22 of the housing 2 in the axial direction 16 of the turbomachine takes place as a result of the flange 9 of the first guide vane support 21 coming to bear with a first flange surface 4 against a flange surface 3 of the flange 22 of the housing 2.
A centering of the second guide vane support 18 on the same flange 22 of the housing 2 viewed in the axial direction 16 of the turbomachine takes place as a result of the flange 23 of the second guide vane support 18 coming to bear with a flange surface 28 against a second flange surface 20, opposite the first flange surface 4, of the flange 9 of the first guide vane support 21.
Accordingly, the first flange surface 4 of the flange 9 of the first guide vane support 21 contacts the flange surface 3 of the flange 22 of the housing 2. The flange surface 20 of the flange 9 of the first guide vane support 21 contacts the flange surface 28 of the flange 23 of the second guide vane support 18. The flange 9 of the first guide vane support 21 is, accordingly, positioned sandwich-like between the flange 22 of the housing 2 and the flange 23 of the second guide vane support 18.
As can be gathered from
In addition to this centering of the guide vane supports 21, 18 in the axial direction 16 of the turbomachine, a centering of the guide vane supports 21, 18 takes place in the radial direction 15 and the circumferential direction 12 of the turbomachine. A centering of the first guide vane support 21 on the flange 22 of the housing 2 in the radial direction 15 and the circumferential direction 12 of the turbomachine takes place as a result of at least three first centering elements 24 extending through the flange 9 of the first guide vane support 21 into the flange 22 of the housing 2.
The centering of the second guide vane support 18 on the same flange 22 of the housing 2 in the radial direction 15 and the circumferential direction 12 of the turbomachine 1 takes place as a result of at least three second centering elements 33 extending through the flange 23 of the second guide vane support 18 and the flange 9 of the first guide vane support 21 into the flange 22 of the housing 2.
Each first centering element 24 has a first, cylindrical section 6 which projects into a bore-like cutout 8 in the flange 22 of the housing 2. Via a second section 37, each first centering element 24 projects into a slot-like cutout 10 in the flange 9 of the first guide vane support 21.
As can best be gathered from
Extending between the two opposite flats 7 of the cylindrical basic contour of the second section 37 of the respective first centering element 24 are, according to
Each second centering element 33 projects via a first, cylindrical section 6 (see in particular
The second section 37 of each second centering element 33 has in turn a cylindrical basic contour with preferably diametrically opposite flats 7, which run parallel to corresponding surfaces 11 of the slot-like cutout 10 such that a spacing between the same allows a defined minimal relative movement between the second guide vane support 18 and the first guide vane support 21 and thus between the second guide vane support 18 and the housing in the circumferential direction 12 of the turbomachine 1.
Furthermore, the second section 37 of each second centering element 33 has further surfaces 14 which extend between the flats 7 and, according to
As already stated, the connecting elements 17 extend through the two flanges 9, 23 of the two guide vane supports 21, 18. According to
At those circumferential positions at which the first centering elements 24 with connecting elements 17 extending through the same are arranged, there are made, in the flange 23 of the second guide vane support 18, through-bores 27 through which the connecting elements 17 can extend. Viewed in the axial direction 16, these through-bores 27 are aligned sectionally with the slot-like cutouts 10 in the flange 9 of the first guide vane support 21.
As can best be gathered from
Accordingly, in the context of the present invention, a plurality of guide vane supports 21, 18 which in each case serve to receive a plurality of guide vanes 5, 19 are to be jointly fastened to and centered on a flange 22 of the housing 2. As a result, the number of the housing-side flanges required for fastening guide vane supports can be reduced compared with the prior art. As a result, the expenditure required for machining such flanges is reduced. Furthermore, the number of fastening elements and centering elements required for the centering and fastening can be reduced.
The centering of the first guide vane support 21 in the radial direction and the circumferential direction takes place via at least three first centering elements 24. The latter project with cylindrical sections 6 into the bores 8 of the flange 22 of the housing 2, there being formed on these bores 8 the threaded bores 25 into which the connecting elements 17 extend with corresponding external thread sections. For the passage of the connecting elements 17, the first centering elements 24 have the through-bores 26. The first centering elements 24 project with their second sections 37 into slots 10 in the flange 9 of the first guide vane support 21, the longitudinal extent of these slots 10 extending in the radial direction 15. Flats 7 on these second sections 37 of the first centering elements 24 run parallel to corresponding surfaces 11 of the slot-like cutouts 10, a spacing between the flats 7 and the surfaces 11 being dimensioned in such a manner that a minimal circumferential movement for compensation for play is possible between the first guide vane support 21 and the housing 2. Surfaces 13, 14, running substantially perpendicularly to these surfaces 7, 11, of the slots 10 and the second sections 37 of the first centering elements 24 have a markedly greater spacing in order to be able to compensate for a temperature-induced expansion of the assemblies in the radial direction in operation. Via the three first centering elements 24, a clearly defined radial centering of the first guide vane support 21 on the housing 2 is ensured. An appreciable displacement of longitudinal center axes of the components relative to one another is therefore not possible. The centering of the second guide vane support 18 on the housing 2 in the radial direction and the circumferential direction takes place substantially analogously thereto, namely via at least three second centering elements 33. First sections 6 of these second centering elements 33 extend into the bore 8 and a through-bore 32 in the flange 9 of the first guide vane support 21, the second sections 37 of the second centering elements 33 extending into the slot-like cutouts 10 in the flange 23 of the second guide vane support 18. The contouring of the second sections 37 of the second centering elements 33 and of the slots 10 in the flange 23 of the second guide vane support 18 corresponds to the contouring of the second sections 37 of the first centering elements 24 and of the slot-like cutouts 10 in the flange 9 of the first guide vane support 21.
In the region of the flange 9 of the first guide vane support 21, the slot-like cutouts 10 and the through-bores 32 are arranged alternately to one another and evenly distributed in the circumferential direction. In the region of the flange 23 of the second guide vane support 18, the slot-like cutouts 10 and the through-bores 27 are alternately arranged and in turn evenly distributed over the circumference.
All the centering elements 24, 33 are provided with through-bores 26, 34 for the passage of the anchoring elements 17.
The axial centering of the two guide vane supports 21, 18 takes place via the flange surfaces 3, 4 coming to bear against one another and the flange surfaces 20, 28 coming to bear against one another, the centering elements 24, 33 extending through the above-mentioned cutouts 10, 27 and 32, 10 in the flanges 9, 23 of the guide vane supports 21, 18 upon assembly.
As can be gathered from
The invention enables a compact design of a turbomachine.
A plurality of guide vane supports can be simultaneously fastened to and centered on a flange of a housing of the turbomachine.
As a result, the expenditure for machining corresponding flange surfaces is reduced. Moreover, the number of centering elements and fastening elements required is reduced.
The invention can be used both in the field of turbines and in the field of compressors of a gas turbine or in other turbomachines.
Thus, while there have been shown and described and pointed out fundamental novel features of the invention as applied to a preferred embodiment thereof, it will be understood that various omissions and substitutions and changes in the form and details of the devices illustrated, and in their operation, may be made by those skilled in the art without departing from the spirit of the invention. For example, it is expressly intended that all combinations of those elements and/or method steps which perform substantially the same function in substantially the same way to achieve the same results are within the scope of the invention. Moreover, it should be recognized that structures and/or elements and/or method steps shown and/or described in connection with any disclosed form or embodiment of the invention may be incorporated in any other disclosed or described or suggested form or embodiment as a general matter of design choice. It is the intention, therefore, to be limited only as indicated by the scope of the claims appended hereto.
Number | Date | Country | Kind |
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10 2013 017 713 | Oct 2013 | DE | national |
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Number | Date | Country | |
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20150118039 A1 | Apr 2015 | US |