The invention relates to a turbocharger.
From DE 10 2013 002 605 A1 the fundamental construction of a turbocharger is known. A turbocharger comprises a turbine in which a first medium is expanded. A turbocharger, furthermore, comprises a compressor in which a second medium is compressed, utilising energy extracted in the turbine during the expansion of the first medium. The turbine of the turbocharger comprises a turbine housing and a turbine rotor. The compressor of the turbocharger comprises a compressor housing and a compressor rotor. Between the turbine housing of the turbine and the compressor housing of the compressor a bearing housing is positioned, wherein the bearing housing on the one hand is connected to the turbine housing and on the other hand to the compressor housing. In the bearing housing, a shaft is mounted via which the turbine rotor is coupled to the compressor rotor.
From practice it is known that the turbine housing of the turbine, namely a so-called inflow housing, as well as the bearing housing, are connected to one another via a fastening device that is preferentially designed as clamping claw. Such a fastening device, designed as clamping claw, is mounted with a first section of the same to a flange of the turbine housing via fastening means and overlaps with a second section a flange of the bearing housing at least in sections. By way of such a fastening device, the combination of bearing housing and turbine housing is clamped, namely clamping a sealing cover and nozzle ring between turbine housing and bearing housing.
The turbine housing is filled with the first medium to be expanded, in particular with exhaust gas to be expanded. The inflow housing of the turbine housing conducts the exhaust gas in the direction of the turbine rotor. In the inflow housing, there is an overpressure relative to the surroundings, which is removed in the turbine subject to extracting energy during the expansion of the first medium. In the region of the connection of turbine housing or inflow housing and bearing housing, a leakage can occur so that the first medium to be expanded in the turbine can enter the surroundings via the connecting region between turbine housing and bearing housing.
In order to counteract such a leakage of the first medium to be expanded in the turbine, the clamping between turbine housing or inflow housing and bearing housing is increased according to practice, in particular via higher tightening torques for the fastening means, via which the fastening device preferentially designed as clamping claw is mounted to the turbine housing. Despite increased tightening torques, leakage cannot be prevented under certain conditions.
One aspect of the present invention is based on creating a new type of turbocharger with improved connection of inflow housing and bearing housing.
According to a further aspect of the invention resiliently deformable elements are positioned between the first section of the fastening device and nuts of the fastening means, which provide a preloading force.
According to one aspect of the invention the fastening device as such is resiliently deformable and provides a preloading force.
According to one aspect of the invention a resiliently deformable element is positioned between the second section of the fastening device and the flange of the bearing housing, which provides a preloading force.
With all three aspects of the invention present here according to the invention it is possible to improve the connection between inflow housing and bearing housing. The risk of an unintentional leakage into the surroundings of the first medium to be expanded can be minimised.
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.
Exemplary embodiments of the invention are explained in more detail by way of the drawings without being restricted to this. There it shows:
The invention relates to a turbocharger.
Here, the turbine 2 comprises a turbine housing 4 and a turbine rotor 5. The compressor 3 comprises a compressor housing 6 and a compressor rotor 7. The compressor rotor 7 is coupled to the turbine rotor 5 via a shaft 8, which is mounted in a bearing housing 9, wherein the bearing housing 9 is positioned between the turbine housing 4 and the compressor housing 5 and connected both to the turbine housing 4 and the compressor housing 5.
The turbine housing 4 of the turbine 2 comprises an inflow housing 11 and an outflow housing 12. By way of the inflow housing 11, the first medium to be expanded in the region of the turbine 2 can be fed to the turbine rotor 5. By way of the outflow housing 12, first medium expanded in the region of the turbine rotor 5 flows away from the turbine 2.
In addition to the inflow housing 11 and the outflow housing 12, the turbine housing 4 comprises an insert piece 13. The insert piece 13 runs in particular in the region of the inflow housing 11, and namely adjacently to the turbine rotor 5 radially outside adjoining moving blades 14 of the turbine rotor 5.
The turbine housing 4, furthermore, comprises a nozzle ring 15. The nozzle ring 15 is also referred to as turbine glide apparatus.
The inflow housing 11 of the turbine 2 is connected to the bearing housing 9 via a fastening device 17 such that the fastening device 17 is mounted to a flange 18 of the inflow housing 11 with a first section 19, namely via multiple fasteners 20, and that the fastening device 17 with a second section 21 overlaps a flange 26 of the bearing housing 9 at least in sections.
The fastening device 17 is also referred to as clamping claw. Seen in the circumferential direction, the fastening device 13 can be segmented.
Each fastener 20 comprises a threaded screw 22 screwed into the flange 18 of the inflow housing 11 and a nut 23 acting on the other end of the threaded screw 22, wherein by tightening the nuts 23 a defined preloading force can be exerted on the inflow housing 11 and on the bearing housing 9 via the fastening device 17. By way of this, corresponding flanges 24, 25 of nozzle ring 15 and sealing cover 16 are clamped between inflow housing 11 and bearing housing 9.
With the turbocharger of
Here, with the turbocharger of
The number and orientation of the resiliently deformable elements 27, namely of the disc springs, combined stack-like determines on the one hand the preloading force and on the other hand a spring travel in the region of the connection of bearing housing 9 and inflow housing 11 of the turbine, wherein the disc springs can altogether be arranged in the same direction or partly in alternating direction. In particular when all disc springs are arranged in the same direction to form a corresponding stack, a high preloading force with small spring travel can be provided. By arranging the disc springs in alternating direction, a smaller preloading force with greater spring travel is provided.
Accordingly, in the exemplary embodiment of
According to a second aspect of the invention, the fastening device 17, i.e. the clamping claw, as such is resiliently deformable and provides a corresponding preloading force with the help of which different thermal expansions of the assemblies connected to one another caused through thermal loads can be compensated for.
Here,
By tightening the respective nut 23, the second leg 30 is resiliently deformed and deformed in the direction of the first leg 29. By way of this, a preloading force can be provided which can offset or compensate for thermally-induced deformations of the assemblies connected to one another.
In the exemplary embodiment of
The nut 23 of the fastener 20 supports itself on the first end 35 of the helically contoured fastening device 17. Arrows 37 visualise in
Accordingly, in the exemplary embodiments of
A turbocharger according to a third aspect of the invention is illustrated by
This elastically deformable element 39 preferentially comprises a ring element 40 that is C-like in the cross section, in which a coil spring 41 is received or positioned. By tightening the nut 23 of the fastener 20 shown in
In all versions of the invention present here it is possible that the clamping claw or the fastening device 17 is segmented in the circumferential direction, i.e. is composed of multiple segments seen in the circumferential direction.
Thus, while there have 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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102017215569.8 | Sep 2017 | DE | national |