Patent Application
20100278651
The disclosure relates to the field of turbomachines, for example, exhaust-gas turbochargers for supercharged internal combustion engines, and to a fastening of a guide device to a housing of a turbomachine.
Exhaust-gas turbochargers can be used to increase the performance of internal combustion engines (for example, reciprocating-piston engines). An exhaust-gas turbocharger includes an exhaust-gas turbine in an exhaust-gas flow of the internal combustion engine and a compressor in the intake section of the internal combustion engine. A turbine wheel of the exhaust-gas turbine can be set in rotation by the exhaust-gas flow of the internal combustion engine and drives a rotor of the compressor via a shaft. The compressor increases the pressure in the intake section of the internal combustion engine, such that a greater quantity of air can pass into the combustion chambers during an intake. Exhaust-gas turbines can also be used as power turbines. In this case, they can drive via the shaft not the compressor of an exhaust-gas turbocharger but rather a generator or, via a clutch, some other mechanical power part.
Recent developments in the field of modern reciprocating-piston engines have been driven by a desire to reduce emissions, costs and fuel consumption. Here, the supercharging system of the engine can make a contribution to achieving these development aims. In the past, in large engines, use was made predominantly of exhaust-gas turbochargers with turbine and compressor components with fixed geometries. The geometries were designed and adapted for each individual engine. They were however invariable during the operating of the engine. To enable a better adaptation of the exhaust-gas turbocharger to the engine during operation in future, consideration is increasingly being given to the use of turbine geometries which can be adjusted (or varied) during operation (variable turbine geometries, VTG). Here, the opening of the guide blades of a guide device of the exhaust-gas turbine can be varied by a rotation of the guide blades. The use of adjustable turbine geometries is known in the field of small engines, as used, for example, in passenger motor vehicles. In large gas engines, variable turbine geometries are used which require precise regulation of the fuel/air ratio.
The flow components of the turbocharger have, for reasons of efficiency, been developed for high specific throughputs (i.e., high mass flow in relation to geometric size). The moving blades of the turbines of such turbomachines can be subjected to extreme vibration excitation. To ensure reliable operating behavior, precise coordination of the guide device (nozzle ring) and guide blade geometry is desirable in the development of the turbine.
In particular, a problem can arise that the guide blades of the guide device constitute a periodic disturbance for the moving blades of the turbine wheel, with a frequency equal to number of guide blades multiplied by rotational speed. If the frequency corresponds with natural frequencies of the moving blades, resonances can occur. The alternating stresses at the resonances can lead to material damage. It is known that the resonance amplitudes increase with decreasing opening of the guide blades. This can lead to a limitation of the admissible openings of the guide blades. In the variable turbine geometry, it is desirable to have a large available adjustment range of the guide blade opening. If the range of the admissible guide blade openings must be restricted as a result of inadmissible resonances, the benefit of the variable turbine geometry can be reduced.
From “Theoretical and Experimental Analysis of the Reduction of Rotor Blade Vibration in Turbomachinery Through the use of Modified Stator Vane Spacing”, R. H. Kemp, M. H. Hirschberg, W. C. Morgan. NACA Technical Note 4373, 1958, it is known that a non-uniform distribution of the circumferential position of the guide blades can bring about a considerable reduction in the resonance amplitudes. The non-uniform arrangement of the guide blades can be used in many turbomachines in order to reduce resonance amplitudes.
In exhaust-gas turbochargers for large engines, the variable guide device (VTG) can be constructed as a separate module and fastened to the gas inlet and gas outlet housings of the exhaust-gas turbine, as indicated in
An exhaust-gas turbine having a variable guide device is likewise known from U.S. Pat. No. 3,542,484.
A turbomachine is disclosed, including a housing; and a guide device of annular design and having rotatable guide blades arranged distributed along a circumference of the guide device and mounted in each case with a radially running shank in a support ring of the guide device. The support ring includes bearing points for holding the guide blade shanks and fasteners for fastening the support ring to the housing. Free ends of the guide blade shanks are arranged radially within a first radius (r1) and the fasteners are arranged radially outside a second radius (r2). The radius (r1) is smaller than the second radius (r2), such that the fasteners for fastening the support ring to the housing are arranged radially outside the free ends of the guide blade shanks and, the circumferential position of the guide blades may be freely selected within predefined angles without collisions occurring between the guide blade shanks and the fasteners.
Exemplary embodiments of the disclosure will be explained in detail below on the basis of drawings, in which
An adjustable guide device is disclosed for a turbomachine, such as an exhaust-gas turbine, in which fasteners used for fastening to an adjacent housing can be attached independently of the alignment of the guide device with respect to the housing.
In the disclosure the fastening for the attachment of the guide device can be located into the region radially outside the guide blades, in particular radially outside the guide blade shanks. In this way, the circumferential position of the guide blades can be freely selected within the predefined angles. No collisions occur between the guide blades and the fasteners.
The guide blades can be distributed either uniformly or non-uniformly on the circumference.
For the non-uniform arrangement, the guide blades can be realized by non-uniform distribution of the guide blade mounting in the relief ring, support ring and groove ring.
In the guide device designed according to the disclosure shown in
The guide blades 41 can therefore be distributed both uniformly and non-uniformly along the circumference of the support ring without the fasteners 50 and the shanks 42 of the guide blades thereby crossing one another. The non-uniform arrangement of the guide blades 41 can be realized by non-uniform distribution of the guide blade mounting in the relief ring 45, support ring 40 and adjusting ring. It is also possible even in the case of non-uniformly distributed guide blades for the support ring 40 to be positioned at any angle in relation to the gas outlet housing 20 permitted by the bores, which can be arranged distributed along the circumference, for the fasteners. The circumferential position of the guide blades may therefore be freely selected within the predefined angles.
As indicated in
Thus, it will be appreciated by those skilled in the art that the present invention can be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The presently disclosed embodiments are therefore considered in all respects to be illustrative and not restricted. The scope of the invention is indicated by the appended claims rather than the foregoing description and all changes that come within the meaning and range and equivalence thereof are intended to be embraced therein.
| Number | Date | Country | Kind |
|---|---|---|---|
| 08150265.0 | Jan 2008 | EP | regional |
This application claims priority as a continuation application under 35 U.S.C. §120 to PCT/EP2009/050258, which was filed as an International Application on Jan. 12, 2009 designating the U.S., and which claims priority to European Application 08150265.0 filed in Europe on Jan. 5, 2008. The entire contents of these applications are hereby incorporated by reference in their entireties.
| Number | Date | Country | |
|---|---|---|---|
| Parent | PCT/EP2009/050258 | Jan 2009 | US |
| Child | 12835401 | US |
