WO2010063518A1 - Configuration géométrique des aubes de la roue d'un turbocompresseur - Google Patents

Configuration géométrique des aubes de la roue d'un turbocompresseur Download PDF

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Publication number
WO2010063518A1
WO2010063518A1 PCT/EP2009/064141 EP2009064141W WO2010063518A1 WO 2010063518 A1 WO2010063518 A1 WO 2010063518A1 EP 2009064141 W EP2009064141 W EP 2009064141W WO 2010063518 A1 WO2010063518 A1 WO 2010063518A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
impeller
turbine
edge
trailing edge
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/EP2009/064141
Other languages
German (de)
English (en)
Inventor
Andre Kaufmann
Michael Klaus
Florian Kronschnabl
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Aumovio Germany GmbH
Original Assignee
Continental Automotive Technologies GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Continental Automotive Technologies GmbH filed Critical Continental Automotive Technologies GmbH
Publication of WO2010063518A1 publication Critical patent/WO2010063518A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/30—Vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade

Definitions

  • the invention relates to a blade or the blading for an impeller of a turbocharger, for example for a turbine impeller or a compressor impeller.
  • a turbocharger generally has a turbine and a turbine
  • the impeller of the turbine is in this case driven by the exhaust gas mass flow and in turn drives an impeller of the compressor, which compresses fresh air and an internal combustion engine feeds.
  • Both wheels are arranged here on a common shaft. For example, if the wheels are not precisely balanced, unwanted vibrations may occur.
  • turbine blades in turbochargers are subject to excitation by pressure pulsations or periodic pressure fluctuations due to a non-symmetrical inflow geometry.
  • One way to increase the natural frequency is to reduce the axial extent of the blades on the housing contour.
  • a blade of an impeller of a turbocharger wherein the blade in the meridional view at a turbine blade at its trailing edge and at a compressor wheel blade at its leading edge at least in one or more sections or areas a non-linear reduction of the axial Length, and wherein the respective portion and the extent of the reduction of the axial length of the blade is selected such that the blade has a predetermined ratio between natural frequencies and the efficiency loss of the blade or the impeller from the axial reduction of the Shovel results, preferably with the highest possible natural frequencies at the lowest possible loss of efficiency of the blade or the impeller are sought.
  • blades are known from the prior art whose trailing edge in the meridional view either perpendicular (see Fig. 1), resulting in low natural frequencies, or blades with a linear reduction of the axial length over the entire trailing edge, such as in the following Fig. 2 is shown. Although such blades have higher natural frequencies but for a worse efficiency of the associated impeller.
  • the blade according to the invention has the advantage over that it provides a blade with an optimal ratio of natural frequencies and efficiency of the blade or the impeller by suitably adjusting the trailing edge in the turbine blade or the leading edge of the compressor blade and the axial length of the blade at the exit edge or entry edge in at least one or more suitable sections or areas nonlinear reduced.
  • the exit edge of a turbine wheel blade runs in the section in the form of a curve backwards against the flow direction in order to increase the natural frequencies without excessively reducing the efficiency, as in the example in the following FIG A compressor impeller, the leading edge in the section in the form of a curve runs rearwardly in the flow direction in order to increase the natural frequencies without reducing the efficiency too much.
  • a blade of an impeller of a turbocharger wherein the blade of the impeller, i. the turbine wheel blade is reduced at its outlet edge or the compressor wheel blade at its inlet edge in a first, upper region in the axial length and wherein the outlet edge in a second, lower region perpendicular, substantially perpendicular or rearward, against the flow direction runs or in which the leading edge extends in a second, lower region perpendicular, substantially perpendicular or rearward, in the flow direction, so that the loss of efficiency of the impeller does not exceed a predetermined limit value or is within a predetermined tolerance range.
  • the blade of an impeller of a turbocharger has the advantage, in contrast to the blades, as they are known from the prior art, that the blade according to the invention is shortened in the first axial length in the first, upper area, in order hereby the Natural frequencies of the impeller suitable to increase.
  • the second, lower area on the other hand, there is no shortening of the axial length of the blade, for the purpose of increasing its natural frequencies. In other words, either no reduction of the axial length of the blade takes place in the second, lower region, so that the outlet edge or inlet edge runs vertically here.
  • the invention allows a suitable optimum for the ratio of natural frequencies and efficiency of the impeller to be achieved.
  • the upper and / or lower area can be shortened so that at most a certain loss of efficiency occurs.
  • the lower region can be shortened less than the upper region in order to minimize the loss of efficiency. Both the upper region and the lower region are relevant for the loss of efficiency.
  • a reduction of the axial length in the lower region and / or upper region can only take place as far as there is no loss of efficiency of the impeller of, for example, greater than 1%.
  • This value of 1% is exemplary and the invention is not limited thereto. Basically, any other value can be selected which is greater or less than 1%, depending on the function and purpose of the impeller or its blades.
  • the trailing edge (turbine wheel blade) of the blade within the first, upper region and / or the second, lower region is continuously curved or at least partially curved back against the flow direction.
  • the leading edge within the first, upper, and / or second, lower regions is continuously curved or at least partially curved rearwardly in the flow direction. Due to the curvature or partly curved tion of the trailing edge or leading edge in the first, upper region to the rear against the flow direction or to the rear in the flow direction, the natural frequencies of the blade or the impeller can be increased.
  • a curvature or partial curvature of the trailing edge or leading edge in the second, lower region also leads to an additional, albeit minor, increase in the natural frequencies, but the curvature or partial curvature is limited to such an extent that the efficiency of the associated impeller does not decreases over a predetermined amount.
  • the trailing edge (turbine wheel blade) of the blade within the first, upper region and / or the second, lower region is bent back towards the direction of flow.
  • the leading edge within the first, upper region and / or the second, lower region is bent backwards in the flow direction.
  • the trailing edge or leading edge has the form of a continuous straight line in the first, upper region or second, lower region, for example, or has at least one or more rectilinear sections.
  • the bending of the trailing edge towards the rear contrary to the flow direction or at the entry edge to the rear in the direction of flow, causes an increase in the natural frequencies of the blade or the impeller.
  • the second, lower region is bent less or curved in the direction of the turbine blade back against the flow direction or in the Ver Whyrrad- maretzei curved backwards in the flow direction than the first, upper region in order not to reduce the efficiency of the impeller too strong or to a predetermined extent.
  • At least the transition between the first, upper region and the second, lower region of the outlet edge (turbine wheel blade) or the leading edge (compressor wheel blade) preferably rounded. This is both thermodynamic and structural-mechanical as well as from a manufacturing point of view more advantageous over a sharp bend as a transition.
  • the trailing edge (turbine wheel blade) or leading edge (compressor wheel blade) of the blade has an S-shape or the first, upper region and the second, lower region of the outlet edge or inlet edge together form an S-shape ,
  • the S-shape is advantageous especially with respect to mechanical stresses which can occur in the blade.
  • the upper part of the S-shape is, for example, convex or arched outwards, and the lower part of the S-shape is concave or arched inwards.
  • the blade is a blade of a turbine wheel and / or a compressor wheel, for example a radial turbine or a radial compressor.
  • the blade can be produced by casting (metal casting) and / or milling.
  • a casting mold can be produced in which the trailing edge (turbine wheel blade) or leading edge (compressor wheel blade) of the blade already has the finished or substantially finished shape.
  • the blade can also be milled as a whole or by means of
  • Milling the contour of the trailing edge or the leading edge are formed according to the invention.
  • At least one, several or all blades may be formed according to the blade according to the invention.
  • This has the advantage that due to the high natural frequencies of the respective impeller, which are higher than the excitation frequency of the impeller, the occurrence of unwanted, harmful resonances can be prevented.
  • FIG. 1 is a meridional view of a turbine comprising the turbine housing and the turbine runner, which has prior art blades;
  • FIG. 2 is a meridional view of a turbine comprising the turbine housing and the turbine runner having rotor blades according to another embodiment of the prior art
  • FIG. 3 shows a meridional view of a turbine comprising the turbine housing and the turbine runner, which has rotor blades according to a first embodiment of the invention, compared to an embodiment according to the prior art;
  • FIG. 4 is a meridional view of a turbine comprising the turbine housing and the turbine runner having blades according to a second embodiment of the invention compared to the embodiment described in FIG. 3;
  • FIG. 5 is a meridional view of a turbine comprising the turbine housing and the turbine runner having blades according to a third embodiment of the invention compared to a prior art embodiment.
  • FIG. 1 shows a meridional view of a turbine of a turbocharger having a turbine housing and a turbine wheel.
  • the turbine runner 14 of the turbine is arranged on a shaft 12.
  • the turbine runner 14 in this case has blades 16 according to the prior art. As can be seen from the detail in FIG. 1 of a blade 16 of the turbine runner 14, this has a continuous vertical exit edge 18. This means that the blade 16 has no reduction of the axial length over its entire outlet edge 18. In this way, although a good efficiency of the turbine can be achieved, but the natural frequencies of this blade 16 and thus of the turbine runner 14 are comparatively low. Due to the low natural frequencies, it may therefore come to unwanted resonances, which can lead to a blade fracture in the worst case.
  • a further meridional view of a turbine of a turbocharger is shown, which has a turbine housing and a turbine wheel.
  • a rotor blade 16 of the turbine runner 14 of a turbocharger is shown.
  • the turbine runner 14 of the turbine is arranged in the turbine housing 10 on a shaft 12.
  • the blades 16 of the turbine runner 14 in this case represent a further embodiment, as is known from the prior art.
  • one of the rotor blades 16 of the turbine runner 14 is shown in the meridional view in FIG. 2, one of the rotor blades 16 of the turbine runner 14 is shown.
  • the rotor blade 16 does not have a vertical exit edge 18, but rather a rectilinear outlet edge 20 which is inclined towards the rear or against the flow direction.
  • the flow direction of the exhaust gas mass flow is shown by arrows in all figures.
  • the vertical exit edge 18 according to the embodiment in FIG. 1 is initially drawn by a solid line for comparison.
  • the inclined exit edge 20 according to the second embodiment of the prior art is drawn in FIG. 2 with a dashed line.
  • a triangular section 22 has been removed, so to speak, in order to provide the rearward or backward inclined edge 20 of the moving blade 16.
  • a non-linear reduction of the axial length of the blade takes place at least in a section of the trailing edge, in order to optimize the ratio of natural frequencies and efficiency of the blade or of the impeller, so that the highest possible gene frequencies at the lowest possible loss of efficiency of the blade or the impeller result.
  • Fig. 3 is a meridional view of a turbine of a turbocharger is shown, which has a turbine housing and a turbine runner 14.
  • a rotor blade 16 of the turbine runner 14 according to a first embodiment of the
  • the trailing edge 24, 30 of the rotor blade 16 according to the invention is now composed, for example, of two regions 26, 28.
  • the exit edge 24, 30 runs initially perpendicularly or substantially vertically.
  • the course of the trailing edge 24 is directed back or the trailing edge 24, 30 is bent backwards or counter to the flow direction.
  • the course of the exit edge 24, 30 is bent in the upper region 26 to the rear against the flow direction.
  • FIG. 3 two examples of a trailing edge 24, 30 of a rotor blade 16 according to the first embodiment of the invention are shown.
  • the first exit edge 24 according to the invention is shown with a dashed line in FIG. 3 and the second exit edge 30 according to the invention with a dotted line.
  • the two exit edges 24, 30 according to the invention both have a The lower region 26, in which the exit edge 24, 30 of the rotor blade 16, for example, is perpendicular.
  • the lower region 26 can extend, for example, up to half the blade height, as indicated in FIG. 3, or up to a first third or second third of the blade
  • Bucket height or even up to a quarter or even up to three quarters of the blade height is not limited to these sizes of the lower portion 26.
  • the upper portion 28 and the corresponding corresponding lower portion 26 can be chosen arbitrarily large, depending on the function and purpose.
  • the aforementioned sizes for the lower region 26 are purely exemplary.
  • the blade 16 whose trailing edge 24, 30 in the lower portion 26 perpendicular, substantially perpendicular or slightly against the flow direction bent back or curved.
  • the trailing edge 24, 30 is further bent off or curved in the opposite direction to the flow direction.
  • the exit edge 24, 30 in the upper region 28 more towards the rear, directed against the flow direction than in the lower region 26 in order to increase the natural frequencies of the impeller 14. The fact that the lower portion 26 is less curved backwards, an excessive reduction of the efficiency of the impeller 14 is avoided.
  • the two illustrated exit edges 24, 30 differ from each other, as shown in Fig. 3, that the second exit edge 30 in the upper region 28 is directed more towards the rear or against the flow direction than the first inventive exit edge 24. Furthermore extends the trailing edge 24 of the first embodiment of the invention the blade 16 in its upper portion 28 in an arc towards the rear against the flow direction.
  • the trailing edge 30 of the second embodiment of the invention is the blade 16 again in its upper portion 28 bent back linearly, wherein the transition of the trailing edge 30 between the lower portion 26 and the upper portion 28 is preferably rounded.
  • the first and second inventive outlet edge 24, 30 each have a better or higher efficiency of the turbine than the outlet edge 20 according to the prior art, as shown in Fig. 2.
  • the first and second exit edges 24, 30 of the invention in the lower portion 26 are, for example, perpendicular, i. the respective blade 16 is not reduced in length in the axial direction, in contrast to the exit edge 20 according to the prior art, as shown in Fig. 2.
  • better flow guidance is achieved both in the upper and lower regions of the outlet edge, as a result of which the efficiency increases.
  • the first exit edge 24 according to the invention which is drawn with a dashed line, has slightly lower natural frequencies than the exit edge 20 according to the prior art, as is also shown in FIG. 2.
  • the natural frequencies of the first exit edge 24 according to the invention are higher than the natural frequencies of the other exit edge 18 according to the prior art, as shown in Fig. 1, which is unabridged in length in the axial direction.
  • the natural frequencies of the second outlet edge 30 according to the invention which is drawn in with a dotted line, are greater than the natural frequencies of the first outlet edge 24 according to the invention, since the second outlet edge 30 according to the invention continues further counter to Flow direction runs. However, this somewhat reduces the efficiency.
  • the moving blades 16 according to the invention are preferably reduced substantially only in the region in their axial length, which leads substantially to an enlargement of the natural frequencies, here in the upper region 28 ,
  • FIG. 4 another meridional view of a turbine of a turbocharger is shown having a turbine housing and a turbine runner 14. More specifically, the turbine runner 14 is shown having blades 16 according to a second embodiment of the invention, with a blade 16 shown in a meridional view.
  • the first, inventive exit edge 24 according to FIG. 3 is shown with a solid line in FIG. 4 and furthermore an example of an exit edge 32 of a rotor blade 16 according to the second embodiment according to the invention with a dashed line.
  • the trailing edge 32 of the rotor blade 16 of the turbine runner 14 according to the second embodiment of the invention has an S-shape or substantially an S-shape.
  • the outlet edge 32 is, for example, curved inward in the lower region 26, curved in an arc against the direction of flow, or concave.
  • the first exit edge 30 of the invention as shown in solid line in FIG. 4 and also shown in FIG. 3, is perpendicular in the lower region 26.
  • the trailing edge 32 according to the second embodiment of the invention in the upper portion 28 is curved outward or convex.
  • the division of the two regions 26 and 28 can be varied as desired. This applies to all embodiments of the invention.
  • the trailing edge can also be divided into more than two areas. This also applies to all embodiments.
  • the S-shape of the Exit edge 32 of the blade 16 is particularly advantageous for the occurring mechanical stresses in the blade 16. Due to the S-shape of the trailing edge 32 of the blade 16, the stress due to the centrifugal force in the lower region or lower point A of the blade 16 can be reduced.
  • FIG. 5 shows a meridional view of a turbine of a turbocharger, which has a turbine housing 10 and a turbine runner 14.
  • the illustrated turbine runner 14 hereby comprises moving blades 16 according to a third embodiment of the invention, wherein a moving blade 16 is shown in a meridional view.
  • the first embodiment of the trailing edge 18 of a blade 16 according to the prior art is shown as a solid line for comparison.
  • This rotor blade 16 has already been shown in FIG. 1 and is characterized in that the outlet edge 18 is designed to be continuous vertically.
  • FIG. 5 shows three examples of exit edges 34, 36, 38 for a rotor blade 16 according to the invention of a turbine wheel 14 in the form of a dashed line 34, a dot-dash line 36 and a dotted line 38.
  • the three curves for the exit edge 34, 36, 38 are characterized in that they are curved backwards, against the direction of flow.
  • the trailing edge 34, 36, 38 according to the invention is not formed in the form of a straight line 20, which is simply inclined backwards, as in the prior art in FIG 2 is shown.
  • the trailing edge 34, 36, 38 of the blade 16 describes a curve or a curve which is curved backwards against the flow direction, wherein the outlet edge 34, 36, 38 itself no continuous straight line forms, but no or at most only at least one or more straight line sections.
  • the blade 16 with the outer, inventive trailing edge 34 which is drawn with a dashed line, has lower natural frequencies and a higher efficiency than, for example, the blade 16 with the innermost, inventive trailing edge 38, the Fig. 5 is shown with a dotted line.
  • the natural frequencies of the rotor blades 16 with the three exit edges 34, 36, 38 according to the invention each have higher natural frequencies than the rotor blade 16 with the exit edge 18 according to the prior art.
  • the turbine efficiency of the rotor blades 16 with the three exit edges 34, 36, 38 according to the invention is less than the efficiency of the rotor blade 16 with the exit edge 18 according to the prior art.
  • the blades 16 counteract the occurrence of unwanted resonances counter to the direction of flow according to the invention with the freely curved backward profile of the respective outlet edge 34, 36, 38 in contrast to the blades 16 according to the prior art, such as e.g. in Figs. 1 and 5 is shown.
  • the loss of efficiency due to the reduction of the axial length is preferably minimized only in a certain, selected area or areas. Furthermore, the natural frequencies in a desired range or ranges can be increased and the loading of the blades by resonances can be avoided. This applies to all embodiments of the invention.
  • the present invention can be used with both turbine runners and compressor runners. The above-described embodiments of the present invention have been explained with reference to a turbine runner and its blades. However, the embodiments apply, as described above, also substantially corresponding to a compressor impeller and its blades or blades and are therefore not repeated for this purpose.
  • Turbine wheels or compressor wheels for example, radial turbine wheels or radial compressor wheels
  • at least one, two, several or all blades can be formed according to the blade or rotor blade according to the invention.
  • the impeller i. a turbine runner or a compressor runner, for example cast and / or milled, to name two manufacturing methods as examples.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne une aube (16) d'une roue (14) d'un turbocompresseur. L'aube présente en vue méridienne, sur son bord de fuite (24, 30) dans le cas d'une aube de roue de turbine ou sur son bord d'attaque dans le cas d'une aube de roue de compresseur, une réduction non linéaire de sa longueur axiale au moins sur une ou sur plusieurs sections. Chaque section et la réduction de la longueur axiale de l'aube sont choisies pour que l'aube présente un rapport fréquences propres/perte de rendement de l'aube ou de la roue qui est prédéterminé.
PCT/EP2009/064141 2008-12-01 2009-10-27 Configuration géométrique des aubes de la roue d'un turbocompresseur Ceased WO2010063518A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008059874.7 2008-12-01
DE200810059874 DE102008059874A1 (de) 2008-12-01 2008-12-01 Geometrische Gestaltung der Laufradschaufeln eines Turboladers

Publications (1)

Publication Number Publication Date
WO2010063518A1 true WO2010063518A1 (fr) 2010-06-10

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PCT/EP2009/064141 Ceased WO2010063518A1 (fr) 2008-12-01 2009-10-27 Configuration géométrique des aubes de la roue d'un turbocompresseur

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WO (1) WO2010063518A1 (fr)

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DE102012212896A1 (de) 2012-07-24 2014-02-20 Continental Automotive Gmbh Laufrad eines Abgasturboladers
DE102016220133A1 (de) * 2016-10-14 2018-04-19 Bosch Mahle Turbo Systems Gmbh & Co. Kg Laufrad für einen Abgasturbolader und Abgasturbolader mit einem solchen Laufrad
JP6998462B2 (ja) 2018-06-22 2022-01-18 三菱重工エンジン＆ターボチャージャ株式会社 回転翼及びこの回転翼を備える遠心圧縮機

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US20050106013A1 (en) * 2003-11-19 2005-05-19 Ghizawi Nidal A. Profiled blades for turbocharger turbines, compressors, and the like
US20070231141A1 (en) * 2006-03-31 2007-10-04 Honeywell International, Inc. Radial turbine wheel with locally curved trailing edge tip

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US20050106013A1 (en) * 2003-11-19 2005-05-19 Ghizawi Nidal A. Profiled blades for turbocharger turbines, compressors, and the like
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116306180A (zh) * 2023-05-22 2023-06-23 陕西空天信息技术有限公司 一种叶轮辅助分析方法、装置、设备、介质及产品
CN116306180B (zh) * 2023-05-22 2023-08-01 陕西空天信息技术有限公司 一种叶轮辅助分析方法、装置、设备及介质

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