EP2877701B1 - Rotor d'un turbocompresseur - Google Patents

Rotor d'un turbocompresseur Download PDF

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Publication number
EP2877701B1
EP2877701B1 EP13733304.3A EP13733304A EP2877701B1 EP 2877701 B1 EP2877701 B1 EP 2877701B1 EP 13733304 A EP13733304 A EP 13733304A EP 2877701 B1 EP2877701 B1 EP 2877701B1
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EP
European Patent Office
Prior art keywords
blade
rotor
region
thickness distribution
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.)
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EP13733304.3A
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German (de)
English (en)
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EP2877701A1 (fr
Inventor
Michael Klaus
Timo MERENDA
Bernhard LEHMAYR
Meinhard Paffrath
Ivo Sandor
Endre Barti
Utz Wever
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Continental Automotive GmbH
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Continental Automotive GmbH
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Publication of EP2877701A1 publication Critical patent/EP2877701A1/fr
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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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/024—Units comprising pumps and their driving means the driving means being assisted by a power recovery turbine
    • 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
    • F05D2240/20—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
    • F05D2240/301—Cross-sectional characteristics
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave

Definitions

  • the invention relates to an impeller of an exhaust-gas turbocharger, which has an impeller hub and impeller blades arranged on the impeller hub, which each have a fluid inlet edge and a fluid outlet edge and which each have a blade thickness distribution running in the flow direction of the fluid mass flow.
  • turbocharged supercharged combustion engines Due to the ever stricter laws regarding the emission of exhaust gases into the environment more and more vehicles are equipped with supercharged turbocharger diesel or gasoline engines. In addition, the requirements for the stationary behavior of the internal combustion engine, d. H. Power, torque and consumption need to be further improved. In turbocharged supercharged combustion engines in particular, the transient response is essential.
  • the simplest possible rotor blading allows turbomachinery with a small moment of inertia, which allows a better transient response can be achieved.
  • the minimum possible blade thickness is limited by the manufacturing process and the strength properties of the materials used.
  • centrifugal forces act on the impeller blades aerodynamic forces in the form of shear stresses and compressive forces.
  • Turbomachine flow creates pressure nonuniformities which affect the impeller blades at each revolution.
  • the impeller vanes must have a stiffness that raises their natural frequency so far that they can not be excited by these pressure pulsations to critical vibrations.
  • the actual thickness distribution is typically covered by a filling radius in the transition to the hub.
  • This radius the lower the stresses and the higher the rigidity of the blade.
  • Production and aerodynamic criteria limit the maximum size of the filling radius.
  • the impeller blade at its top ie in the radial edge region, thinner than at the hub. If the rigidity or the natural frequency of the blade is not sufficient, often the blade height, at the position of greatest blade height, is shortened in the flow direction, which however is aerodynamically disadvantageous. Another possibility is to make the blade thicker overall.
  • a blade of an impeller of a turbocharger which has a non-linear reduction of the axial length in the meridional view at its trailing edge at a turbine blade or at its leading edge at a Ver emphasizerradschaufel at least in one or more sections, and wherein the respective portion and the reduction the axial length of the blade are selected such that the blade has a predetermined ratio of natural frequency and a loss of efficiency of the blade or the impeller.
  • an impeller blade which is reduced in the meridional view at its trailing edge at a turbine wheel blade or at its leading edge at a Ver Whyrradschaufel in a first, upper region in the axial length and wherein the trailing edge in a second, lower region perpendicular, substantially perpendicular or to the rear, contrary to the flow direction, runs, or the leading edge in a second lower portion perpendicular, substantially perpendicular or rearward, in the flow direction, so that the loss of efficiency of the impeller is limited in a predetermined range.
  • Generic wheels which are suitable for exhaust gas turbocharger, are for example in the US 2005/0260074 A1 .
  • the object of the invention is to provide an impeller of an exhaust gas turbocharger, which has improved properties during operation.
  • An impeller of an exhaust gas turbocharger according to the invention has an impeller hub and impeller blades arranged on the impeller hub, each of which has a fluid inlet edge, a fluid outlet edge and a blade height and a blade thickness distribution.
  • the impeller according to the invention is characterized in that the blade thickness distribution is selected such that the impeller blades along their extension from the fluid inlet edge to the fluid outlet edge, ie in the flow direction of the fluid flow, at least one transition between a stiffness-oriented blade thickness distribution and a inertial and voltage-oriented blade thickness distribution over the blade height exhibit.
  • the stiffness oriented blade thickness distribution is a bottle-shaped blade thickness distribution over the blade height and the inertia and stress oriented blade thickness distribution is an eiffel tower blade thickness distribution over the blade height.
  • a bottle-shaped blade thickness distribution represents a stiffness-optimized geometry and, at least on one side face of the impeller blade, but preferably on both sides, pressure side and suction side, seen in a sectional plane perpendicular to the impeller axis of rotation, a bottle-shaped side surface contour.
  • This side surface contour is characterized inter alia by a curvature change region, in which from radially inward to radially outward, with respect to an imaginary center line of the considered impeller vane cross section, convex profile of the side surface contour, ie the side surface curvature, merges into a concave profile.
  • the mentioned side surface contour between the blade root and the curvature change region has in each case a straight or a curved first transition region.
  • the result is a basic shape with a bulbous, stiff foot, wherein the blade thickness initially decreases radially outward until in the curvature change region slowly (bottle belly).
  • the blade thickness first decreases more strongly with a convex course of the side surface contour. Following this, the side surface contour merges into a concave profile, so that the blade thickness decreases beyond this region of the blade height to become weaker radially outward.
  • the side surface contour of the respective impeller vane has a straight or a curved second transition region (bottleneck) between its radial blade edge and its curvature change region.
  • a total of a side surface curvature of the impeller blade which is similar to the contour line of a bottle and therefore named here so.
  • An eiffel tower-shaped blade thickness distribution represents a geometry that is optimized in terms of inertia and stress and has a concave profile of the side surface contour, ie the side surface curvature of the rotor blade in the radial direction outwards, at least on one side surface of the impeller blade, but preferably on both sides (pressure side and suction side), so that the Blade thickness over the blade height decreases radially outward becoming weaker.
  • the outlet of the side surface curvature in the direction of the radial blade edge can be designed so that the concavely curved profile of the side surface contour of the respective impeller blade, in the direction of the radial blade edge, continues continuously or in a straight, inclined to an imaginary center line of the impeller blade cross-section or parallel to this center line, so that there is a transition region having a trapezoidal taper in the cross section of the impeller blade radially outward or a constant thickness.
  • the outlet in the blade root area can result from the curvature of the blade side wall or with an additional Foot rounding be executed.
  • there is a side surface curvature of the impeller blade which is similar to the contour line of the Eiffel Tower and therefore therefore named here.
  • an impeller according to the invention is optimized with regard to the properties required by it during operation, in particular with regard to its rigidity, inertia and strength.
  • the claimed blade thickness distribution can be used for cast, eroded and also milled radial, radial-axial and axial-turbines or compressors.
  • the invention favors the production engineering boundary conditions during casting with regard to minimum distances between adjacent blades.
  • the blade thickness distribution When produced by casting, it is possible to set the blade thickness distribution as desired both over the blade height and over the blade length.
  • This possibility is used in the present invention in that an inertia-optimized thickness distribution in areas of the impeller blades, which are of minor importance for the blade stiffness, as well as a stiffness-optimized thickness distribution in areas of the impeller blades, which are in danger of vibration, is made.
  • the areas of little importance for overall blade stiffness are the areas of low blade height in the radial direction.
  • the areas with a high influence on the blade rigidity are the areas with large blade height in the radial direction.
  • the thickness distribution strategy according to the invention is based on a combination of the two fundamentally different blade thickness distributions, namely, for example, one eiffel tower-shaped blade thickness distribution and a bottle-shaped blade thickness distribution such that the impeller blades have along their extension from the fluid inlet edge to the fluid outlet edge at least one transition between a stiffness-oriented blade thickness distribution and a inertial and voltage-oriented blade thickness distribution over the blade height.
  • the Eiffel Tower shape is inertia and stress optimized, while the bottle shape is stiffness-optimized.
  • FIG. 1 shows a sketch to illustrate an impeller of an exhaust gas turbocharger, which is in the illustrated embodiment, for example, a turbine wheel of an exhaust gas turbocharger. If it is a turbine wheel, so this is located between the turbine housing 6 and the bearing housing 7 of the exhaust gas turbocharger and rotates during operation of the exhaust gas turbocharger to an impeller axis 10.
  • the impeller 1 is rotatably connected by means of its impeller hub 2 with a rotor shaft 11.
  • On the impeller hub 2 equidistantly impeller blades 3 are arranged in the circumferential direction of the impeller, which are fixed by means of their blade root B1 on the impeller hub 2.
  • the impeller hub 2 and the impeller blades 3 are manufactured in one step and materially connected to each other.
  • the impeller blades 3 each have a fluid inlet edge 4, 5 'and a fluid outlet edge 5, 4'. Since a turbine impeller and a compressor impeller hardly differ in the schematic representation, are in FIG. 1 Both versions are summarized in a representation. The main difference in the schematic representation consists in the flow direction of the fluid flow.
  • the turbine runner which is acted upon by exhaust gases of an internal combustion engine, has an exhaust gas inlet edge 4 and an exhaust gas outlet edge 5.
  • the flow direction of the exhaust gas is in the FIG. 1 indicated by arrows and designated by the reference numeral 8.
  • the compressor impeller which is supplied with fresh air, has a fresh air inlet edge 5 'and a fresh air outlet edge 4'.
  • the flow direction of the fresh air is in the FIG. 1 indicated by arrows which are designated by the reference numeral 8 '.
  • FIG. 2 shows three examples of blade thickness distributions over the blade height 9 of an impeller blade 3 in a sectional view with a plane perpendicular to the impeller axis 10 extending cutting plane. It is in the left illustration in FIG. 2 a bottle-shaped blade thickness distribution, in the middle representation of FIG. 2 an eiffel tower-shaped blade thickness distribution and in the right-hand illustration of FIG. 2 illustrates a trapezoidal blade thickness distribution.
  • the respective blade thickness distribution is formed here by way of example symmetrically to an imaginary blade center line 13 of the respective impeller blade cross-section.
  • a blade thickness distribution is such that two fundamentally different blade thickness distributions, such as the Eiffel Tower shape and the bottle shape, are alternated or combined in a particular manner.
  • the Eiffel Tower shape is inertial and tension optimal.
  • the bottle shape is stiffness-optimal.
  • the Eiffel Tower shape is characterized in particular by a outgoing from the foot, radially outward toward the inside, to the imaginary center line 13 to, curved course of the side surface contour, wherein the blade thickness decreases in the radial direction outwardly weakening.
  • the side surface contour can continue to run in continuation of the Eiffel Tower shape, as can be seen from the middle illustration of FIG. 2 can also be in a straight, to an imaginary center line of the impeller blade inclined or parallel to this center line course, so that there is a transition region whose cross-sectional area has a trapezoidal taper radially outward or a constant thickness.
  • the foot area may result from the curvature of the side wall of the scoop. Alternatively, the foot area can also be designed with an additional cognitive task.
  • the bottle shape in the left illustration of FIG. 2 in contrast, is characterized in particular by a curvature change area, in which the Side surface contour of the impeller blade from radially inward to radially outward passes from a convex curvature into a concave curvature.
  • the trapezoidal blade thickness distribution as shown in the right-hand illustration of FIG. 2 is shown, is used in known blade thickness distributions according to the prior art and is in the flow direction between the fluid inlet and the fluid outlet edge continuously before.
  • FIG. 3 shows an example of a stiffness-optimized blade thickness distribution, which is referred to as bottle shape and a inertia and voltage optimized blade thickness distribution, which is referred to as Eiffelturmform in a sectional view according to a sectional plane perpendicular to the impeller axis of rotation 10.
  • the respective blade thickness distribution in FIG. 3 is subdivided into the areas B1, C2, B4 and B5 in the bottle shape into areas B1 to B5 and in the Eiffel tower shape, in both cases B1 the blade root area and B5 the radially outer blade edge area.
  • a first transitional region B2 (bottle belly), a curvature change region B3 (bottle shoulder) and a second transition region B4 (bottleneck) are predetermined.
  • a concave area C2 and also a transition area B4 are defined between the blade root B1 and the blade edge area B5.
  • the foot region or blade root B1 in which the blade 3 is connected to the hub, in each case has the greatest thickness and preferably merges with a foot rounding 12 into the impeller hub 2.
  • the radially outer blade edge closes the side surface contour with a defined edge and is preferably slightly rounded in each case, wherein the rounding follows the respective circumferential circle of the impeller or results from it.
  • the side surface contour of the impeller blade may be straight or preferably slightly convexly curved in the first transition region B2 provided between the foot region B1 and the bending change region B3.
  • the change of curvature region B3 takes place - as already stated above - a transition of the side surface contour of a convex curvature in a concave curvature.
  • the Eiffel Tower shape is characterized in particular by the adjoining the foot area concave area C2, in which the side surface contour in the radial direction R outwardly to the imaginary center line 13 to, concave curved course, the blade thickness decreases in the radial direction outwardly weakening.
  • the side surface contour can again run slightly concavely curved or merge into an inclined or center line parallel to an imaginary center line of the impeller blade cross section. so that there is a transition region whose cross-sectional area has a trapezoidal taper radially outward or a constant thickness.
  • the extending in the radial direction R sections of the individual areas B1 to B5 and C2 can be optimized in their extent and their relationship to each other depending on the specific application, the division of the sections of the individual areas B1 to B5 also depending on the position along the extension of the impeller blade between the fluid inlet edge and the fluid outlet edge and the blade height present there takes place.
  • the gradient of the course of the side surface contour in the bending change region B3 can be optimized depending on the particular application in order to achieve the best possible compromise between stiffness and inertia.
  • FIG. 4 Two examples illustrating blade thickness distributions according to the invention are schematically shown in FIG FIG. 4 shown in meridional view of the impeller blades.
  • the left-hand illustration refers to a radial-axial impeller and the right-hand depiction to a radial impeller.
  • the embodiments described below can be used both in turbine wheels and in compressor wheels.
  • the fluid inlet edge 4 is the area of small blade height (in each case the left-hand area of the illustration) and the fluid outlet edge 5 is the area of large blade height (in each case the right-hand area of the illustration).
  • the foot areas are not drawn for the sake of clarity. Since the illustrated meridional view represents a projection of the three-dimensional impeller vane onto a two-dimensional plane, the deflection angle of the vane is not captured in the representations. Due to the real existing deflection angle and the consideration of the thickness distributions in a plane perpendicular to the impeller axis cutting plane are, in contrast to the representation, the real contour curves of the side surface contours in this cutting plane on both sides of the impeller blades in the in FIG. 4 Sectional planes Abis D shown are generally not completely symmetrical, although they have in principle the same contour. Depending on the angle of deflection of the blade arise in reality on both sides slightly different contour curves.
  • sectional views A to D according to the FIG. 4 are thus understood as a blade thickness distribution perpendicular to the skeletal surface (which is approximately given by an imaginary center line of the profile over the blade length and appears in the respective section as the center line) of the blade profile.
  • the thickness distribution illustrated in the right-hand illustration has an eiffel tower-shaped blade thickness distribution in the region of small radial blade height and at the same time greater distance from the impeller rotational axis, section AA, and goes in the axial direction (to the right in the illustration), as from the sections BB and CC is continuously in a bottle-shaped blade thickness distribution in the range of large radial blade height at the same time smaller distance to the impeller axis 10, section DD, over.
  • Such a distribution corresponds to the rule that with a large blade height, in particular a stiffness-oriented blade thickness distribution is advantageous, whereas with a small blade height a inertia-oriented and tension-oriented blade thickness distribution is to be preferred.
  • this distribution has the additional effect that the larger mass arrangements required for the rigidity, in the form of the "bottle belly" of the bottle-shaped blade thickness distribution, are arranged closer to the impeller rotational axis and thus have less negative influence on the inertia of the impeller and thus on the transient behavior of the turbocharger.
  • the eiffel tower-shaped blade thickness distribution in section A-A initially goes in the direction of greater blade height (in the illustration to the right) into the bottle-shaped blade thickness distribution, section C-C.
  • This additional transition and the eiffel tower-shaped blade thickness distribution thus present at the fluid outlet / fluid inlet edge 5, 5 'can optionally be used on the one hand to reduce critical stresses in the hub region of the fluid outlet / fluid inlet edge 5, 5' and on the other hand to aerodynamic advantages by reducing the thickness the Fluidaus- / fluid inlet edge 5, 5't. to achieve the appropriate edge radius.
  • the axial transition regions between different blade thickness distributions have Cross-sectional shapes corresponding to a combination of an eiffel tower-shaped blade thickness distribution and a bottle-shaped blade thickness distribution.
  • FIG. 5 shows an example for illustrating a specific embodiment of the invention.
  • This embodiment has the advantage that a production of the impeller blades is made possible in the milling process shown.
  • FIG. 6 shows examples to illustrate further embodiments of the invention.
  • FIG. 6 Examples of a different, asymmetrical blade thickness distribution on the suction side S and the pressure side P of the impeller blades 3, wherein the two outer contours with respect to an imaginary center line have different contour curves.
  • the designation of the suction side and the pressure side of the impeller blades are chosen here freely and serve only to distinguish the two sides of the blade.
  • Presentation 6.1 of the FIG. 6 shows, for example, a trapezoidal straight radially outwardly decreasing blade thickness distribution on the suction side S and an eiffel tower-shaped blade thickness distribution on the pressure side P of the impeller blade 3.
  • Figure 6.2 shows an eiffel tower-shaped blade thickness distribution on the suction side S and a bottle-shaped blade thickness distribution on the pressure side P.
  • Figure 6.3 shows again a bottle-shaped blade thickness distribution on the suction side S and a conical Vane thickness distribution on the pressure side P.
  • P can be counteracted thermally induced stresses in the blade material, residual stresses of the blade material and during operation occurring aerodynamic forces.
  • this can also be done by the fact that the blade is not exactly aligned with radial rays, but slightly inclined or curved in the circumferential direction.
  • FIG. 7 shows a superimposed view of sectional views illustrating various blade thickness distributions. These blade thickness distributions are those already described in the above FIG. 2 shown embodiments.
  • the lowest blade thickness that can be implemented in terms of manufacture extends over larger blade height portions of the impeller blade in the case of the bottle-shaped blade thickness distribution as well as in the eiffel tower-shaped blade thickness distribution than in the case of a conical blade thickness distribution.
  • an inertia reduction is achieved in the blade thickness distribution according to the invention.
  • the stiffness compared to the conical Blade thickness distribution are maintained as nearly the maximum thickness in the blade root area is used over larger blade height portions.
  • the thickness maximum at the hub can be placed in the flow direction to an almost arbitrary position. If it is in an ideal position perpendicular to the swing axis of the lowest eigenmode, then the maximum blade thickness can be minimized because the rigidity is optimized. This benefits the inertia of the turbocharger.
  • the wedge angle of the fluid outlet edge can be optimized by positioning the maximum thickness at the hub towards more acute exit angles.
  • the radial blade thickness distribution of the fluid outlet edge 5 is again designed in Eiffel tower shape, as in the left display of FIG. 4 is shown at the section DD.
  • a flatter wedge angle at the fluid outlet edge 5 of turbine runner blades is possible by the blade thickness distribution according to the invention.
  • the object of the invention can also be used in an advantageous manner to reduce the so-called cut-back by an improved rigidity of the turbine blading.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)

Claims (11)

  1. Rotor (1) d'un turbocompresseur à gaz d'échappement, qui présente un moyeu de rotor (2) et des aubes de rotor (3) disposées sur le moyeu de rotor, qui présentent à chaque fois une arête d'attaque de fluide (4), une arête de fuite de fluide (5), une embase d'aube (B1), un bord d'aube radial (B5) et une hauteur d'aube (9) ainsi qu'une répartition d'épaisseur d'aube, caractérisé en ce que la répartition d'épaisseur d'aube est sélectionnée de telle sorte que les aubes de rotor (3) présentent le long de leur étendue depuis l'arête d'attaque de fluide (4) jusqu'à l'arête de fuite de fluide (5) au moins une transition entre une répartition d'épaisseur d'aube radiale orientée en fonction de la rigidité et une répartition d'épaisseur d'aube radiale orientée en fonction de l'inertie et de la contrainte sur toute la hauteur de l'aube,
    la répartition d'épaisseur d'aube orientée en fonction de la rigidité étant une répartition d'épaisseur d'aube en forme de bouteille sur toute la hauteur de l'aube et la répartition d'épaisseur d'aube orientée en fonction de l'inertie et de la contrainte étant une répartition d'épaisseur d'aube en forme de tour Eiffel sur toute la hauteur de l'aube,
    un contour de surface latérale de l'aube de rotor respective (3) présentant dans la région de la répartition d'épaisseur d'aube en forme de bouteille entre son embase d'aube (B1) et son bord d'aube radial (B5) à chaque fois une région de changement de courbure (B3) dans laquelle une allure convexe du contour de surface latérale se prolonge radialement de l'intérieur vers l'extérieur en une allure concave par rapport à un axe médian imaginaire (13) de la section transversale d'aube de rotor considérée,
    un contour de surface latérale de l'aube de rotor respective (3) présentant dans la région de la répartition d'épaisseur d'aube en forme de tour Eiffel entre son embase d'aube (B1) et son bord d'aube radial (B5) une allure de courbure concave de telle sorte que l'épaisseur d'aube diminue sur la hauteur de l'aube (9) en devenant plus faible radialement vers l'extérieur.
  2. Rotor (1) selon la revendication 1, caractérisé en ce que le contour de surface latérale de l'aube de rotor respective (3) présente entre son embase d'aube (B1) et sa région de changement de courbure (B3) à chaque fois une première région de transition (B2) droite ou courbe.
  3. Rotor selon la revendication 2, caractérisé en ce que le contour de surface latérale de l'aube de rotor respective (3) présente entre son bord d'aube radial (B5) et sa région de changement de courbure (B3) à chaque fois une deuxième région de transition (B4) droite ou courbe.
  4. Rotor (1) selon la revendication 1, caractérisé en ce que l'allure de courbure concave du contour de surface latérale de l'aube de rotor respective (3), dans la région du bord d'aube radial (B5), se prolonge en une allure inclinée vers un axe médian imaginaire (13) de l'aube de rotor (3) ou parallèle à cet axe médian (13), de sorte qu'une région de transition (B4) soit produite, laquelle présente, en coupe transversale de l'aube de rotor, un rétrécissement trapézoïdal radialement vers l'extérieur ou une épaisseur constante.
  5. Rotor (1) selon l'une quelconque des revendications 1 à 4, caractérisé en ce que le rotor (1) est un rotor de turbine et en ce que les aubes de rotor (3) présentent, dans la région de leur arête d'attaque de fluide (4), à chaque fois une répartition d'épaisseur d'aube en forme de tour Eiffel sur toute la hauteur de l'aube et, dans la région de leur arête de fuite de fluide (5), à chaque fois une répartition d'épaisseur d'aube en forme de bouteille sur toute la hauteur de l'aube.
  6. Rotor (1) selon l'une quelconque des revendications 1 à 4, caractérisé en ce que le rotor (1) est un rotor de turbine et en ce que les aubes de rotor (3) présentent, dans la région de leur arête d'attaque de fluide (4) et dans la région de leur arête de fuite de fluide (5), à chaque fois une répartition d'épaisseur d'aube en forme de tour Eiffel sur toute la hauteur de l'aube et entre la région de leur arête d'attaque de fluide (4) et la région de leur arête de fuite de fluide (5), à chaque fois une région ayant une répartition d'épaisseur d'aube en forme de bouteille sur toute la hauteur de l'aube (9).
  7. Rotor (1) selon l'une quelconque des revendications 1 à 4, caractérisé en ce qu'il s'agit d'un rotor de compresseur et en ce que les aubes de rotor (3) présentent, dans la région de leur arête d'attaque de fluide (5'), à chaque fois une répartition d'épaisseur d'aube en forme de bouteille et, dans la région de leur arête de fuite de fluide (4'), à chaque fois une répartition d'épaisseur d'aube en forme de tour Eiffel.
  8. Rotor (1) selon l'une quelconque des revendications 1 à 4, caractérisé en ce qu'il s'agit d'un rotor de compresseur et en ce que les aubes de rotor (3) présentent, dans la région de leur arête d'attaque de fluide (5') et dans la région de leur arête de fuite de fluide (4), à chaque fois une répartition d'épaisseur d'aube en forme de tour Eiffel sur toute la hauteur de l'aube, et entre la région de leur arête d'attaque de fluide (5') et la région de leur arête de fuite de fluide (4'), à chaque fois une région ayant une répartition d'épaisseur d'aube en forme de bouteille.
  9. Rotor selon l'une quelconque des revendications 1 à 4, caractérisé en ce qu'un contour de surface latérale des aubes de rotor (3) présente, dans la région de la répartition d'épaisseur d'aube en forme de bouteille et dans la région de la répartition d'épaisseur d'aube en forme de tour Eiffel, dans la direction radiale vers l'extérieur, à chaque fois une pluralité de portions de contour s'étendant sous forme rectiligne.
  10. Rotor (1) selon l'une quelconque des revendications précédentes, caractérisé en ce que les aubes de rotor (3) présentent à chaque fois un côté d'aspiration (S) et un côté de pression (P) avec un contour de surface latéral respectif et des répartitions d'épaisseur d'aube identiques sur le côté d'aspiration (S) et sur le côté de pression (P), de sorte que les deux contours de surface latérale des aubes de rotor respectives s'étendent symétriquement l'un par rapport à l'autre par rapport à un axe médian imaginaire.
  11. Rotor selon l'une quelconque des revendications 1 à 9, caractérisé en ce que les aubes de rotor (3) présentent chacune un côté d'aspiration (S) et un côté de pression (P) avec un contour de surface latéral respectif et différentes répartitions d'épaisseur d'aube sur le côté d'aspiration (S) et le côté de pression (P), de sorte que les deux contours de surface latérale présentent des allures de contour différentes par rapport à un axe médian imaginaire.
EP13733304.3A 2012-07-24 2013-07-02 Rotor d'un turbocompresseur Active EP2877701B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102012212896.4A DE102012212896A1 (de) 2012-07-24 2012-07-24 Laufrad eines Abgasturboladers
PCT/EP2013/063958 WO2014016084A1 (fr) 2012-07-24 2013-07-02 Rotor de turbocompresseur sur gaz d'échappement

Publications (2)

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EP2877701A1 EP2877701A1 (fr) 2015-06-03
EP2877701B1 true EP2877701B1 (fr) 2017-05-10

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EP13733304.3A Active EP2877701B1 (fr) 2012-07-24 2013-07-02 Rotor d'un turbocompresseur

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US (1) US10253633B2 (fr)
EP (1) EP2877701B1 (fr)
CN (1) CN104471190B (fr)
BR (1) BR112015001398B8 (fr)
DE (1) DE102012212896A1 (fr)
IN (1) IN2014DN10346A (fr)
WO (1) WO2014016084A1 (fr)

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JP2016084751A (ja) * 2014-10-27 2016-05-19 三菱重工業株式会社 インペラ、遠心式流体機械、及び流体装置
JP6210459B2 (ja) * 2014-11-25 2017-10-11 三菱重工業株式会社 インペラ、及び回転機械
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Also Published As

Publication number Publication date
IN2014DN10346A (fr) 2015-08-07
EP2877701A1 (fr) 2015-06-03
CN104471190B (zh) 2017-07-04
US10253633B2 (en) 2019-04-09
CN104471190A (zh) 2015-03-25
DE102012212896A1 (de) 2014-02-20
BR112015001398B8 (pt) 2023-04-18
BR112015001398A2 (pt) 2017-07-04
WO2014016084A1 (fr) 2014-01-30
BR112015001398B1 (pt) 2021-09-28
US20150204195A1 (en) 2015-07-23

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