WO2014165355A1 - Turbine wheel of an exhaust-gas turbocharger - Google Patents

Turbine wheel of an exhaust-gas turbocharger Download PDF

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Publication number
WO2014165355A1
WO2014165355A1 PCT/US2014/031724 US2014031724W WO2014165355A1 WO 2014165355 A1 WO2014165355 A1 WO 2014165355A1 US 2014031724 W US2014031724 W US 2014031724W WO 2014165355 A1 WO2014165355 A1 WO 2014165355A1
Authority
WO
WIPO (PCT)
Prior art keywords
wheel
turbine
turbine wheel
region
connection region
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/US2014/031724
Other languages
French (fr)
Inventor
Frank Scherrer
Menno RODER
Gerald Schall
Juergen STRELBITSKI
Michael LOEWENBERG
Stefan Eisinger
Adnan ADILOVIC
Achim Klein
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.)
BorgWarner Inc
Original Assignee
BorgWarner Inc
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 BorgWarner Inc filed Critical BorgWarner Inc
Priority to JP2016506327A priority Critical patent/JP6409048B2/en
Priority to DE112014001067.7T priority patent/DE112014001067T5/en
Priority to CN201480017760.1A priority patent/CN105074161B/en
Priority to KR1020157030501A priority patent/KR20150138272A/en
Priority to US14/778,742 priority patent/US10001012B2/en
Publication of WO2014165355A1 publication Critical patent/WO2014165355A1/en
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
    • 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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B33/00—Engines characterised by provision of pumps for charging or scavenging
    • F02B33/32—Engines with pumps other than of reciprocating-piston type
    • F02B33/34—Engines with pumps other than of reciprocating-piston type with rotary pumps
    • F02B33/40—Engines with pumps other than of reciprocating-piston type with rotary pumps of non-positive-displacement type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/25—Manufacture essentially without removing material by forging
    • 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
    • F05D2240/24—Rotors for turbines
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/174—Titanium alloys, e.g. TiAl
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • the invention relates to a turbine wheel for the supercharging of a combustion engine, in particular of an internal combustion engine.
  • a turbine wheel of said type is known from DE 10 2005 050 707 Al .
  • an Ni-based material of the turbine wheel has an adverse effect on the acceleration of the rotor (assembly formed from the turbine wheel, the compressor wheel and the shaft) because turbine wheels composed of said material have a high mass moment of inertia.
  • said document describes the use of titanium-aluminum alloys which have a lower density, such that the mass moment of inertia of a turbine wheel composed of a material of said type can be reduced.
  • the wheel back outer diameter being greater than or equal to the connection region outer diameter of the turbine blades, a closed wheel back is formed, resulting in lower ventilation losses. In this way, the efficiency of the turbine composed of a titanium aluminide material can be increased.
  • the wheel back has, at least adjacent to the connection region, a wall thickness which is in a ratio of 1.5 : 1 to 2.5 : 1, in particular of 1.7 : 1 to 2.3 : 1, particularly preferably of 1.8 : 1 to 2.2 : 1 with respect to a wall thickness of the turbine blade.
  • the mass inertia of the turbine wheel is, owing to the low density of the titanium aluminide material, still low enough that an expedient acceleration characteristic of the exhaust-gas turbocharger can be achieved.
  • a wheel hub region extending in the axial direction merges in continuous fashion, in a chamfer region with radially outwardly increasing connection radii, into an intermediate region, extending in the radial direction, of the wheel back.
  • the turbine blades extend from the wheel back and from the hub of the turbine wheel with a turbine blade connection radius, the turbine blade connection radius being constant over an entire length of extent of the turbine blade.
  • a heat transfer rate from the wheel back and the hub to the turbine blade is achieved which is substantially constant over the length of extent of the turbine blade.
  • the wheel back and the hub can release the heat stored therein to the turbine blade in uniform fashion, such that non-uniform temperature distributions along the length of extent, and thus internal stresses along the line of extent, are reduced to a level tolerable for titanium aluminide materials.
  • a ratio of the wall thickness of the turbine blades to the connection region outer diameter lies in the range of up to 0.7 : 40; particularly preferably between 0.3 : 40 and 0.5 : 40; in particular between 0.35 : 40 and 0.45 : 40.
  • FIG. 1 shows a schematically greatly simplified diagrammatic illustration of an exhaust-gas turbocharger according to the invention
  • Figure 2 shows a side view of a first embodiment of a turbine wheel according to the invention
  • Figure 3 is a sectional illustration through a second embodiment of the turbine wheel according to the invention, wherein only the upper half of the turbine wheel is illustrated in the illustration selected in figure 3, and
  • Figure 4 is a sectional illustration of the embodiment of the turbine wheel according to the invention illustrated in Figure 1.
  • FIG. 1 is a schematically highly simplified illustration of an exhaust-gas turbocharger 2 according to the invention for the supercharging of an internal combustion engine (not illustrated), said exhaust-gas turbocharger having a turbine wheel 1 which is arranged in a turbine housing 12.
  • the turbine wheel 1 is fastened to one end of a shaft 14, on the other end of which there is mounted a compressor wheel 15 which is arranged in a compressor housing 16.
  • the turbine wheel 1, the shaft 14 and the compressor wheel 15 form an assembly which is also referred to as rotor.
  • the shaft 14 is mounted in a bearing housing 13 which is arranged between the compressor housing 16 and the turbine housing 12.
  • Figure 2 illustrates a first embodiment of the turbine wheel 1 according to the invention composed of a titanium aluminide (TiAl) material.
  • the turbine wheel 1 may be cast from a titanium aluminide alloy in a casting process.
  • the turbine wheel 1 may also be milled from a forged titanium aluminide blank.
  • the turbine wheel 1 has a circular outer contour 17 and a hub 3 on which there is arranged a multiplicity of turbine blades, one of which is denoted, as a representative of all of the turbine blades, by the reference sign 4.
  • the turbine blades 4 extend along a length of extent L.
  • Each of the turbine blades 4 has a connection region 5 in which an imaginary circle drawn around the turbine blades 4 at the radially outer tips thereof has an outer diameter DAB.
  • the connection region 5 is adjoined by an outlet region 6 of the turbine blades 4, which in the case of the embodiment of figure 2 has a smaller outer diameter than the connection region 5.
  • the turbine wheel 1 also has a wheel back 7 which adjoins the connection region 5 and which is formed on the hub 3, as can be seen from Figure 2.
  • the wheel back 7 has, in an outer region 11 , an outer diameter DR which at least substantially corresponds to the diameter DAB but preferably has the same value as the diameter DAB.
  • the wheel back 7 has a wall thickness WRR.
  • the turbine wheel blades have a wall thickness WTS, wherein Figure 2 shows, by way of example, two regions of the turbine blades 4 in which the stated wall thickness region WTS is indicated.
  • the wheel back 7 is thickened slightly and has, at least adjacent to the connection region 5, a wall thickness WRR which is in a ratio of 1.5 : 1 to 2.5 : 1, in particular of 1.7 : 1 to 2.3 : 1 , particularly preferably of 1.8 : 1 to 2.2 : 1 with respect to a wall thickness WTS of the turbine blade 4.
  • the cooling of the turbine wheel 1 in a period of overrun operation following a period of normal or elevated engine load of the internal combustion engine is slowed.
  • the slowed cooling has proven to be advantageous, in the case of turbine wheels composed of titanium aluminide, for a long service life. The reason for this may be seen in the fact that high internal stresses in the turbine wheel 1 that may arise as a result of non-homogeneous cooling when a temperature at which the ductility of the titanium aluminide material decreases is reached can be eliminated, or at least reduced to a tolerable level.
  • FIG 3 illustrates a second embodiment of the turbine wheel 1 according to the invention, in which all elements that correspond to those in Figure 2 are denoted by the same reference signs, such that, in this regard, reference may be made to the above description of Figure 2.
  • the turbine wheel 1 of the embodiment as per Figure 3 is a so-called "mixed- flow turbine wheel", the connection region 5 of which has, as in the case of the embodiment of Figure 2, an outer diameter DAB which corresponds to the outer diameter DRR of the wheel back 7.
  • the outlet region 6 is, as shown in Figure 3, extended upward in a radial direction R, giving rise to the special geometry of the mixed-flow turbine wheel which can be driven by an exhaust-gas stream impinging on the turbine wheel 1 obliquely with respect to the axial direction A.
  • Figures 3 and 4 show, in section, the design of the wheel back 7, in which a wheel hub region 8 extending in the axial direction A merges, in a rounded chamfer region 9 with a connection radius A(R), into an intermediate region 10, which extends in the radial direction R, of the wheel back 7.
  • a connection radius AR(R) increases continuously with increasing distance outward from the axis of rotation A.
  • Figure 4 shows the embodiment of the turbine wheel 1 according to the invention shown in Figure 1, in a sectional illustration, corresponding to Figure 3, of only the upper region, that is to say the region above the longitudinal axis A.
  • This embodiment concerns a radial wheel which has, adjoining the connection region 5, an outlet region 6 which has the same outer diameter as the connection region 5.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to a turbine wheel (1) of an exhaust-gas turbocharger (2), formed from a titanium aluminide material, having a wheel back (7) which is of closed configuration as viewed from an axial direction (A) and which has an outer contour (17), and having a hub (3) which extends from the wheel back (7) and which tapers along the axial direction (A), having a multiplicity of turbine blades (4) which extend from the wheel back (7) and from the hub (3) and which extend outward in a radial direction (R), as far as a connection region outer diameter (DAB) at least in a connection region (5), the wheel back (7) having, in an outer region (11) adjoining the connection region (5), a wheel back outer diameter (DRR) which is greater than or equal to the connection region outer diameter (DAB).

Description

TURBINE WHEEL OF AN EXHAUST-GAS TURBOCHARGER
DESCRIPTION The invention relates to a turbine wheel for the supercharging of a combustion engine, in particular of an internal combustion engine.
A turbine wheel of said type is known from DE 10 2005 050 707 Al . In said document, it is described that an Ni-based material of the turbine wheel has an adverse effect on the acceleration of the rotor (assembly formed from the turbine wheel, the compressor wheel and the shaft) because turbine wheels composed of said material have a high mass moment of inertia.
As a measure for reducing the mass moment of inertia, said document describes the use of titanium-aluminum alloys which have a lower density, such that the mass moment of inertia of a turbine wheel composed of a material of said type can be reduced.
It is an object of the present invention to provide a turbine wheel composed of titanium aluminide (TiAl) which is of simple dimensioning and thus construction, wherein a high level of efficiency of the turbine can be achieved.
This object is achieved by the features of claim 1. The dependent claims relate to preferred refinements of the invention. These may be combined with one another in a technologically expedient manner, whereby to some extent effects may be realized which go beyond the sum total of the individual effects.
By virtue of the wheel back outer diameter being greater than or equal to the connection region outer diameter of the turbine blades, a closed wheel back is formed, resulting in lower ventilation losses. In this way, the efficiency of the turbine composed of a titanium aluminide material can be increased.
In one refinement, the wheel back has, at least adjacent to the connection region, a wall thickness which is in a ratio of 1.5 : 1 to 2.5 : 1, in particular of 1.7 : 1 to 2.3 : 1, particularly preferably of 1.8 : 1 to 2.2 : 1 with respect to a wall thickness of the turbine blade.
When the internal combustion engine is in overrun operation, the internal combustion engine remains in rotation owing to its mass inertia. During this time, no fuel is injected, and as a result cold exhaust gas or air flows to the turbocharger, such that the turbine wheel cools down relatively quickly. The cooling of the turbine wheel results in internal stresses in the turbine wheel. In the case of turbine wheels composed of Ni-based materials from the prior art, said internal stresses are non-critical. The ductility, that is to say the ability of the titanium aluminide material to be deformed without damage, however decreases with falling temperature in the relevant temperature range. Furthermore, owing to a coefficient of expansion of titanium aluminide materials being non-constant with respect to temperature, more intensely cooled regions cause high internal stresses. In the case of turbine wheels composed of titanium aluminide materials, a combination of the non-constant coefficient of expansion and the decreasing ductility can result in the formation of cracks in the turbine wheel. It has surprisingly been found that, if the ratio of the wall thickness of the turbine blades with respect to the wall thickness of the wheel back is the ratio mentioned in the preceding paragraph, it is ensured that adequate material is provided, which yields slower and thus more homogeneous cooling in overrun operation.
With the stated ratio, the mass inertia of the turbine wheel is, owing to the low density of the titanium aluminide material, still low enough that an expedient acceleration characteristic of the exhaust-gas turbocharger can be achieved.
In one refinement, a wheel hub region extending in the axial direction merges in continuous fashion, in a chamfer region with radially outwardly increasing connection radii, into an intermediate region, extending in the radial direction, of the wheel back.
The configuration of the wheel back as described in the preceding paragraph yields a turbine wheel of high strength.
In a further refinement, the turbine blades extend from the wheel back and from the hub of the turbine wheel with a turbine blade connection radius, the turbine blade connection radius being constant over an entire length of extent of the turbine blade.
Owing to this refinement, a heat transfer rate from the wheel back and the hub to the turbine blade is achieved which is substantially constant over the length of extent of the turbine blade. In this way, during the cooling process, the wheel back and the hub can release the heat stored therein to the turbine blade in uniform fashion, such that non-uniform temperature distributions along the length of extent, and thus internal stresses along the line of extent, are reduced to a level tolerable for titanium aluminide materials. In a further refinement, a ratio of the wall thickness of the turbine blades to the connection region outer diameter lies in the range of up to 0.7 : 40; particularly preferably between 0.3 : 40 and 0.5 : 40; in particular between 0.35 : 40 and 0.45 : 40.
It has been found that, with the stated ratio, an adequately stable turbine blade can be formed.
Further details, features and advantages of the invention become apparent from the following description of exemplary embodiments with reference to the drawing, in which:
Figure 1 shows a schematically greatly simplified diagrammatic illustration of an exhaust-gas turbocharger according to the invention,
Figure 2 shows a side view of a first embodiment of a turbine wheel according to the invention,
Figure 3 is a sectional illustration through a second embodiment of the turbine wheel according to the invention, wherein only the upper half of the turbine wheel is illustrated in the illustration selected in figure 3, and
Figure 4 is a sectional illustration of the embodiment of the turbine wheel according to the invention illustrated in Figure 1.
Figure 1 is a schematically highly simplified illustration of an exhaust-gas turbocharger 2 according to the invention for the supercharging of an internal combustion engine (not illustrated), said exhaust-gas turbocharger having a turbine wheel 1 which is arranged in a turbine housing 12. The turbine wheel 1 is fastened to one end of a shaft 14, on the other end of which there is mounted a compressor wheel 15 which is arranged in a compressor housing 16. The turbine wheel 1, the shaft 14 and the compressor wheel 15 form an assembly which is also referred to as rotor. The shaft 14 is mounted in a bearing housing 13 which is arranged between the compressor housing 16 and the turbine housing 12.
Figure 2 illustrates a first embodiment of the turbine wheel 1 according to the invention composed of a titanium aluminide (TiAl) material. The turbine wheel 1 may be cast from a titanium aluminide alloy in a casting process. The turbine wheel 1 may also be milled from a forged titanium aluminide blank.
The turbine wheel 1 has a circular outer contour 17 and a hub 3 on which there is arranged a multiplicity of turbine blades, one of which is denoted, as a representative of all of the turbine blades, by the reference sign 4. The turbine blades 4 extend along a length of extent L. Each of the turbine blades 4 has a connection region 5 in which an imaginary circle drawn around the turbine blades 4 at the radially outer tips thereof has an outer diameter DAB. The connection region 5 is adjoined by an outlet region 6 of the turbine blades 4, which in the case of the embodiment of figure 2 has a smaller outer diameter than the connection region 5.
The turbine wheel 1 also has a wheel back 7 which adjoins the connection region 5 and which is formed on the hub 3, as can be seen from Figure 2.
The wheel back 7 has, in an outer region 11 , an outer diameter DR which at least substantially corresponds to the diameter DAB but preferably has the same value as the diameter DAB.
Furthermore, the wheel back 7 has a wall thickness WRR. The turbine wheel blades have a wall thickness WTS, wherein Figure 2 shows, by way of example, two regions of the turbine blades 4 in which the stated wall thickness region WTS is indicated. The wheel back 7 is thickened slightly and has, at least adjacent to the connection region 5, a wall thickness WRR which is in a ratio of 1.5 : 1 to 2.5 : 1, in particular of 1.7 : 1 to 2.3 : 1 , particularly preferably of 1.8 : 1 to 2.2 : 1 with respect to a wall thickness WTS of the turbine blade 4. Owing to the slight thickening, it is ensured that the cooling of the turbine wheel 1 in a period of overrun operation following a period of normal or elevated engine load of the internal combustion engine is slowed. The slowed cooling has proven to be advantageous, in the case of turbine wheels composed of titanium aluminide, for a long service life. The reason for this may be seen in the fact that high internal stresses in the turbine wheel 1 that may arise as a result of non-homogeneous cooling when a temperature at which the ductility of the titanium aluminide material decreases is reached can be eliminated, or at least reduced to a tolerable level.
Figure 3 illustrates a second embodiment of the turbine wheel 1 according to the invention, in which all elements that correspond to those in Figure 2 are denoted by the same reference signs, such that, in this regard, reference may be made to the above description of Figure 2.
The turbine wheel 1 of the embodiment as per Figure 3 is a so-called "mixed- flow turbine wheel", the connection region 5 of which has, as in the case of the embodiment of Figure 2, an outer diameter DAB which corresponds to the outer diameter DRR of the wheel back 7. The outlet region 6 is, as shown in Figure 3, extended upward in a radial direction R, giving rise to the special geometry of the mixed-flow turbine wheel which can be driven by an exhaust-gas stream impinging on the turbine wheel 1 obliquely with respect to the axial direction A.
Furthermore, Figures 3 and 4 show, in section, the design of the wheel back 7, in which a wheel hub region 8 extending in the axial direction A merges, in a rounded chamfer region 9 with a connection radius A(R), into an intermediate region 10, which extends in the radial direction R, of the wheel back 7. Here, a connection radius AR(R) increases continuously with increasing distance outward from the axis of rotation A. This yields a rigid and thus dimensionally stable turbine wheel 1 which stores heat, and releases said heat to the outer region 11 of the wheel back 7, over a relatively long period of time. In this way, both the wheel back 7 in the outer region 11 and also regions of the turbine blades 4 adjoining said outer region cool down correspondingly more slowly in overrun operation.
Figure 4 shows the embodiment of the turbine wheel 1 according to the invention shown in Figure 1, in a sectional illustration, corresponding to Figure 3, of only the upper region, that is to say the region above the longitudinal axis A. This embodiment concerns a radial wheel which has, adjoining the connection region 5, an outlet region 6 which has the same outer diameter as the connection region 5.
In addition to the above written disclosure, reference is hereby explicitly made, for supplementation thereof, to the diagrammatic illustration of the invention in Figures 1 to 4.
List of reference signs
1 Turbine wheel
2 Exhaust-gas turbocharger
3 Hub
4 Turbine blades
5 Connection region
6 Outlet region
7 Wheel back
8 Wheel hub region
9 Chamfer region
10 Intermediate region
1 1 Outer region
12 Turbine housing
13 Bearing housing
14 Shaft
15 Compressor wheel
16 Compressor housing
17 Outer contour
DAB Connection region outer diameter
DRR Wheel back outer diameter
A Axial direction/longitudinal axis
AR(R) Connection radii
TA Turbine blade connection radius
R Radial direction
WRR Wall thickness of the wheel back
WTS Turbine blade wall thickness

Claims

1. A turbine wheel (1) of an exhaust-gas turbocharger (2), formed from a titanium aluminide material,
· having a wheel back (7) which is of closed configuration as viewed from an axial direction (A) and which has an outer contour (17), and
• having a hub (3) which extends from the wheel back (7) and which tapers along the axial direction (A),
• having a multiplicity of turbine blades (4) which extend from the wheel back (7) and from the hub (3) and which extend outward in a radial direction (R), as far as a connection region outer diameter (DAB) at least in a connection region (5),
• the wheel back (7) having, in an outer region (11) adjoining the connection region (5), a wheel back outer diameter (DRR) which is greater than or equal to the connection region outer diameter (DAB).
2. The turbine wheel as claimed in claim 1, wherein the wheel back (7) has, at least adjacent to the connection region (5), a wall thickness (WRR) which is in a ratio of 1.5 : 1 to 2.5 : 1, in particular of 1.7 : 1 to 2.3 : 1, particularly preferably of 1.8 : 1 to 2.2 : 1 with respect to a wall thickness (WTS) of the turbine blade (4).
3. The turbine wheel as claimed in either of claims 1 and 2, wherein a wheel hub region (8) extending in the axial direction (A) merges in continuous fashion, in a chamfer region (9) with radially outwardly increasing connection radii (AR(R)), into an intermediate region (10), extending in the radial direction (R), of the wheel back (7).
4. The turbine wheel as claimed in one of claims 1 to 3, wherein the turbine blades (4) extend from the wheel back (7) and from the hub (3) of the turbine wheel with a turbine blade connection radius (TA), the turbine blade connection radius (TA) being substantially constant over an entire length of extent (L) of the turbine blade (4).
5. The turbine wheel as claimed in one of claims 1 to 4, wherein a ratio of the wall thickness (WTS) of the turbine blades (4) to the connection region outer diameter (DAB) lies in the range of up to 0.7 : 40; particularly preferably between 0.3 : 40 and 0.5 : 40; in particular between 0.35 : 40 and 0.45 : 40.
6. The turbine wheel as claimed in one of claims 1 to 5, wherein it is formed as a forged and milled turbine wheel.
7. The turbine wheel as claimed in one of claims 1 to 5, wherein it is formed as a cast turbine wheel.
8. The turbine wheel as claimed in one of claims 1 to 5, wherein it can be driven by an exhaust-gas stream flowing inward in the radial direction (R).
9. The turbine wheel as claimed in one of claims 1 to 5, wherein it can be driven by an exhaust-gas stream flowing obliquely both in the radial direction (R) and also in the axial direction (A).
10. An exhaust-gas turbocharger (2) for the supercharging of an internal combustion engine, having a turbine wheel (1) as claimed in one of claims 1 to 9.
PCT/US2014/031724 2013-04-05 2014-03-25 Turbine wheel of an exhaust-gas turbocharger Ceased WO2014165355A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
JP2016506327A JP6409048B2 (en) 2013-04-05 2014-03-25 Turbine wheel of exhaust gas turbocharger
DE112014001067.7T DE112014001067T5 (en) 2013-04-05 2014-03-25 Turbine wheel of an exhaust gas turbocharger
CN201480017760.1A CN105074161B (en) 2013-04-05 2014-03-25 Turbine wheel for exhaust turbocharger
KR1020157030501A KR20150138272A (en) 2013-04-05 2014-03-25 Turbine wheel of an exhaust-gas turbocharger
US14/778,742 US10001012B2 (en) 2013-04-05 2014-03-25 Turbine wheel of an exhaust-gas turbocharger

Applications Claiming Priority (2)

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JP6409048B2 (en) 2018-10-17
US10001012B2 (en) 2018-06-19
US20160053616A1 (en) 2016-02-25
CN105074161A (en) 2015-11-18
JP2016514798A (en) 2016-05-23
KR20150138272A (en) 2015-12-09
CN105074161B (en) 2018-10-02
DE112014001067T5 (en) 2015-11-12

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