Exhaust gas turbocharger, in particular for a motor vehicle

• US 9,835,045 B2
• Filed: 12/01/2014
• Issued: 12/05/2017
• Est. Priority Date: 11/29/2013
• Status: Active Grant

• Current Assignee: BMTS Technology GmbH & Co. KG
• Original Assignee: Bosch Mahle Turbo Systems Gmbh & Co. Kg (MAHLE-STIFTUNG GmbH)
• Inventors: Laubender, Jochen, Schneider, Marcus
• Primary Examiner(s): Anderson, Gregory
• Assistant Examiner(s): Brockman, Eldon
• Application Number:
  US14/556,789
• Publication Number:
  US 20150159502A1
• Time in Patent Office: 1,100 Days
• CPC Class Codes: F01D 17/165 for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F05D 2220/40 in turbochargers

Abstract

An exhaust gas turbocharger may include a turbine housing and a turbine wheel. The turbine wheel may include a first quantity of a plurality of moving blades. The turbine wheel may be rotatable relative to the turbine housing about a turbine wheel center of rotation and have a turbine wheel radius. A variable turbine geometry may include a blade bearing ring on which a second quantity of a plurality of guide blades are rotatably mounted in each case about a guide blade center of rotation. The plurality of guide blades may be adjustable between a closed position, in which a flow cross section between the guide blades for an exhaust gas to flow through is at a minimum, and an opened position, in which the flow cross section is at a maximum.

Claims

1. An exhaust gas turbocharger, comprising:

a turbine housing;

a turbine wheel including a first quantity of a plurality of moving blades, the turbine wheel being rotatable relative to the turbine housing about a turbine wheel centre of rotation and having a turbine wheel radius (R_TR);

a variable turbine geometry including a blade bearing ring and a second quantity of a plurality of guide blades disposed on the blade bearing ring, the plurality of guide blades respectively rotatably mounted about a guide blade centre of rotation, wherein the plurality of guide blades are adjustable between a closed position where a flow cross section between the guide blades for an exhaust gas to flow through is at a minimum and an opened position where the flow cross section is at a maximum;

wherein each of the plurality of guide blades in a longitudinal profile includes a first profile nose facing away from the turbine wheel centre of rotation and a second profile nose facing towards the turbine wheel centre of rotation, and a straight connecting line between the first profile nose and the second profile nose defining a profile chord;

wherein a spacing (R_TE) of the second profile nose from the turbine wheel centre of rotation in the opened position of the guide blades and the turbine wheel radius (R_TR) satisfy the following relationship;

1.03≦

R_TE/R_TR≦

1.06; and

wherein an angle (χ

) formed as an apex point with respect to the turbine wheel centre of rotation between two adjacent guide blade centres of rotation and an opening angle (κ

) of at least one of the plurality of moving blades in a longitudinal section satisfy the following relationship;

0.4≦

χ

/η

≦

2.4.

2. The exhaust gas turbocharger according to claim 1, wherein the spacing (R_TE) and the turbine wheel radius (R_TR) satisfy the following relationship:

1.04≦

R_TE/R_TR≦

1.06.

3. The exhaust gas turbocharger according to claim 1, wherein:

the longitudinal profile of the respective guide blades includes a centre line, the centre line being divided by the guide blade centre of rotation into a first chord with a first chord length and a second chord with a second chord length and

wherein the first chord is defined by a first connecting straight line of the guide blade centre of rotation with the first profile nose and the second chord is defined by a second connecting straight line of the guide blade centre of rotation with the second profile nose.

4. The exhaust gas turbocharger according to claim 3, wherein the plurality of guide blades are configured such that the exhaust gas entering the turbine housing strikes the guide blade at an inflow angle <

4°

relative to the first chord when the guide blades are in the closed position.

5. The exhaust gas turbocharger according to claim 3, wherein an angle (ξ

₂) between (i) a third connecting straight line connecting the turbine wheel centre of rotation and the second profile nose and (ii) the first chord lies in the following angle interval;

35°

≦

ξ

₂≦

55°

, when the guide blades are in the opened position, and

95°

≦

ξ

₂≦

110°

, when the guide blades are in the closed position.

6. The exhaust gas turbocharger according to claim 3, wherein a first angle (ξ

₁) between (i) a third connecting straight line connecting the turbine wheel centre of rotation and the second profile nose and (ii) the second chord with respect to a second angle (ξ

₂) between (i) a fourth connecting straight line connecting the turbine wheel centre of rotation and the second profile nose and (ii) the first chord satisfies at least one of the following relationships;

1.4≦

ξ

₂/ξ

₁≦

1.6, and

1.2≦

ξ

₂/ξ

₁≦

1.4.

7. The exhaust gas turbocharger according to claim 1, wherein a ratio of a flow area (A_TR) between two moving blades with respect to an inlet area (A_LS) between two guide blades obeys the following relationship:

0.36≦

A_LS/A_TR≦

3.82.

8. The exhaust gas turbocharger according to claim 1, wherein a ratio of a height (h_TR) of one of the plurality of moving blades with respect to a height (h_LS) of one of the plurality of guide blades obeys the following relationship:

0.8≦

h_LS/h_TR≦

1.2.

9. The exhaust gas turbocharger according to claim 1, wherein a ratio of a diameter (D_TR) of at least one of the plurality of moving blades with respect to a height (h_TR) of the at least one of the plurality of moving blades obeys the following relationship:

0.1≦

h_TR/D_TR≦

0.2.

10. The exhaust gas turbocharger according to claim 1, wherein the angle (χ

) and the opening angle (κ

) further satisfy the following relationship;

0.6≦

χ

/κ

≦

1.7.

11. The exhaust gas turbocharger according to claim 1, wherein a length (S₂) of a second connecting line between two adjacent second profile noses in the opened state of the guide blades and an inlet width (S₃) between two adjacent moving blades obey the following relationship:

0.92≦

S₂/S₃≦

1.25.

12. The exhaust gas turbocharger according to claim 3, wherein the first chord length and the second chord length in the longitudinal profile of at least one of the plurality of guide blades has the following relationship:

0.5≦

L₁/L₂≦

1.0, wherein L₁ is the first chord length and L₂ is the second chord length.

13. An exhaust gas turbocharger for an internal combustion engine, comprising:

a turbine housing and a turbine wheel disposed therein rotatable relative to the turbine housing about a turbine wheel centre of rotation, the turbine wheel defining a turbine wheel radius (R_TR) and including a plurality of moving blades;

a variable turbine geometry including a blade bearing ring and a plurality of guide blades rotatably mounted about a guide blade centre of rotation on the blade bearing ring, the plurality of guide blades adjustable between a closed position where a flow cross-section between the respective guide blades for an exhaust gas flow is at a minimum, and an opened position where the flow cross-section is at a maximum;

the plurality of guide blades respectively having in a longitudinal profile a first profile nose facing away from the turbine wheel centre of rotation, a second profile nose facing towards the turbine wheel centre of rotation, and a profile chord defined by a first connecting line between the first profile nose and the second profile nose;

wherein a spacing (R_TE) of the second profile nose from the turbine wheel centre of rotation in the opened position of the plurality of guide blades and the turbine wheel radius (R_TR) satisfy the following relationship;

1.03≦

R_TE/R_TR≦

1.06; and

wherein a length (S₂) of a second connecting line between two adjacent second profile noses in the opened position of the guide blades and an inlet width (S₃) between two adjacent moving blades satisfy the following relationship;

0.45≦

S₂/S₃≦

3.2.

14. The exhaust gas turbocharger according to claim 13, wherein the length (S₂) and the inlet width (S₃) further satisfy the following relationship:

0.65≦

S₂/S₃≦

1.7.

15. An exhaust gas turbocharger for an internal combustion engine, comprising:

a turbine housing and a turbine wheel disposed therein rotatable relative to the turbine housing about a turbine wheel centre of rotation, the turbine wheel defining a turbine wheel radius (R_TR) and including a plurality of moving blades;

a variable turbine geometry including a blade bearing ring and a plurality of guide blades rotatably mounted about a guide blade centre of rotation on the blade bearing ring, the plurality of guide blades adjustable between a closed position where a flow cross-section between the respective guide blades for an exhaust gas flow is at a minimum, and an opened position where the flow cross-section is at a maximum;

the plurality of guide blades respectively having in a longitudinal profile a first profile nose facing away from the turbine wheel centre of rotation, a second profile nose facing towards the turbine wheel centre of rotation, and a profile chord defined by a connecting line between the first profile nose and the second profile nose;

wherein a spacing (R_TE) of the second profile nose from the turbine wheel centre of rotation in the opened position of the plurality of guide blades and the turbine wheel radius (R_TR) satisfy the following relationship;

1.03≦

R_TE/R_TR≦

1.06; and

wherein the first profile nose in the longitudinal profile of at least one guide blade of the plurality of guide blades defines an origin of a Cartesian coordinate system with an X-coordinate extending along the profile chord and a Y-coordinate extending orthogonally to the X-coordinate, the X-coordinate and the Y-coordinate of the following points being defined in the Cartesian coordinate system;

x_p, y_p;

Cartesian coordinates of the guide blade centre of rotation,

x₁, y₁;

a low point of a profile bottom side having a convex shape,

x₂, y₂;

a height of the profile bottom side having a concave shape,

x₃, y₃;

a height of a profile top side having a convex shape,

x₄, y₄;

a high point of a centre line of the longitudinal profile,

x₅, y₅;

an intersection of the profile bottom side having the convex shape with the profile chord,

x₆, y₆;

an intersection of the profile bottom side having the concave shape with the profile chord; and

wherein the at least one guide blade in the longitudinal profile includes the following relationship;

0≦

y_p/y₄≦

2;

0≦

y_p/y₁≦

5; and

0≦

y₂/y_p≦

0.7.

16. The exhaust gas turbocharger according to claim 15, wherein the at least one guide blade in the longitudinal profile further includes the following relationship:

0.3 L_{Profile chord}<

x_p<

0.5 L_{Profile chord};

wherein L_{Profile chord} is a length of the profile chord.

17. The exhaust gas turbocharger according to claim 15, wherein the at least one guide blade in the longitudinal profile further includes at least one of the following relationships:

0≦

y_p/y₃≦

1; and

0≦

y₃/y₁≦

5.

18. The exhaust gas turbocharger according to claim 15, wherein the at least one guide blade in the longitudinal profile further includes the following relationship:

0≦

|y₁|/x₁≦

1.5.

19. The exhaust gas turbocharger according to claim 15, wherein the at least one guide blade in the longitudinal profile further includes one of the following relationships:

0.8≦

(x_p−

x₁)/x_p; and

0.3≧

(x_p−

x₁)/x_p.

20. The exhaust gas turbocharger according to claim 15, wherein the at least one guide blade in the longitudinal profile further includes the following relationships:

0.7≦

(x_p−

x₃)/x_p≦

0.7;

b

1.5≦

(x_p−

x₅)/x_p≦

1.5;

0.7≦

(x_p−

x₄)/x_p≦

0.7;

1.7≦

(x_p−

x₂)/x_p≦

1.7;

1.5≦

(x₂−

x₅)/(x₆−

x₂)≦

1.5; and

1.5≦

(x₆−

x₂)/(x₂−

x₅)≦

1.5.