Variable capacity turbine

• US 4,880,351 A
• Filed: 05/27/1987
• Issued: 11/14/1989
• Est. Priority Date: 05/30/1986
• Status: Expired due to Fees

• Current Assignee: Honda Giken Kogyo Kabushiki Kaisha (Honda Motor Company)
• Original Assignee: Honda Giken Kogyo Kabushiki Kaisha (Honda Motor Company)
• Inventors: Kubota, Osamu, Endo, Tsuneo, Tateishi, Fusao, Inoue, Kazuo, Yamaguchi, Koji, Yano, Shunji, Noda, Etsuo
• Primary Examiner(s): Garrett, Robert E.
• Assistant Examiner(s): KWON, JOHN
• Application Number:
  US07/054,499
• Time in Patent Office: 902 Days
• Field of Search: 415/148, 415/151, 415/159, 415/162, 415/163, 415/164, 415/167, 415/202
• US Class Current: 415/164
• 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

Abstract

Disclosed is a turbine comprising a turbine wheel, a turbine scroll passage defined in a turbine casing around the turbine wheel for introduction of gas to the turbine wheel, and an axial central passage defined in the turbine casing for ejection of gas from the turbine wheel, wherein: a plurality of variable nozzles are arranged outside of a throat section having a locally minimum cross section which is defined in the turbine casing around the turbine wheel. The variable nozzles may be defined by fixed vanes and moveable vanes which cooperate with each other in such a manner that each of the moveable vanes and the corresponding fixed vane define a substantially smooth and continuous airfoil. The moveable vanes may be pivotally supported by a back plate of the casing while the fixed vanes may be integrally provided with a fixed vane member having a disk portion which defines a surface opposing the inner surface of the back plate. The moveable vanes may rotate along and between these mutually opposing surfaces for varying the cross section of the nozzles defined between the fixed vanes and the moveable vanes.

Claims

1. A radial in-flow turbine comprising a turbine wheel, a turbine scroll passage defined in a turbine casing around the turbine wheel for introduction of gas to the turbine wheel, and an axial central passage defined in the turbine casing for ejection of gas from the turbine wheel. wherein:

a plurality of variable nozzles, having an axial width, are arranged concentrically with respect to the turbine wheel and inside of the turbine casing and outside of an annular throat section defined inside the turbine casing concentric to the turbine wheel and having a locally minimum axial width less than said nozzle axial width, said variable nozzles are defined by fixed vanes and moveable vanes.

2. A variable capacity turbine as defined in claim 1, wherein the fixed vanes are comprised of arcuate vanes arranged along a circle which is concentric to the turbine wheel and the moveable vanes are adapted to rotate along a plane which is perpendicular to the axial line of the turbine.

3. A variable capacity turbine as defined in claim 2, wherein the moveable vanes are each provided with a center of rotation at its base end which is adjacent to one of the fixed vanes and are adapted to rotate between a most closed position which is substantially aligned with the circle and a most open position which is inclined inwardly with respect to the circle.

4. A variable capacity turbine as defined in claim 3,

wherein each of the fixed vanes and the corresponding moveable vane define a substantially continuous and smooth airfoil.

5. A variable capacity turbine as defined in claim 4, further comprising:

a fixed vane member having a disk portion which defines a surface opposing an inner surface of a back plate which covers an axial end of the turbine casing remote from an axial end of the central axial passage and the fixed vanes arranged at an equal interval along a peripheral portion of the disk portion radially outside of the outer periphery of the turbine wheel and extend axially towards the back plate;

moveable vane members having the moveable vanes and pivot means for supporting the moveable vanes in a rotatable manner along and between the opposing surfaces of the disk portion and the back plate;

fastener means for connecting an axial free ends of the fixed vanes to the back plate.

6. A variable capacity turbine as defined in claim 5, wherein the moveable vanes are pivotally supported by the back plate.

7. A variable capacity turbine as defined in claim 6, wherein the gap defined by the back plate and the disk portion for receiving one of the moveable vane is flared from an outer circumferential portion thereof to an inner circumferential portion thereof.

8. A variable capacity turbine as defined in claim 7, wherein the disk portion of the fixed vane member is provided with a central tubular portion which is adapted to be connected to an internal end of the axial passage in a substantially air tight and floating manner.

9. A variable capacity turbine as defined in claim 8, wherein the minimum opening angle of the moveable vanes is determined by the side edges of the moveable vanes contacting complementary shoulders formed in at least one of the back plate and the disk portion of the fixed vane member.

10. A variable capacity turbine as defined in claim 9, wherein an overlap along the circumferential direction is provided between the leading edge of each of the fixed vanes and the trailing edge of the corresponding moveable vane, the ratio of this overlap to the axial width of the moveable vane being from 20 to 60%.

11. A variable capacity turbine as defined in claim 10, wherein the ratio of the overlap to the axial width of the moveable vane is from 20 to 30%.

12. A variable capacity turbine as defined in claim 1, wherein the opening areas of the variable nozzles are each defined by a fixed axial width and a variable width extending in a direction perpendicular to the axial direction.

13. A turbine comprising a turbine wheel, a turbine scroll passage defined in a turbine casing around the turbine wheel for introduction of gas to the turbine wheel, and an axial central passage defined in the turbine casing for ejection of gas from the turbine wheel, comprising:

a plurality of fixed vanes and movable vanes arranged around the turbine wheel in alternating fashion located inside said turbine casing and outside of an annular throat section;

each of the movable vanes being pivoted at its base end adjacent to a trailing edge of an adjacent one of the fixed vanes rotatable between a first position, in which the fixed vanes and movable vanes are substantially aligned with a circle and a free end of the movable vane adjoins a leading edge of the adjacent fixed vane along a circumferential direction so as to define a minimally open nozzle therebetween, and a second position, in which said movable vanes are rotated inwardly toward the turbine wheel so as to define a maximally open nozzle between the free end of each of the movable vanes and the leading edge of the corresponding adjacent fixed vane.

14. A variable capacity turbine as defined in claim 13, further comprising:

a fixed vane member having a disk portion which defines a surface opposing an inner surface of a back plate which covers an axial end of the turbine casing remote from an inlet end of the central axial passage and the fixed vanes arranged at an equal interval along a peripheral portion of the disk portion radially outside of the outer periphery of the turbine wheel and extend axially towards the back plate;

moveable vane members having the moveable vanes and pivot means for supporting the moveable vanes with respect to the back plate in a rotatable manner along and between the opposing surfaces of the disk portion and the back plate in such a manner that each of the moveable vanes and the corresponding fixed vane define a substantially smooth and continuous airfoil; and

fastener means for connecting an axial free ends of the fixed vanes to the back plate.

15. A variable capacity turbine as defined in claim 13, wherein the free end of each of the movable vanes overlaps the leading edge of the adjacent fixed vane along a circumferential direction when the movable vanes are rotated outwardly away from the turbine wheel so as to define a minimally open nozzle between the moveable vane and the fixed vane.

16. A radial in-flow turbine comprising a turbine wheel, a turbine scroll passage defined in a turbine casing around the turbine wheel for introduction of gas to the turbine wheel, and an axial central passage defined in the turbine casing for ejection of gas from the turbine wheel, wherein:

a plurality of variable nozzles located inside said turbine casing and outside of an annular throat section, said nozzles comprised of a plurality of moveable vanes and fixed vanes arranged around the turbine wheel;

the moveable vanes and fixed vanes being substantially aligned along a circle concentric to the turbine wheel and presenting substantially smooth inner and outer circumferential contour surfaces when the moveable vanes are positioned to define a minimally open state of the variable nozzles.

17. A radial in-flow turbine comprising a turbine wheel, a turbine scroll passage defined in a turbine casing around the turbine wheel for introduction of gas to the turbine wheel, and an axial central passage defined in the turbine casing for ejection of gas from the turbine wheel, wherein:

a plurality of variable nozzles located inside said turbine casing and outside of an annular throat section, said nozzles comprised of a plurality of moveable vanes and fixed vanes having ends, said moveable vanes and fixed vanes arranged around the turbine wheel, and each of the moveable vanes and the corresponding fixed vanes define an airfoil having a substantially smooth contour, the end of each of the fixed vanes remote from the corresponding moveable vane defining the leading edge of the airfoil while the end of the moveable vane remote from the corresponding fixed vane defines the trailing edge of the airfoil.