Turbocharger engine

Patent metadata

Field	Value
Publication number	US-10760477-B2
Application number	US-201715609766-A
Country	US
Kind code	B2
Filing date	May 31, 2017
Priority date	May 31, 2016
Publication date	Sep 1, 2020
Grant date	Sep 1, 2020

Abstract

A turbocharger engine includes a dual stage turbocharger in which a first turbo unit is disposed on the upstream side of a second turbo unit on an exhaust passage. The turbocharger is disposed in such a manner that a second turbine shaft of the second turbo unit is far from an engine output shaft than a first turbine shaft of the first turbo unit in a plan view in an axis direction of a cylinder. Further, a second turbine is rotated clockwise around an axis thereof in a side view when the turbocharger is viewed from the side of the turbine, and an intra-turbine passage is disposed on the side of an engine body than the second turbine shaft.

First claim

The invention claimed is:

1. An engine, comprising:
an engine body including a cylinder and an engine output shaft; and
a turbocharger disposed adjacent to the engine body, and including an exhaust passage through which exhaust air is supplied from the engine body, and an intake passage through which intake air is supplied to the engine body to supercharge the intake air, wherein
the turbocharger includes
a first turbo unit provided with:
a first turbine chamber communicating with the exhaust passage and configured to accommodate a first turbine,
a first compressor chamber communicating with the intake passage and configured to accommodate a first compressor, and
a first turbine shaft extending between the first turbine chamber and the first compressor chamber to connect between the first turbine and the first compressor, and

a second turbo unit provided with:
a second turbine chamber communicating with the exhaust passage and configured to accommodate a second turbine,
a second compressor chamber communicating with the intake passage and configured to accommodate a second compressor, and
a second turbine shaft extending between the second turbine chamber and the second compressor chamber to connect between the second turbine and the second compressor,

the first turbine chamber is disposed on an upstream side of the second turbine chamber in the exhaust passage,
the first turbine shaft and the second turbine shaft are disposed to extend generally in a same direction as the engine output shaft,
the second turbo unit is disposed with respect to the engine body in such a manner that the second turbine shaft is farther from the engine output shaft than the first turbine shaft in a plan view of the cylinder and the engine body,
in a plan view of the cylinder and the engine body, the first turbine shaft and the second turbine shaft are disposed non-parallel to each other in such a manner that a first distance between the first turbine shaft and the second turbine shaft at a first end on a turbine side is larger than a second distance between the first turbine shaft and the second turbine shaft at a second end on a compressor side, and in such a manner that a first extension line defined by extending an axis of the first turbine shaft toward a side of the first compressor chamber and a second extension line defined by extending an axis of the second turbine shaft toward a side of the second compressor chamber intersect with each other, and
in a side view when the first turbine shaft and the second turbine shaft are viewed from a side of the first turbine chamber and the second turbine chamber,
the engine body is located on a left side of the second turbo unit,
the second turbine shaft is rotated clockwise around an axis thereof, and
an intra-turbine passage from an exit of the first turbine chamber to an entrance of the second turbine chamber is disposed between a side of the engine body and the second turbine shaft.

2. The engine according to claim 1 , wherein
A is a distance between an axis of the first turbine shaft and an axis of the second turbine shaft in a direction transverse to the direction of the engine output shaft, and B is an outer diameter of an impeller of the second turbine in the side view, the distance A is set in a range defined by the following formula:
B/ 2≤ A≤B.

3. The engine according to claim 2 , wherein
the outer diameter of the impeller of the second turbine is larger than an outer diameter of an impeller of the first turbine.

4. The engine according to claim 2 , further comprising:
a bypass passage disposed on a right side of the intra-turbine passage in the side view, and configured to bypass the first turbine chamber so as to guide exhaust air to be supplied from the engine body to the second turbine chamber.

5. The engine according to claim 4 , wherein
a downstream end of the bypass passage joins the intra-turbine passage.

6. The engine according to claim 1 , wherein
the second turbine chamber includes a scroll passage formed in a periphery of the second turbine, and
A is a distance between an axis of the first turbine shaft and an axis of the second turbine shaft in a direction transverse to the direction of the engine output shaft, B is an outer diameter of an impeller of the second turbine, and C is a diameter of an inlet portion of the scroll passage in the side view, the distance A is set in a range defined by the following formula:
B/ 2≤ A≤B/ 2+ C.

7. The engine according to claim 6 , wherein
the outer diameter of the impeller of the second turbine is larger than an outer diameter of an impeller of the first turbine.

8. The engine according to claim 6 , further comprising:
a bypass passage disposed on a right side of the intra-turbine passage in the side view, and configured to bypass the first turbine chamber so as to guide exhaust air to be supplied from the engine body to the second turbine chamber.

9. The engine according to claim 1 , wherein
the second turbine is a turbine whose impeller has an outer diameter larger than an outer diameter of an impeller of the first turbine.

10. The engine according to claim 9 , further comprising:
a bypass passage disposed on a right side of the intra-turbine passage in the side view, and configured to bypass the first turbine chamber so as to guide exhaust air to be supplied from the engine body to the second turbine chamber.

11. The engine according to claim 1 , further comprising:
a bypass passage disposed on a right side of the intra-turbine passage in the side view, and configured to bypass the first turbine chamber so as to guide exhaust air to be supplied from the engine body to the second turbine chamber.

12. The engine according to claim 11 , wherein
a downstream end of the bypass passage joins the intra-turbine passage.

Assignees

• Mazda Motor

Inventors

• Niwa Yasushi
• Uehane Yoshiyuki
• Araki Keiji

Classifications

• F04D17/14

  with means for changing the flow-path through the stages, e.g. series-parallel, e.g. side-loads, (surge control F04D27/02) · CPC title

• F02B37/013

  with exhaust-driven pumps arranged in series · CPC title

• F02B37/004 Primary

  with exhaust drives arranged in series · CPC title

• F04D29/4206

  especially adapted for elastic fluid pumps · CPC title

• F04D17/127

  with radially spaced stages, e.g. for contrarotating type · CPC title