Rotary Valve

Patent metadata

Field	Value
Publication number	US-2022010883-A1
Application number	US-201917293170-A
Country	US
Kind code	A1
Filing date	Nov 11, 2019
Priority date	Nov 13, 2018
Publication date	Jan 13, 2022
Grant date	—

Abstract

A rotary turbine bypass valve comprises a valve chamber and a valve rotor. The chamber is positioned at a junction of an inlet port, an outlet port and a bypass port. The inlet port is configured to receive exhaust gas, the outlet port is configured to fluidly communicate with a turbine inlet, and the bypass port is configured to fluidly communicate with an exhaust aftertreatment device.The rotor comprises a first and second recess, the first recess defining a primary flow passage, the second recess defining a secondary flow passage. The rotor is rotatable between a first position in which the rotor substantially blocks exhaust gas flow through the bypass port and a second position in which the rotor permits such. The secondary flow passage is configured to selectively permit fluid communication between the inlet port and the bypass port when the primary flow passage is partially blocked.

First claim

What is claimed:

1 . A rotary turbine bypass valve for an engine arrangement, the rotary turbine bypass valve comprising:
a valve chamber positioned at a junction of an inlet port, an outlet port and a bypass port, the inlet port configured to fluidly communicate with a flow of exhaust gas from an engine, the outlet port configured to fluidly communicate with an inlet of a turbine, and the bypass port configured to fluidly communicate with an exhaust aftertreatment device; and a valve rotor supported for rotation, about a valve axis, within the valve chamber, the valve rotor comprising a first recess and a second recess, the first recess defining at least part of a primary flow passage, the second recess defining at least part of a secondary flow passage; wherein the valve rotor is rotatable about the valve axis between a first position in which the valve rotor substantially blocks exhaust gas flow through the bypass port and a second position in which the valve rotor permits exhaust gas flow through the bypass port; and wherein the secondary flow passage is configured to selectively permit fluid communication between the inlet port and the bypass port when the primary flow passage is at least partially blocked.

2 . The rotary turbine bypass valve of claim 1 , wherein the second recess is smaller than the first recess.

3 . The rotary turbine bypass valve claim 1 , wherein the second recess spans at least a portion of an outer circumference of the valve rotor.

4 . The rotary turbine bypass valve of claim 1 , wherein the second recess opposes the first recess.

5 . The rotary turbine bypass valve of claim 1 , wherein the first and second recesses are separated by a barrier.

6 . The rotary turbine bypass valve of claim 5 , wherein the barrier defines a chord of the valve rotor.

7 . The rotary turbine bypass valve of claim 1 , wherein the valve rotor is movable about the valve axis to selectively open and close the primary flow passage whilst the secondary flow passage remains open.

8 . The rotary turbine bypass valve of claim 1 , wherein the secondary flow passage is configured to selectively provide fluid communication between the inlet port and the bypass port when the primary flow passage is substantially blocked.

9 . The rotary turbine bypass valve of any proceeding claim, wherein the first and second recesses occupy substantially the same axial extent of the valve rotor.

10 . The rotary turbine bypass valve of any proceeding claim, wherein the second recess is one or more of generally rectangular, triangular, and/or teardrop-shaped.

11 . The rotary turbine bypass valve of any proceeding claim, wherein the second recess has a substantially uniform depth.

12 . The rotary turbine bypass valve claim 1 , wherein the second recess has a non-uniform depth.

13 . The rotary turbine bypass valve according to claim 1 , wherein the second recess is one of two second recesses forming part of a secondary arrangement, and the first recess is one of two first recesses forming part of a primary arrangement.

14 . The rotary turbine bypass valve of claim 13 , wherein either or both of the second recesses are one or more of generally rectangular, triangular, and teardrop-shaped.

15 . The rotary turbine bypass valve of claim 13 , wherein both of the second recesses have substantially the same shape.

16 . The rotary turbine bypass valve of claim 13 , wherein the second recesses have substantially the same depths.

17 . The rotary turbine bypass valve of claim 13 , wherein the second recesses have different depths.

18 . The rotary turbine bypass valve of claim, wherein the second recesses are circumferentially aligned.

19 . The rotary turbine bypass valve of claim, wherein the second recesses are circumferentially offset.

20 . The rotary turbine bypass valve of claim 13 , wherein the first and/or second arrangements are symmetrically disposed about a length of the valve rotor.

21 . The rotary turbine bypass valve according to claim 1 , wherein the turbine forms part of a turbocharger.

22 . An engine arrangement comprising an engine, a turbine and the rotary turbine bypass valve according to claim 1 .

23 . A method of operating the rotary turbine bypass valve of claim 1 , wherein the rotary turbine bypass valve exhibits the following flow regimes in order as the valve rotor rotates from a position in which the outlet port is substantially blocked:
(i) a complete turbine bypass regime in which the outlet port is substantially blocked by the valve rotor; (ii) a braking regime in which the inlet port is substantially blocked; (iii) a thermal management regime in which the primary flow passage is at least partially blocked and the secondary flow passage permits fluid communication between the inlet port and the bypass port; (iv) a 100% turbine regime in which the bypass port is substantially blocked and the inlet and outlet ports are open; and (v) a wastegate regime in which the outlet port is open and the bypass port is at least partially open.

24 . The method of claim 23 , wherein the rotational position of the valve rotor is adjusted from the position of step (iii) to increase or reduce the extent of the blockage of the primary flow passage to adjust a temperature and/or pressure of the exhaust gas in the inlet port.

25 . The method of claim 23 or 24 , wherein no fuel is supplied to the engine during step (ii).

Assignees

• Cummins Ltd

Inventors

• Willey Donald E
• Brookes Matthew

Classifications

• F02D9/16

  the members being rotatable · CPC title

• F02B37/22

  by varying cross-section of exhaust passages or air passages {, e.g. by throttling turbine inlets or outlets or by varying effective number of guide conduits} (F02B37/24 takes precedence) · CPC title

• F02M26/43

  in which exhaust from only one cylinder or only a group of cylinders is directed to the intake of the engine · CPC title

• F01N3/021

  by means of filters · CPC title

• F01N13/08

  Other arrangements or adaptations of exhaust conduits {(pipes, joints or supports therefor in general F16L; collecting or removing exhaust gases of vehicle engines in workshops B08B15/00, on highways E01C1/005)} · CPC title