Search

EP-3880942-B1 - ROTARY VALVE

EP3880942B1EP 3880942 B1EP3880942 B1EP 3880942B1EP-3880942-B1

Inventors

  • WILLEY, Donald, E.
  • BROOKES, Matthew

Dates

Publication Date
20260506
Application Date
20191111

Claims (15)

  1. A rotary turbine bypass valve (30) for an engine arrangement (10a, 10b), the rotary turbine bypass valve (30) comprising: a valve chamber (70) positioned at a junction of an inlet port (30b), an outlet port (30a) and a bypass port (30c), the inlet port (30b) configured to fluidly communicate with a flow of exhaust gas from an engine, the outlet port (30a) configured to fluidly communicate with an inlet (20b) of a turbine (20), and the bypass port (30c) configured to fluidly communicate with an exhaust aftertreatment device (24); and a valve rotor (60, 160, 260, 360, 460, 560, 660) supported for rotation, about a valve axis (A 1 ), within the valve chamber (70), the valve rotor (60, 160, 260, 360, 460, 560, 660) comprising a first recess (56, 56a, 56b) and a second recess (58, 58a, 58b, 158, 158b, 258a, 258b, 358a, 358b, 458a, 458b, 558b, 658b), the first recess (56, 56a, 56b) defining at least part of a primary flow passage, the second recess (58, 58a, 58b, 158, 158b, 258a, 258b, 358a, 358b, 458a, 458b, 558b, 658b) defining at least part of a secondary flow passage; wherein the valve rotor (60, 160, 260, 360, 460, 560, 660) is rotatable about the valve axis (A 1 ) between a first position in which the valve rotor (60, 160, 260, 360, 460, 560, 660) substantially blocks exhaust gas flow through the bypass port (30c) and a second position in which the valve rotor (60, 160, 260, 360, 460, 560, 660) permits exhaust gas flow through the bypass port (30c); wherein the secondary flow passage is configured to selectively permit fluid communication between the inlet port (30b) and the bypass port (30c) when the primary flow passage is at least partially blocked; wherein the second recess (58a, 58b, 158, 158b, 258a, 258b, 358a, 358b, 458a, 458b, 558b, 658b) is smaller than the first recess (56a, 56b); and characterized in that the second recess (58a, 58b, 158, 158b, 258a, 258b, 358a, 358b, 458a, 458b, 558b, 658b) is one of two second recesses forming part of a secondary arrangement (64, 164, 264), and the first recess (56a, 56b) is one of two first recesses forming part of a primary arrangement (62).
  2. The rotary turbine bypass valve (30) of claim 1, wherein at least one of the second recesses (58a, 58b, 158a, 158b, 258a, 258b, 358a, 358b, 458a, 458b, 558b, 658b) spans at least a portion of an outer circumference of the valve rotor (60, 160, 260, 360, 460, 560, 660).
  3. The rotary turbine bypass valve (30) of claims 1 or 2, wherein at least one of the second recesses (58a, 58b, 158a, 158b, 258a, 258b, 358a, 358b, 458a, 458b) opposes a corresponding first recess (56a, 56b); and/or wherein at least one of the first and at least one of the second recesses (56a, 56b, 58a, 58b, 158a, 158b, 258a, 258b, 358a, 358b, 458a, 458b) are separated by a barrier; optionally wherein the barrier defines a chord of the valve rotor (60, 160, 260, 360, 460, 560, 660).
  4. The rotary turbine bypass valve (30) of any preceding claim, wherein the valve rotor (60, 160, 260, 360, 460, 560, 660) is movable about the valve axis (A 1 ) to selectively open and close the primary flow passage whilst the secondary flow passage remains open; and/or wherein the secondary flow passage is configured to selectively provide fluid communication between the inlet port (30b) and the bypass port (30c) when the primary flow passage is substantially blocked; and/or wherein at least one of the first and second recesses (56a, 56b, 58a, 58b, 158a, 158b, 258a, 258b, 358a, 358b, 458a, 458b) occupy substantially the same axial extent of the valve rotor (60, 160, 260, 360, 460, 560, 660).
  5. The rotary turbine bypass valve (30) of any preceding claim, wherein at least one of the second recesses (58a, 58b, 158a, 158b, 258a, 258b, 358a, 358b) is one or more of generally rectangular, triangular, and/or teardrop-shaped; optionally wherein both of the second recesses (58a, 58b, 158a, 158b, 258a, 258b, 358a, 358b) are one or more of generally rectangular, triangular, and teardrop-shaped.
  6. The rotary turbine bypass valve (30) of any preceding claim, wherein at least one of the second recesses (58a, 58b, 158a, 158b, 258a, 258b, 358a, 358b, 458a, 458b, 558b) has a substantially uniform depth.
  7. The rotary turbine bypass valve (30) of any of claims 1 to 5, wherein at least one of the second recesses (658b) has a non-uniform depth.
  8. The rotary turbine bypass valve (30) according to any preceding claim, wherein both of the second recesses (58a, 58b, 158a, 158b, 258a, 258b, 358a, 358b, 458a, 458b) have substantially the same shape.
  9. The rotary turbine bypass valve (30) of any preceding claim, wherein the second recesses (58a, 58b, 158a, 158b, 258a, 258b, 358a, 358b, 458a, 458b) have substantially the same depths; or wherein the second recesses have different depths.
  10. The rotary turbine bypass valve (30) of any preceding claim, wherein the second recesses (58a, 58b, 358a, 358b) are circumferentially aligned; or wherein the second recesses (158a, 158b, 258a, 258b, 458a, 458b) are circumferentially offset; and/or wherein the first and/or second arrangements (62, 64, 164, 264) are symmetrically disposed about a length of the valve rotor (60, 160, 260, 360, 460, 560, 660).
  11. The rotary turbine bypass valve (30) according to any preceding claim, wherein the turbine (20) forms part of a turbocharger (18).
  12. An engine arrangement (10a, 10b) comprising an engine, a turbine (20) and the rotary turbine bypass valve (30) according to any preceding claim.
  13. A method of operating the rotary turbine bypass valve (30) of any of claims 1 to 11, wherein the rotary turbine bypass valve (30) exhibits the following flow regimes in order as the valve rotor (60, 160, 260, 360, 460, 560, 660) rotates from a position in which the outlet port (30a) is substantially blocked: (i) a complete turbine (20) bypass regime in which the outlet port (30a) is substantially blocked by the valve rotor (60, 160, 260, 360, 460, 560, 660); (ii) a braking regime in which the inlet port (30b) 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 (30b) and the bypass port (30c); (iv) a 100% turbine (20) regime in which the bypass port (30c) is substantially blocked and the inlet (30b) and outlet (30a) ports are open; and (v) a wastegate regime in which the outlet port (30a) is open and the bypass port (30c) is at least partially open.
  14. The method of claim 13, wherein the rotational position of the valve rotor (60, 160, 260, 360, 460, 560, 660) 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 (30b).
  15. The method of claims 13 or 14, wherein no fuel is supplied to the engine during step (ii).

Description

The present invention relates to a rotary valve. In particular, the present invention relates to a rotary turbine bypass valve suitable for bypassing an inlet to a turbine. Turbines are well known devices for converting the kinetic energy within a flowing gas into useful work. In particular, known turbines convert the kinetic energy of flowing gas into rotation of a rotor (or turbine wheel) of the turbine. The rotation of the rotor may be transmitted by a suitable linkage to any device suitable for doing useful work. Examples of such device include a power generator (such that the turbine forms part of a power turbine) and a compressor (such that the turbine forms part of a turbocharger). As is well known in the art, turbochargers function by their turbine receiving exhaust gas from an internal combustion engine and consequently rotating a turbine wheel of the turbocharger so as to drive rotation of a compressor wheel. The compressor wheel draws in gas and pressurises it so that the gas output by the compressor is at an elevated pressure (or boost pressure) as compared to that at the inlet of the compressor. The output of the compressor of the turbocharger (i.e. the gas at boost pressure) can be fed to an inlet of the internal combustion engine of which the turbocharger forms part. In some applications of turbine, a turbine bypass valve may be required to enable exhaust gas produced by the engine, to which the turbine is attached, to bypass the turbine so the exhaust gas flows to an exhaust aftertreatment system of the engine without passing through the turbine. One known type of turbine bypass valve is a rotary valve. A rotary valve includes a housing defining a valve chamber positioned at a junction of an inlet port, an outlet port and a bypass port. A valve rotor is supported for rotation in the valve chamber. The valve rotor is rotatable about a valve axis between a first position in which the valve rotor permits gas flow through the bypass port and a second position in which the valve rotor blocks gas flow through the bypass port. US2018023460A1 discloses a turbine section of a turbocharger includes a turbine wheel disposed in a turbine housing, the turbine housing defining a gas inlet, a volute configured to direct gas from the inlet to the turbine wheel, and a gas outlet. A rotary diverter valve is disposed in the gas inlet upstream of the volute, and provides three modes of controlling exhaust gas flow about the turbocharger. US2017101925A1 discloses a turbocharger system comprises a first relatively small high-pressure (HP) turbocharger and a second relatively large low pressure (LP) turbocharger. The turbine of the LP turbocharger is connected in series downstream of the turbine of the HP turbocharger. A first exhaust bypass flow passage provides a bypass flow path around the HP turbine. A second exhaust bypass flow passage provides a bypass flow path around the LP turbine. A rotary valve is located at a junction of the first and second bypass flow passages and a first exhaust gas flow passage. The rotary valve comprises a valve rotor which is rotatable selectively to permit or block flow to the LP turbine and to permit or block flow to the first and second bypass paths. US2018238226A1 discloses a variable geometry turbine having a wastegate, which meets the requirements of EGR circulation, includes a turbine housing and a power turbine. The turbine housing is provided with an inner intake gas flow channel and an outer intake gas flow channel which is configured to guide exhaust gas of an engine to the power turbine for driving the power turbine to rotate. The turbine housing is further provided with a wastegate pipeline configured to discharge the exhaust gas without passing through the power turbine, and a wastegate valve configured to control communication and cutting off of the wastegate pipeline, and in the case that an intake gas amount of the exhaust gas entering into the turbine exceeds a preset value, the wastegate valve is opened to discharge a part of the exhaust gas via the wastegate pipeline. There exists a need to provide an alternative rotary turbine bypass valve which overcomes one or more of the disadvantages of known bypass valves whether set out above or otherwise. Additionally, there is a need for an alternative rotary turbine bypass valve. According to a first aspect of the invention there is provided a rotary turbine bypass valve as recited in appended claim 1. The engine arrangement may form part of an automotive vehicle such as an automobile. More specifically, the vehicle may be a car, truck, bus, train or the like. The engine arrangement may be an internal combustion engine. The internal combustion engine may be a petrol engine or a diesel engine. The internal combustion engine may otherwise be a natural gas or Liquefied Petroleum Gas (LPG) engine, or some other variety of engine. The engine arrangement may be a hybrid arrangement which comprises the aforementioned intern