Combustion system for gaseous fuelled internal combustion engine

Patent metadata

Field	Value
Publication number	US-2016348571-A1
Application number	US-201414916952-A
Country	US
Kind code	A1
Filing date	Aug 27, 2014
Priority date	Sep 6, 2013
Publication date	Dec 1, 2016
Grant date	—

Abstract

Gaseous fuel injection pressures are normally less than liquid fuel injection pressures, resulting in reduced gaseous fuel jet momentum and mixing. A combustion system for an internal combustion engine comprises an intake port and valve, a cylinder and a piston that cooperate to provide a quiescent combustion chamber. The piston includes a re-entrant type piston bowl comprising an outer periphery and a protuberance emanating from the outer periphery. A fuel injector is configured to directly introduce a gaseous fuel into the combustion chamber and an ignition source is provided for igniting the gaseous fuel. A controller actuates the fuel injector such that a gaseous fuel jet is directed towards and splits upon impacting the protuberance forming first and second fuel plumes. The first fuel plume is redirected towards a first mixing zone adjacent a cylinder head and the second fuel plume redirected towards a second mixing zone adjacent the piston bowl.

First claim

1 . A method for combusting a gaseous fuel in a combustion chamber of an internal combustion engine comprising:
introducing an intake charge into said combustion chamber with a swirl number within a range of 0 to 0.5; introducing a gaseous fuel jet directly into said combustion chamber; igniting said gaseous fuel; and when under high load conditions:
splitting said gaseous fuel jet into at least a first fuel plume and a second fuel plume;
redirecting said first fuel plume towards a first mixing zone adjacent a cylinder head; and
redirecting said second fuel plume towards a second mixing zone adjacent a piston bowl; or
when under light load conditions:
guiding said gaseous fuel jet towards said second mixing zone.

2 . The method of claim 1 , wherein an injection angle of said gaseous fuel jet comprises a correction angle to compensate for the hydrodynamic effect of boundary layer flow between said gaseous fuel jet and a fire deck of said combustion chamber such that said gaseous fuel jet impacts a splitting feature within a predetermined range of tolerance.

3 . The method of claim 1 , further comprising introducing a pilot fuel jet directly into said combustion chamber whereby said pilot fuel jet compression ignites thereby igniting said gaseous fuel.

4 . The method of claim 3 , further comprising at least one of:
introducing said pilot fuel jet into said combustion chamber before said gaseous fuel jet; and introducing said pilot jet with a pilot fuel injection angle less than a gaseous fuel injection angle.

5 . (canceled)

6 . The method of claim 1 , further comprising an operating mode comprising:
fuelling said internal combustion engine only with a pilot fuel; introducing a pilot fuel jet directly into said combustion chamber; splitting said pilot fuel jet into at least a first pilot fuel plume and a second pilot fuel plume; redirecting said first pilot fuel plume towards said first mixing zone; redirecting said second fuel plume towards said second mixing zone; and compression igniting said first and second pilot fuel plumes.

7 . The method of claim 1 , wherein a positive ignition source ignites said gaseous fuel.

8 . (canceled)

9 . The method of claim 1 , wherein said gaseous fuel jet is split when said piston is between at least one of:
a range of 15° before top dead center during a compression stroke and 15° after top dead center during a power stroke; and a range of 30° before top dead center during a compression stroke and 30° after top dead center during a power stroke.

10 .- 11 . (canceled)

12 . The method of claim 1 , wherein said gaseous fuel is selected from the list containing biogas, butane, ethane, hydrogen, methane, propane, natural gas and mixtures of these fuels.

13 . The method of claim 1 , further comprising during a high fuelling condition:
performing a first gaseous fuel injection such that gaseous fuel is primarily directed towards said first mixing zone; and performing a second gaseous fuel injection such that gaseous fuel is primarily directed towards said second mixing zone.

14 . A combustion system for an internal combustion engine comprising:
a combustion chamber defined in part by a cylinder wall and a cylinder head; a piston further defining said combustion chamber and comprising a re-entrant piston bowl reciprocating within said cylinder wall, said re-entrant piston bowl comprising an outer periphery and a protuberance emanating from said outer periphery; an intake port; an intake valve allows selective communication of an intake charge from said intake port to said combustion chamber, said intake port, said intake valve and said piston cooperating to introduce said intake charge quiescently into said combustion chamber with a swirl number within a range of 0 to 0.5; a fuel injector configured to directly introduce a gaseous fuel into said combustion chamber; an ignition source for igniting said gaseous fuel; and a controller operatively connected with said fuel injector and programmed to actuate said fuel injector to introduce said gaseous fuel into said combustion chamber; wherein when under high load conditions the controller is adjusted so that a gaseous fuel jet emanating from said fuel injector ignites and is directed towards and splits upon impacting said protuberance forming at least a first fuel plume and a second fuel plume, said first fuel plume redirected towards a first mixing zone adjacent said cylinder head and said second fuel plume redirected towards a second mixing zone adjacent said piston bowl; or wherein when under light load conditions the controller is adjusted so that said gaseous fuel jet emanating from said fuel injector is guided by said protuberance towards said second mixing zone.

15 . The combustion system of claim 14 , wherein said fuel injector is configured to introduce said gaseous fuel jet at an injection angle comprising a correction angle to compensate for the hydrodynamic effect of boundary layer flow between said gaseous fuel jet and a fire deck of said combustion chamber such that said gaseous fuel jet impacts a splitting feature within a predetermined range of tolerance.

16 .- 18 . (canceled)

19 . The combustion system of claim 14 , wherein said fuel injector is a concentric needle fuel injector configured to introduce said gaseous fuel and a pilot fuel.

20 . The combustion system of claim 19 , wherein start of injection timing for said pilot fuel is earlier than start of injection timing for said gaseous fuel.

21 . The combustion system of claim 19 , wherein a gaseous fuel jet injection angle is greater than a pilot fuel jet injection angle.

22 . The combustion system of claim 19 , said controller further programmed to introduce only said pilot fuel into said combustion chamber when at least one of (1) said gaseous fuel pressure drops below a predetermined value and (2) a quantity of gaseous fuel drops below a predetermined value, such that said internal combustion engine is fuelled with only said pilot fuel, and wherein a pilot fuel jet emanating from said fuel injector splits upon impacting said protuberance forming at least a first pilot fuel plume and a second pilot fuel flume, said first pilot fuel plume redirected towards said first mixing zone and said second pilot fuel plume redirected towards said second mixing zone.

23 . The combustion system of claim 14 , further comprising a second fuel injector configured to introduce a pilot fuel into said combustion chamber.

24 . The combustion system of claim 23 , a pilot fuel jet emanating from said second fuel injector splits upon impacting said protuberance forming at least a first pilot fuel plume and a second pilot fuel flume, said first pilot fuel plume redirected towards said first mixing zone and said second pilot fuel plume redirected towards said second mixing zone.

25 . (canceled)

26 . The combustion system of claim 24 , wherein said ignition source is one of a spark igniter, a microwave ignition apparatus and a laser igniter.

27 . The combustion system of claim 14 , wherein said combustion chamber comprises a bore size less than 180 mm.

28 . (canceled)

29 . The combustion system of claim 14 , wherein during a high fuelling condition said controller further programmed to:
perform a first gaseous fuel injection such that gaseous fuel is primarily directed towards said first mixing zone; and

Assignees

• Westport Power Inc

Inventors

• Huang Jian
• Goudie Dale W

Classifications

• F02D19/10

  peculiar to compression-ignition engines in which the main fuel is gaseous · CPC title

• F02B23/101

  the injector being placed on or close to the cylinder centre axis, e.g. with mixture formation using spray guided concepts · CPC title

• F02D19/0686

  Injectors · CPC title

• F02B23/0624 Primary

  Swirl flow · CPC title

• F02B23/0651

  the fuel spray impinging on reflecting surfaces or being specially guided throughout the combustion space · CPC title