IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0387732
(2003-03-13)
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발명자
/ 주소 |
|
출원인 / 주소 |
- International Engine Intellectual Property Company, LLC
|
인용정보 |
피인용 횟수 :
15 인용 특허 :
14 |
초록
▼
A combustion chamber assembly for use in a piston of a diesel engine includes a combustion chamber being defined intersecting a crown of the piston, the combustion chamber being substantially defined by three surfaces, a post being in part a spherical surface, a bottom and first side portion being a
A combustion chamber assembly for use in a piston of a diesel engine includes a combustion chamber being defined intersecting a crown of the piston, the combustion chamber being substantially defined by three surfaces, a post being in part a spherical surface, a bottom and first side portion being an annular surface, and a second side portion being a taper surface, the combustion chamber having at least three reentrancies. A piston incorporating the combustion chamber assembly and a method of forming the combustion chamber are further included.
대표청구항
▼
1. A combustion chamber assembly for use in a piston of a diesel engine, comprising:a combustion chamber being defined intersecting a crown of the piston, the combustion chamber being substantially defined by three surfaces, the three surfaces including a post being at least in part a spherical surf
1. A combustion chamber assembly for use in a piston of a diesel engine, comprising:a combustion chamber being defined intersecting a crown of the piston, the combustion chamber being substantially defined by three surfaces, the three surfaces including a post being at least in part a spherical surface, a bottom and first side portion being an annular surface, and a second side portion being a tapered surface, the combustion chamber having a rounded edge intersecting the crown and at least three reentrancies, a reentrancy being a structural ring centered on a center axis of the combustion chamber having a radius that is less than adjacent chamber structure.2. The combustion chamber assembly of claim 1, the combustion post being at least in part a portion of a convex sphere, the spherical surface having a radius and an origin, the origin of the spherical surface lying on a combustion chamber central axis;the annular surface being concave and having an origin and a radius and being operatively coupled to the post; andthe tapered surface being joined at a first end to the annular surface and being transitioned to the crown of the piston.3. The combustion chamber assembly of claim 2 wherein the center axis of the combustion chamber is coaxial with a center axis of the piston.4. The combustion chamber assembly of claim 1 wherein a first reentrancy is disposed at an upper margin of the tapered surface, a second reentrancy transitions the tapered surface to the annular surface and a third reentrancy transitions the annular surface to the spherical post.5. The combustion chamber assembly of claim 1 wherein the combustion chamber is symmetrical about a combustion chamber axis.6. The combustion chamber assembly of claim 1 wherein a distance H4 between the origin of the spherical surface RS1 and a point of intersection of the combustion chamber axis and the bottom plane of the combustion chamber is equal to or greater than zero and less than 0.35 D1, D1 being the piston diameter.7. The combustion chamber assembly of claim 6 wherein the distance H4 between the origin of the spherical surface RS1 and the point of intersection of the combustion chamber axis and the bottom plane of the combustion chamber is substantially 0.105 D1.8. The combustion chamber assembly of claim 2 wherein a distance H3 between the central axis of the combustion chamber and a central axis of the piston is equal to or greater than zero and less than 0.08 D1, D1 being the piston diameter.9. The combustion chamber assembly of claim 8 wherein the distance H3 is preferably zero.10. The combustion chamber assembly of claim 2 wherein an included angle between the tapered surface and the central axis of the combustion chamber is greater than zero and less than 25 degrees.11. The combustion chamber assembly of claim 10 wherein the included angle between the tapered surface and the central axis of the combustion chamber is substantially 10 degrees.12. The combustion chamber assembly of claim 2 wherein the ratio of a dimension L2, the distance between the reentrancy RE2 and the reentrancy RE3, to a dimension L1, the diameter of the annular surface R3, is greater than 0.55 and less than 0.99.13. The combustion chamber assembly of claim 12 wherein the ratio of the dimension L2, the distance between the reentrancy RE2 and the reentrancy RE3, to the dimension L1, the diameter of the annular surface R3, is substantially 0.882.14. The combustion chamber assembly of claim 2 wherein the ratio of a combustion chamber bowl diameter D2 to a piston diameter D1 is greater than 0.44 and less than 0.88.15. The combustion chamber assembly of claim 14 wherein the ratio of the combustion chamber bowl diameter D2 to the piston diameter D1 is preferably substantially 0.596.16. The combustion chamber assembly of claim 2 wherein the ratio of a diameter of the bowl lip D3 to a maximum combustion chamber diameter D2 is greater than 0.33 and less than 0.99.17. The combustion chamber assembly of claim 16 wherein the ratio of the diameter of the bowl lip D3 to the maximum combustion chamber diameter D2 is substantially 0.859.18. The combustion chamber assembly of claim 2 wherein the ratio of an annular surface R1 to a maximum diameter of the bowl D2 is less than 0.17.19. The combustion chamber assembly of claim 18 wherein the ratio of the annular surface R1 to the maximum diameter of the bowl D2 is substantially 0.027.20. The combustion chamber assembly of claim 2 wherein the ratio of an annular surface R2 to a maximum diameter of the bowl D2 is between 0.01 and 0.15.21. The combustion chamber assembly of claim 20 wherein the ratio of the annular surface R2 to the maximum diameter of the bowl D2 is substantially 0.025.22. The combustion chamber assembly of claim 2 wherein the ratio of a bowl depth H1 to a maximum bowl diameter D2 is between 0.21 and 0.55.23. The combustion chamber assembly of claim 22 wherein the ratio of the bowl depth H1 to the maximum bowl diameter D2 is preferably substantially 0.315.24. The combustion chamber assembly of claim 2 wherein a ratio of a height of the bowl post H2 to a maximum bowl diameter D2 is between 0.11 and 0.46.25. The combustion chamber assembly of claim 18 wherein the ratio of the bowl post height H2 to the maximum bowl diameter D2 is preferably substantially 0.216.26. The combustion chamber assembly of claim 2 wherein a ratio of the radius of the spherical surface RS1 to a maximum bowl diameter D2 is between 0.11 and 0.59.27. The combustion chamber assembly of claim 26 wherein the ratio of the radius of the spherical surface RS1 to the maximum bowl diameter D2 is preferably substantially 0.392.28. The combustion chamber assembly of claim 2 wherein the ratio of the radius of an annular surface R3 to a maximum bowl diameter D2 is between 0.05 and 0.34.29. The combustion chamber assembly of claim 28 wherein the ratio of the radius of the annular surface R3 to the maximum bowl diameter D2 is preferably substantially 0.124.30. The combustion chamber assembly of claim 2 wherein the ratio of a radius of an annular surface R4 to a maximum bowl diameter D2 is between 0.01 and 0.09.31. The combustion chamber assembly of claim 30 wherein the ratio of the radius of the annular surface R4 to the maximum bowl diameter D2 is preferably substantially 0.018.32. The combustion chamber assembly of claim 1 the combustion chamber having a central axis, the combustion chamber central axis being coincident with a piston central axis.33. A piston of a diesel engine having a combustion chamber assembly, comprising:a combustion chamber being defined intersecting a crown of the piston, the combustion chamber being substantially defined by three surfaces, the three surfaces including a post being at least in part a spherical surface, a bottom and first side portion being an annular surface, and a second side portion being a tapered surface the combustion chamber having a rounded edge intersecting the crown and at least three reentrancies, a reentrancy being a structural ring centered on a center axis of the combustion chamber having a radius that is less than adjacent chamber structure.34. The piston of claim 33, a combustion chamber first curved surface being a center portion, a center portion being defined at least in part by a surface being a portion of a convex sphere to define the post, the sphere having a radius and an origin, the origin of the sphere lying on a combustion chamber central axis;the annular surface being concave and having an origin and a radius and being joined to the post; andthe tapered surface being joined at a first end to the annular surface and being transitioned to the crown of the piston.35. The piston of claim 34 wherein the center axis of the combustion chamber is coaxial with a center axis of the piston.36. The piston of claim 33 wherein a first reentrancy is at the upper margin of the tapered surface, a second reentrancy transitions the tapered surface to the annular surface and a third reentrancy transitions the annular surface to the spherical post.37. The piston of claim 33 wherein the combustion chamber is symmetrical about a combustion chamber axis.38. The piston of claim 33 wherein a distance H4 between the origin of the spherical surface RS1 and a point of intersection of the combustion chamber axis and a bottom plane of the combustion chamber is equal to or greater than zero and less than 0.35 D1, the piston diameter.39. The piston of claim 38 wherein the distance H4 between the origin of the spherical surface RS1 and the point of intersection of the combustion chamber axis and the bottom plane of the combustion chamber is substantially 0.105 D1.40. The piston of claim 34 wherein a distance H3 between the central axis of the combustion chamber and a central axis of the piston is equal to or greater than zero and less than 0.08 D1, D1 being the piston diameter.41. The piston of claim 40 wherein the distance H3 between the central axis of the combustion chamber and the central axis of the piston is preferably zero.42. The piston of claim 34 wherein an included angle between the tapered surface and the central axis of the combustion chamber is greater than zero and less than 25 degrees.43. The piston of claim 42 wherein the included angle between the tapered surface and the central axis of the combustion chamber is substantially 10 degrees.44. The piston of claim 34 wherein the ratio of a dimension L2, the distance between a reentrancy RE2 and a reentrancy RE3, to a dimension L1, the diameter of the annular surface R3, is greater than 0.55 and less than 0.99.45. The piston of claim 44 wherein the ratio of the dimension L2, the distance between the reentrancy RE2 and the reentrancy RE3, to the dimension L1, the diameter of the annular surface R3, is substantially 0.882.46. The piston of claim 34 wherein the ratio of a combustion chamber bowl diameter D2 to a piston diameter D1 is greater than 0.44 and less than 0.88.47. The piston of claim 46 wherein the ratio of the combustion chamber bowl diameter D2 to the piston diameter D1 is preferably substantially 0.596.48. The piston of claim 34 wherein the ratio of a diameter of a bowl lip D3 to a maximum combustion chamber diameter D2 is greater than 0.33 and less than 0.99.49. The piston of claim 48 wherein the ratio of the diameter of the bowl lip D3 to the maximum combustion chamber diameter D2 is substantially 0.859.50. The piston of claim 34 wherein the ratio of an annular surface R1 to a maximum diameter of the bowl D2 is less than 0.17.51. The piston of claim 50 wherein the ratio of the annular surface R1 to the maximum diameter of the bowl D2 is substantially 0.027.52. The piston of claim 34 wherein the ratio of an annular surface R2 to a maximum diameter of the bowl D2 is between 0.01 and 0.15.53. The piston of claim 52 wherein the ratio of the annular surface R2 to the maximum diameter of the bowl D2 is substantially 0.025.54. The piston of claim 34 wherein the ratio of a bowl depth H1 to a maximum bowl diameter D2 is between 0.21 and 0.55.55. The piston of claim 54 wherein the ratio of the bowl depth H1 to the maximum bowl diameter D2 is preferably substantially 0.315.56. The piston of claim 34 wherein a ratio of the height of a bowl post H2 to a maximum bowl diameter D2 is between 0.11 and 0.46.57. The piston of claim 56 wherein the ratio of the bowl post height H2 to the maximum bowl diameter D2 is preferably substantially 0.216.58. The piston of claim 34 wherein a ratio of the radius of the spherical surface RS1 to a maximum bowl diameter D2 is between 0.11 and 0.59.59. The piston of claim 58 wherein the ratio of the radius of the spherical surface RS1 to the maximum bowl diameter D2 is preferably substantially 0.392.60. The piston of claim 34 wherein the ratio of the radius of an annular surface R3 to a maximum bowl diameter D2 is between 0.05 and 0.34.61. The piston of claim 60 wherein the ratio of the radius of the annular surface R3 to the maximum bowl diameter D2 is preferably substantially 0.124.62. The piston of claim 34 wherein the ratio of a radius of an annular surface R4 to a maximum bowl diameter D2 is between 0.01 and 0.09.63. The piston of claim 62 wherein the ratio of the radius of the annular surface R4 to the maximum bowl diameter D2 is preferably substantially 0.018.64. The piston of claim 33 the combustion chamber having a central axis, the combustion chamber central axis being coincident with a piston central axis.65. A method of defining a combustion chamber assembly for a diesel engine, comprising:forming a combustion chamber as a bowl space in a piston;intersecting the combustion chamber with a crown of the piston;substantially defining the combustion chamber by three surfaces, a post being at least in part a spherical surface, a bottom and first side portion being an annular surface, and a second side portion being a tapered surface;rounding an edge and intersecting the crown at the rounded edge; andforming at least three reentrancies entering the combustion chamber bowl space, each reentrancy defining a structural ring centered on a center axis of the combustion chamber having a radius that is less than adjacent chamber structure.66. The method of claim 65, including forming the combustion chamber spherical surface as a convex combustion chamber center portion with an origin and a radius, disposing the origin of the spherical surface on a combustion chamber central axis;forming the annular surface being concave with an origin and a radius and joining the annular surface to the post;joining the tapered surface at a first end to the annular surface; andtransitioning the tapered surface to the crown of the piston at a second end.67. The method of claim 66 including disposing the center axis of the combustion chamber coaxial with a center axis of the piston.68. The method of claim 65 including forming a first reentrancy proximate a first margin of the tapered surface, transitioning the tapered surface to the annular surface with a second reentrancy and transitioning the annular surface to the spherical post with a third reentrancy.69. The method of claim 65 including forming the combustion chamber symmetrically about a combustion chamber axis.
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