阅读说明：本技术 一种高湍流气体机燃烧室 (High-turbulence gas engine combustion chamber ) 是由 徐敏 马磊 余光建 田城 陈欢 胡晶晶 于 2020-04-28 设计创作，主要内容包括：本发明涉及发动机领域,尤其涉及一种高湍流气体机燃烧室。高湍流气体机燃烧室,包括由活塞的顶面向活塞内部延伸的燃烧室,所述燃烧室包括位于燃烧室顶面的顶面开口、位于燃烧室上部的喉口、位于燃烧室下部的侧壁和位于燃烧室底部的底面；所述喉口包括沿轴向方向的喉口上边缘、喉口下边缘和过渡连接喉口上边缘和喉口下边缘的环状弧形凸起以及沿径向方向的喉口开口部；所述侧壁从侧壁底部逐渐向内收缩至喉口处形成缩口型燃烧室,所述喉口开口部形状为椭圆形,且所述底面为椭圆形状的平底面。通过改进喉口开口部和底面的形状引导大尺度流动偏离运动轨迹形成撞击效应,提高大尺度流动破碎形成湍流的比例。(The invention relates to the field of engines, in particular to a high-turbulence gas engine combustion chamber. The high-turbulence gas engine combustion chamber comprises a combustion chamber extending from the top surface of a piston to the interior of the piston, wherein the combustion chamber comprises a top surface opening positioned on the top surface of the combustion chamber, a throat positioned on the upper part of the combustion chamber, a side wall positioned on the lower part of the combustion chamber and a bottom surface positioned on the bottom of the combustion chamber; the throat comprises a throat upper edge, a throat lower edge, an annular arc bulge and a throat opening part, wherein the throat upper edge and the throat lower edge are arranged along the axial direction, the annular arc bulge is in transition connection with the throat upper edge and the throat lower edge, and the throat opening part is arranged along the radial direction; the side wall gradually shrinks inwards from the bottom of the side wall to the throat to form a throat-type combustion chamber, the shape of the opening part of the throat is oval, and the bottom surface is an oval flat bottom surface. The impact effect is formed by improving the shapes of the opening part and the bottom surface of the throat opening to guide the large-scale flow to deviate from the motion track, and the proportion of the large-scale flow to be broken and form turbulent flow is improved.)

1. A high turbulence gas engine combustion chamber comprises a combustion chamber (2) extending from the top surface of a piston (1) to the interior of the piston (1), wherein the combustion chamber (2) comprises a top surface opening (3) positioned on the top surface of the combustion chamber (2), a throat (4) positioned on the upper part of the combustion chamber (2), a side wall (7) positioned on the lower part of the combustion chamber (2) and a bottom surface (5) positioned on the bottom of the combustion chamber (2); the throat (4) comprises a throat upper edge (41), a throat lower edge (42) and an annular arc-shaped bulge (43) which is in transition connection with the throat upper edge (41) and the throat lower edge (42) along the axial direction, and a throat opening part (44) along the radial direction; the combustion chamber is characterized in that the side wall (7) gradually shrinks inwards from the bottom of the side wall (7) to the throat (4) to form a throat-shaped combustion chamber, the shape of the throat opening part (44) is oval, and the bottom surface (5) is a flat bottom surface with an oval shape.

2. A highly turbulent gas engine combustion chamber according to claim 1, characterized in that the central axis of the combustion chamber (2) coincides with the piston central axis (o).

3. A highly turbulent gas engine combustor according to claim 2, characterized in that the throat opening (44) center and the bottom surface (5) center are on the piston central axis (o) and the throat opening (44) ovality is greater than or equal to the bottom surface (5) ovality.

4. A highly turbulent gas burner combustion chamber according to claim 3, wherein the long axis of the throat opening (44) is 1.2-4 times the short axis; the long axis of the bottom surface (5) is 1.2-4 times of the short axis.

5. A highly turbulent gas engine combustion chamber according to claim 1 or 2, characterized in that the longitudinal section of the side wall (7) is of a straight line shape inclined from bottom to top in the direction of the piston central axis (o).

6. The high turbulence gas turbine combustor of claim 1 or 2, characterized in that the combustor (2) further comprises a bottom surface transition arc (6) for transitionally connecting the bottom edge of the sidewall (7) and the edge of the bottom surface (5), the longitudinal section of the bottom surface transition arc (6) is in a fillet shape, and the fillet radius of the bottom surface transition arc (6) is 10-100 mm.

7. The high turbulence gas turbine combustor of claim 1 or 2, characterized in that the combustor (2) further comprises an opening transition arc (8) for transitionally connecting the throat upper edge (41) and the top surface opening (3), the longitudinal section of the opening transition arc (8) is in a fillet shape, and the fillet radius of the opening transition arc (8) is 10-50 mm.

8. A highly turbulent gas burner according to claim 1 or 2, wherein the longitudinal section of the annular arc shaped protrusion (43) is in the shape of a fillet, and the fillet radius of the annular arc shaped protrusion (43) is 5-30 mm.

Technical Field

The invention relates to the field of engines, in particular to a high-turbulence gas engine combustion chamber.

Background

At present, a gas engine piston combustion chamber is mainly a straight cylinder type piston combustion chamber, and the intake vortex and the compression vortex of the gas engine piston combustion chamber are weak, so that the combustion tumble and the turbulence intensity are low, the oil-gas mixing is insufficient, and the combustion quality is not ideal. In order to make the gas burn fast and fully in the combustion chamber, researchers try to increase the piston flow area through the throat mode, strengthen the in-cylinder flow, improve turbulent kinetic energy, accelerate the burning rate, chinese utility model patent with application number 201520598758.X discloses a combustion chamber of piston of gas engine, the oral area of body is equipped with the protruding throat fillet of center department from the lateral wall of body to the body, make the oral area of body form the throat for the lower part, when making the gas of engine burn in the combustion chamber, receive the guide of throat fillet, the gas sprays behind the combustion chamber bottom, roll up and cause stronger crowded flow effect by the circular-arc pit of bottom, but the researcher finds that the gas can't effectively break in circular cavity and form the torrent, can't give full play to the effect that the throat mode increases the in-cylinder turbulent kinetic energy and accelerate the burning rate.

Disclosure of Invention

In order to solve the problems, the invention aims to provide a high-turbulence gas turbine combustor, which leads large-scale flow to deviate from a motion track to form an impact effect by improving the shapes of a throat opening part and a bottom surface, and improves the proportion of the large-scale flow to be broken into turbulence.

In order to achieve the purpose, the high-turbulence gas engine combustion chamber comprises a combustion chamber extending from the top surface of a piston to the interior of the piston, wherein the combustion chamber comprises a top surface opening positioned on the top surface of the combustion chamber, a throat positioned on the upper part of the combustion chamber, a side wall positioned on the lower part of the combustion chamber and a bottom surface positioned on the bottom of the combustion chamber; the throat comprises a throat upper edge, a throat lower edge, an annular arc bulge and a throat opening part, wherein the throat upper edge and the throat lower edge are arranged along the axial direction, the annular arc bulge is in transition connection with the throat upper edge and the throat lower edge, and the throat opening part is arranged along the radial direction; the side wall gradually shrinks inwards from the bottom of the side wall to the throat to form a throat-type combustion chamber, the shape of the opening part of the throat is oval, and the bottom surface is an oval flat bottom surface.

Preferably, the central axis of the combustion chamber coincides with the central axis of the piston.

Preferably, the center of the throat opening and the center of the bottom surface are both on the central axis of the piston, and the ellipticity of the throat opening is greater than or equal to the ellipticity of the bottom surface.

Preferably, the long axis of the throat opening part is 1.2 to 4 times of the short axis; the long axis of the bottom surface is 1.2-4 times of the short axis.

Preferably, the longitudinal section of the side wall has a linear shape inclined from bottom to top toward the central axis of the piston.

As a preferred scheme, the combustion chamber further comprises a bottom surface transition arc in transition connection with the bottom edge of the side wall and the bottom edge, the longitudinal section of the bottom surface transition arc is in a round angle shape, and the radius of the round angle of the bottom surface transition arc is 10-100 mm.

Preferably, the combustion chamber further comprises an opening transition arc which is in transition connection with the upper edge of the throat and the opening on the top surface, the longitudinal section of the opening transition arc is in a fillet shape, and the fillet radius of the opening transition arc is 10-50 mm.

Preferably, the longitudinal section of the annular arc-shaped protrusion is in a round angle shape, and the radius of the round angle of the annular arc-shaped protrusion is 5-30 mm.

The invention has the advantages that: compared with a necking combustion chamber with the application number of 201520598758.X, the high-turbulence gas engine combustion chamber disclosed by the invention has the advantages that the shape of the opening part and the bottom surface of the throat is improved to guide large-scale flow to deviate from a motion track to form an impact effect, the proportion of the large-scale flow to be crushed to form turbulence is increased, the turbulence energy intensity in a cylinder is increased, and the combustion speed is accelerated.

Drawings

FIG. 1 is a schematic perspective view of a combustion chamber of a high turbulence gas turbine in accordance with example 1, the combustion chamber being disposed on a top surface of a piston;

FIG. 2 is a top view of FIG. 1;

FIG. 3 is a cross-sectional view A-A of FIG. 2;

FIG. 4 is a cross-sectional view taken along line B-B of FIG. 2;

FIG. 5 is an enlarged view of portion I of FIG. 4;

FIG. 6 is a schematic perspective view of a high turbulence gas turbine combustion chamber disposed on the top surface of a piston in accordance with example 2;

FIG. 7 is a top view of FIG. 6;

the components in the figures are numbered as follows: the combustion chamber comprises a piston 1, a combustion chamber 2, a top surface opening 3, a throat 4, a throat upper edge 41, a throat lower edge 42, an annular arc-shaped bulge 43, a throat opening part 44, a long shaft 44b, a short shaft 44a, a bottom surface 5, a bottom surface transition arc 6, a side wall 7, an opening transition arc 8 and a piston central axis o.

Detailed Description

For a better understanding of the present invention, reference will now be made in detail to the present invention, examples of which are illustrated in the accompanying drawings.