KR20210071059A - Method for machining the edge of the bore of the branch connection of a common fuel line and the common fuel line thus manufactured - Google Patents

Abstract

The present invention relates to a method for machining the edge of a radial bore 21 of a connection 2 for branching of an injection nozzle with an axial chamber 11 of a common fuel line 100 of an injection system of an internal combustion engine and, according to this method, the passage of the radial bore 21 into the chamber 11 of the common fuel line is deburred. A connecting rim 3 is produced in the form of a rotating surface 3S along the axis ZZ of the bore 21 , this connecting rim having a surface 11S of the axial chamber 11 and a radial bore 21 . The edge 22 of the passage of the radial bore 21 to the axial chamber 11, protruding from the surface 21S of the

Description

Method for machining the edge of the bore of the branch connection of a common fuel line and the common fuel line thus manufactured

The present invention relates to a method for manufacturing a common fuel line of an injection system, which is configured to manufacture a fuel line body by warm forging and through machining a chamber along a main axis and by forming a radial bore for a branching of an injection nozzle. In accordance with this method, the passage of the bore into the chamber of the common fuel line is deburred.

Very high fuel pressure variations cause severe fatigue in the common fuel line of the injection system, which leads to a risk of rupture at the connection of the radial bore with the chamber of the fuel line.

It is known to deburr the passage of the radial bore of a common fuel line to reduce the risk of failure.

However, some degree of fatigue remains, along with the risk of sticking and rupture of the engine fueled through the fuel line.

SUMMARY OF THE INVENTION It is an object of the present invention to develop a method capable of improving the fatigue behavior of a common fuel line of an injection system. It is also an object of the invention to develop a fuel line for an injection system obtained by a method of this type.

To this end, the invention is directed to a method for machining the edge of a radial bore of a connection for branching of an injection nozzle with an axial chamber of a common fuel line of an injection system of an internal combustion engine, according to this method The passage of the radial bore into the chamber of the common fuel line is deburred.

According to the invention, this method produces a connecting rim in the form of a surface comparable to a surface of rotation along the axis of the bore, this surface protruding from the surface of the axial chamber and the surface of the radial bore, the axial chamber The edges of the passages of the radial bores of the furnace are polished, thereby creating a jacket line with vertices located on the axis of rotation.

The surface of the connecting rim in the passage of each radial bore to the chamber of the common fuel line prevents the effect of periodic pressure changes from being concentrated on the edge, as in the case of a simply deburred edge according to the prior art. can be distributed within a common fuel line.

Furthermore, the method for machining is characterized in that the connecting rim is created through a jacket line, in which the jacket line

- one end is a point located on the surface of the radial bore,

- the other end is a point on the surface of the axial chamber,

- the relative positions of the end on the surface of the radial bore and the end on the surface of the axial chamber determine the respective influence of the connecting rim on the surface of the radial bore and on the surface of the axial chamber;

The jacket line thus forms a certain angle with respect to the axis of the radial bore, thus creating a generic frusto-conical surface.

According to another preferred feature, the jacket line comprises an arc convex with respect to the axis of the radial bore; straight segment; continuous line; a segment having a concave curvature with respect to the axis; It is a combination of a convex curved segment and a concave curved segment;

In a particularly preferred manner, residual compressive stresses are induced at least locally in the surface of the connecting rim. These residual compressive stresses are induced in particular by the tool creating the connecting rim.

According to another preferred feature, the surface of the connecting rim has a width of at least 0.1 mm to 0.5 mm.

The angle the jacket line locally forms is preferably dependent on the residual compressive stress to be introduced in the surface of the connecting rim.

These residual stresses depend on the material and operating conditions of the fuel line, and in particular the yield point of the fuel line material.

According to another preferred feature, the jacket line is a straight line with an inclination of 40° to 55° with respect to the axis of rotation.

Preferably and as described above, the tool generating the connecting rim induces a residual compressive stress in the surface of the rim in the same working process. This residual compressive stress reduces the fatigue effects of severe cyclic pressure changes in the common fuel line.

The overall angle of the connecting rim is preferably between 40° and 55°, which results in an optimal distribution of the cyclic stresses exerted on the surface of the rim during operation of the fuel line. This distribution is optimal with respect to the residual resistance and the risk of pre-damage of this zone to be machined at the connection of the bore of the axial chamber and the radial bore.

The invention also covers a common fuel line of the injection system obtained by the method as described above, which fuel line consists of a body provided with an axial chamber, which axial chamber is integral to the body and of the injection nozzles. Radial bores of connections used for branches or other equipment in the fuel line follow.

The passage of the radial bore for the branching of the injection nozzle into the chamber of the common fuel line comprises a connecting rim at the integration of the respective radial bore with the axial chamber of the common fuel line.

Preferably, the upper rim and the lower rim of the surface of the connecting rim respectively reach the surface of the axial bore of the chamber with the groove and the surface of the respective radial bore.

부분 3a 및 부분 3b는, 본 발명에 따른 2개의 보어들의 에지에서의 연결 림의 일반적인 제1 실시예의, 도 2a, 도 2b의 절단면에 상응하는 도면이고,

부분 3c 및 부분 3d는, 절단 에지에서 조정되는 2개의 보어들의 에지에서의 연결 림의 제2 실시예의 도면이며,
- 도 4의 부분 4a 및 부분 4b은, 2개의 세그먼트를 구비한 볼록한 연속선 형태의 재킷 라인을 갖는 축방향 챔버 및 반경 방향 보어의 에지에서의 연결 림의 다른 일 실시예의, 도 2의 절단면에 상응하는 단면도이고,
- 도 5의 부분 5a 및 부분 5b는, 볼록한 만곡형 재킷 라인을 통해 형성되는, 본 발명에 따른 연결 림의 다른 일 실시예의, 도 2의 절단면과 동일한 절단면에 따른 도면이며,
- 도 6의 부분 6a 및 부분 6b는, 오목한 만곡형 호 형태와 볼록한 만곡형 호 형태를 조합하는 재킷 라인을 통해 형성되는 연결 림의 다른 일 실시예의, 도 2의 절단면과 동일한 절단면에 따른 단면도이고,
- 도 7의 부분 7a 및 부분 7b는, 2개의 세그먼트들로 형성된 오목한 연속선 형태의 재킷 라인을 갖는 연결 림의 다른 일 실시예를 도시한, 도 2의 절단면과 동일한 절단면에 따른 단면도이다.The invention is explained in more detail below by way of embodiments of a common fuel line having a connecting rim in the form of a rotating surface at the connecting edge between the radial bore and the axial chamber, these embodiments being enlarged in the figures shown on a scale.
1 is a cross-sectional view of a common fuel line according to the invention,
- part 2a and part 2b of figure 2 of the common fuel line at the height of the radial bore, through a plane bearing on the one hand the axis of the radial bore and the axis of the axial chamber, before application of the method of the invention an axial section, on the other hand a section through a plane perpendicular to the axis of the axial chamber, extending through the axis of the radial bore,
- of Figure 3,

Part 3a and part 3b are views corresponding to the cross-sections in FIGS. 2a, 2b , of a first general embodiment of the connecting rim at the edge of the two bores according to the invention,

Part 3c and part 3d are views of a second embodiment of a connecting rim at the edge of two bores that are adjusted at the cutting edge,
- parts 4a and 4b of figure 4 in the cut-away plane of figure 2 of another embodiment of an axial chamber with a jacket line in the form of a convex continuous line with two segments and a connecting rim at the edge of the radial bore a corresponding cross-section,
- part 5a and 5b of figure 5 are views along the same section as in figure 2 of another embodiment of the connecting rim according to the invention, formed through a convex curved jacket line,
- parts 6a and 6b of FIG. 6 are cross-sectional views along the same cutting plane as that of FIG. 2 of another embodiment of a connecting rim formed through a jacket line combining a concave curved arc shape and a convex curved arc shape; ,
- Part 7a and 7b of FIG. 7 are sectional views taken along the same section as in FIG. 2 , showing another embodiment of a connecting rim having a jacket line in the form of a concave continuous line formed of two segments.

According to FIG. 1 , the present invention is directed to a method capable of improving the fatigue behavior of a common fuel line 100 of an injection system according to FIG. 1 . This common fuel line 100 consists of a warm forged body 1 perforated with an axial chamber 11 that receives fuel which is subjected to very high pressure for supply to the injection nozzles. This fuel line comprises an integral connection 2 with a radial bore 21 leading to the axial chamber 11 of the body 1 for receiving the end of the line connected to the injection nozzle.

The fuel line 100 comprises a plurality of integral connections 2 depending on the number of injection nozzles to be supplied and the number of inlets required for the high-pressure pump. One end 101 generally includes a pressure sensor and the other end 102 receives a pressure restrictor or pressure regulator that returns excess fuel through the outlet connection 103 to the reservoir. If one or the other of the above components is not required or otherwise installed, the ends 101 and 102 may receive the same stopper as the connection 2 or an additional interface connection. These various devices are not shown.

Since the manufacture of the radial bore creates a sharp edge and leaves a burr at the point of connection with the axial chamber 11 , this edge is machined with a tool forming the connecting rim 3 as described below. do.

2a and 2b of FIG. 2 have a bore 21 leading to the axial chamber 11 by a cross section of the common fuel line 100 through two vertical planes bearing the axis ZZ of the radial bore 21 . ) of the edge 22 is shown,

- part 2a is a cross-section through the plane bearing the axes XX and ZZ of the axial bore 11,

FIG. 2b is a cross-section through a plane bearing the transverse axis YY and the axis ZZ perpendicular to the axis XX in the direction of the axial bore 11 .

The intersection of the radial bore 21 and the axial bore 11, considered both to be a cylindrical surface 21S, 11S with a circular cross-section, is a quaternary three-dimensional intersection curve 22 (X, Y, Z) to be. Since the diameter of the radial bore 21 is smaller than the diameter of the axial bore 11 , the radial bore 21 “sets down” into the axial bore 11 in the sectional side view of FIG. 2A , whereas FIG. 2B . In the cross section of , the intersecting curve 22 is “embedded” in the surface 11S of the axial bore 11 and merges with the arc of the cross section of the surface 11S of the chamber 11 . The "top" jacket line (cylindrical surface created by a straight line) of the surface 11S has a reference numeral XoXo.

Cross-sectional views through two vertical planes according to part 2a and part 2b of FIG. 2 are used in the description below.

In order to facilitate the interpretation of the figure and the description of the method, it is useful to mark the curve 22 and the four intersections 22B, 22H of the two cut planes. The height difference e (height difference along the axis ZZ) between the two lower points 22B and the two upper points 22H of the curve 22 is also clearly highlighted.

The dimensions of the bore 21 and the dimensions of the axial chamber 11 are not to scale and are very enlarged in order to facilitate the illustration of the curved geometry and the present invention. The same applies to the elements of the drawings relating to the connecting rim 3 described in the various embodiments. Finally, the terms top/bottom and right/left relate only to the orientation of the figures.

In FIG. 3 , the edge 11 of the passage of the surface 11S to the axial chamber 11 is polished, whereby a rotating surface 3S (along the axis ZZ, also referred to as the axis of rotation of the radial bore 21 ) and Two embodiments of a method are shown which are arranged to produce the connecting rim 3 in the form of a comparable surface.

This connecting rim 3 is formed as a surface which, as will be explained, is created through a straight jacket line or a curved jacket line, the vertex S of this surface being located on the axis ZZ.

In the first and simplest case, the vertex S is fixed on the axis of rotation ZZ. The connecting rim, for example, is created by a tool which schematically includes an edge formed through the jacket line and rotates about the axis ZZ.

In the second case, the circular jacket line is adjusted at the cutting edge 22 , this adjustment being made by physically following the edge 22 or the theoretical intersection of the two surfaces 11S, 21S which are cylindrical surfaces with a circular cross-section. This can be done through the indication by the curve 22 . In the second case, the "vertex" Sv of the surface, which is the intersection of the jacket line and the axis ZZ, is not fixed, but is displaced on the axis of rotation ZZ along a path corresponding to the height difference e of the edge 22 do.

In the first case, by way of example, the point of intersection of the jacket line and the surface 21S is due, whereas in the second case the geometrical position of this intersection with the surface 21S is a curve displaced from the curve representing the edge 22 . Because the height difference e is small, the polished surface resembles a rotating surface.

Since the illustration of the method according to the first case is geometrically simpler, since the vertices S of the cone generated through the jacket line are fixed, this explanation is executed first, and the explanation of the second case is, so to speak, an extrapolation of the first one.

3a and 3b show a connecting rim 3 which is a rotating surface 3S which rotates about an axis ZZ and is created through a jacket line 31g defined by an upper point 32P and a lower point 33P. A first embodiment of The jacket line 31G intersects the rotation axis ZZ at the point S forming the vertex of the rotation cone it creates. Upper point 32P represents a circle 32 on surface 21S, while lower point 33P represents a circle in a plane perpendicular to axis ZZ. However, this circle 33 does not coincide with the lower rim 34 of the connecting rim 3, only with the lower rim 34 in the plane ZZ/XX (Fig. 3a). This jacket line 31g of the turning surface 3S is, for example, the active surface (cutting edge) of a milling type turning tool, which tool has a surface 11S of the axial chamber 11 with an axis YY. It engages with the radial bore 21 to overlap the intersection curve 22 of the radial bore 21 with the axis ZZ and then develops in the radial bore.

The jacket line 31g affects the surface 21S of the radial bore 21 through the formation of a circular upper rim 32 , which is described by way of a point 32P, of the connecting rim 3 .

The lower rim 34 of the surface 31S of the connecting rim 3 is a curve described through the intersection of the surface 11S of the axial bore 11 and the jacket line 31g (the running point 34P) , because this intersection is located on the surface 11S, which is, by definition, always also the angular position of the jacket line 31g about the axis of rotation ZZ.

In other words, the lower end 33P of the jacket line 31g represents a circle in a plane perpendicular to the axis ZZ, while the jacket line 31g centered on the axis ZZ (extending through the axis ZZ). During this rotation, the advancing point 34P is located at the intersection of the jacket line 31g and the surface 11S, and during the rotation of the jacket line, the upper point 33P and the lower Displaced on segments 33P-34Po of jacket line 31g between points 34Po.

Curve 34 is shown in cross section in the side view of FIG. 3A . This curve corresponds to a kind of three-dimensional ellipse with two planes of symmetry, and in the projection of the planes XX, ZZ (Fig. 3a), it is highly compressed at the lowest point (33Po) and the highest point (34Po) (Fig. 3A).

Preferably, the illustration used in this description is limited to a cross-section through the two planes XX/ZZ and YY/ZZ corresponding to the outermost position of the jacket line 31g, and intermediate positions complicated to show in the cross-sectional view complicate the illustration. It should be noted that this will make

Figures 3a and 3b are divided into two parts via the axis ZZ for facilitating geometric construction and illustration by a dimension extension line between Figures 3a and 3b.

The right part of FIG. 3a shows a cross-section of a surface 3S with a jacket line 31g in the plane XX/ZZ, the circular shape of the upper rim 32 and of this frusto-conical surface 3S of the connecting rim 3 . A three-dimensional curve 34 of the lower rim is shown.

The left part of Figure 3a shows the jacket line 31g in the plane XX/ZZ having two ends 32P and 33P, and the running point 34P at the top intersection of the straight line X0X0 of the surface 11S. do. In this position, the advancing point 34P has the reference numeral 34Po.

The cutting edge 22 is shown to show the extension of the turning surface 3S above and below this line 22 which disappears due to the formation of the connecting rim 3 .

The right part of Figure 3b shows a cross-sectional view before the edge 22 is polished. Since the edge 22 in the surface 11S is cut off, the projection into the plane YY/ZZ is an arc, which arc is defined by the lower point 22B and the two upper points integrated on the jacket line X0X0. (22H) is reached.

The left part of FIG. 3B shows the jacket line 31g and the jacket line end 32P on the surface 21S and the jacket line end 33P on the surface 11S. In these two extreme positions, point 33P has the reference numeral 33Po. The right part of FIG. 3b shows the departure of the edge 22 in the plane YY/ZZ.

The two curved arrows show the progress of the advancing point 34P on the surface 11S, which rises through the rotation of the jacket line 31g to the upper straight line XoXo.

3c and 3d show sectional views corresponding to a second embodiment of the method, such that the intersection Sv of the jacket line 31gv with the axis of rotation ZZ is adjusted at the cutting edge 22 . This can be plotted as the intersection Sv is displaced in a path having a length e equal to the difference in height of the curve of the edge 22 on the axis ZZ.

This means that the upper point 32P of the jacket line 31gv, which is the point of intersection with the surface 21S, is no longer displaced on the circle 32, but a curve corresponding to the translational motion of the curve 22 along the height H 22V). This height can be seen in Figure 3c. This translational motion means that the rotation of the jacket line 31gv is combined with the translational motion of the length e.

The intersection 34P of the surface 11S and the jacket line 31gv describes a curve 34v nested between the curve 34 and the curve 22 of the jacket line 31G of the first embodiment, and this curve ( 34) is shown in Fig. 3c for comparison.

Accordingly, the obtained surface of the rim 3Sv is slightly reduced compared to the surface of the rim 3S of the jacket line 31g having the fixed vertex S. The difference between these two surfaces is further reduced as the actual manufacture of these surfaces is made on a very small scale compared to the scale of FIGS. 3A-3D .

In the following, the description of various variants is carried out in the case of a conical surface with fixed vertices, and the application to the case of a surface created by a jacket line steered at the edge 22 is simply derived from this.

4a and 4b show the case of a jacket line 41g in the form of a continuous line convex with respect to the axis ZZ, consisting of two straight segments 41g1 and 41g2 meeting at point 41g3, in the same illustrated conditions as above. shown under

For ease of explanation, the jacket line 41g is shown in combination with the jacket line 31g of FIGS. 3A and 3B, and the above reference numerals are kept as far as possible except for modified elements.

jacket line 41g intersects edge 22 according to a double cone of rotation about axis ZZ; The two parts 3S1 , 3S2 of this double cone forming a surface of rotation about the axis ZZ of the connecting rim 3 have a circular edge 35 when the connecting point 41g3 is located on the surface 11S. ) (2D curve), or through a 3D curve when the connection point 41g3 is located below the upper straight line XoXo and circulates on the surface 11S. The curve described by the point 41g3 in this case is the position shown in Fig. 4b, until the point 41g3 contacts the surface 11S and the segments 41g3-41g1 start to penetrate into the surface 11S. It is formed from an arc centered on the axis ZZ starting from . Starting from this position, the curve is the part of the curve of the jacket line 41g4-32P described through the advancing point 41g4 [thus, the advancing point 41g4 is the point 33P of the jacket line 31g. ), thus having a shape similar to but smaller than that of curve 34 in FIGS. 3A and 3B . This combination of curved arcs created by point 41g3 is symmetric about the two end planes XX/ZZ and YY/ZZ, like all curves in the various figures.

The lower rim 44 of these double cones 3S (3S1, 3S2) is a three-dimensional curve having a shape similar to an ellipse that is deformed and compressed in three dimensions, and this curve has two lowermost points on the surface 11S ( 33Po), a straight line XoXo is reached at the upper positions 44Po on this side of the points 34Po shown as reference points and inside the curve 34 .

Part 5a and part 5b of FIG. 5 show the case of jacket line 51g defined by upper and lower points 32P, 33P identical to jacket line 31 described above intersecting with edge 22 . .

Preferably, it should be noted that this jacket line starting at point 33P is tangent to surface 11S at most.

If, for example, through penetration into the axial chamber 11 through the surface 11S, the jacket line has to intersect this surface 11S at the position closest to the surface 11S (according to FIG. 5b ), the point To deviate again from this at 331P (Fig. 5b), instead of the jacket line 51g between the points 32P and 33P, we simply take the part between the points 331P and 32P as the jacket line. it will be enough

This will result in a lower rim 541 closer to the curve 22 than the rim 54 .

5A shows jacket lines 51g and 511g and curves 54 and 541 for comparison.

The surface 3S is a conical surface formed by a curved jacket line centered on the axis ZZ, in which case the degree of convexity is defined with respect to the axis ZZ.

Part 6a and 6b of FIG. 6 show a jacket line 61g consisting of two curved arcs 61g1 , 61g2 , one of which is convex with respect to the axis ZZ and the other is concave. Do. This jacket line creates a conical surface 3S with a double curve.

Part 7a and part 7b of FIG. 7 show the turning surface 3S created by the concave jacket line 71g, the construction of which consists of two straight segments 71g1, 71g2 at point 71g3.

The resulting surface 3S is, as in the above example, an arc-shaped upper rim 32 within the surface 21S and a quaternary 3D located beyond the curve 34 of the jacket line 31g shown for comparison. It is defined by a lower rim 74 formed through a curve.

The surfaces 3S of the connecting rims 3 created by the various jacket lines 31g-71g given by way of non-limiting example are, in order to induce residual stresses there, by a tool with a jacket line or by various tools. can be processed.

Likewise, the raised edge, for example the upper edge 32 and the lower edge 34, 44, 54, 64, 74 of the surface 3S, can be smoothed by the groove.

It should be noted that preferably, the overall angle of the jacket line, ie the angle of the straight line meeting the ends 32P, 33P of the jacket line, is preferably an angle of 40 to 55°.

For example, the angle of a jacket line segment such as jacket line 41g or jacket line 71g is preferably between 25° and 40°.

Finally, the width of the surface 3S created through the jacket line behind the bore edge 22 preferably has a dimension of 0.1 to 0.5 mm between the narrowest part and the widest part. This width is the spacing between points 32P and 34P (running points), this spacing being a segment of the jacket line of varying length, creating the surface 3S of the connecting rim.

100 common fuel lines
101 End of fuel line/inlet of axial chamber
102 End of pressure line/end receiving pressure limiter
103 outlet connection
1 lamp body
11 axial chamber
11S axial chamber surface
2 Integral connection
21 radial bore
21S Radial Bore Surface
22 Edge/intersection curve to be deburred
3 connecting rim
Turning surface of 3S connecting rim
31g, 41g, 51g, 61g, 71g jacket line
32 Upper edge of the rotating surface
The upper point of the 32P jacket line
33 The curve described through the lower point (33P) of the jacket line
The lower point of the 33P jacket line
34 Lower edge of the turning surface (3S)
The intersection/running point of 34P jacket line and surface (21S)
35 Curve described by the junction of two jacket line segments
S fixed vertex
Sv moveable vertices
ZZ Axis/Rotation Axis of Radial Bore

Claims (12)

A method for machining an edge of a radial bore 21 of a connection 2 for branching of an injection nozzle with an axial chamber 11 of a common fuel line 100 of an injection system of an internal combustion engine, comprising: Thus, in the method in which the passage of the radial bore 21 with the axis ZZ into the chamber 11 of the common fuel line is deburring,
A connecting rim 3 is produced in the form of a surface comparable to a surface of rotation 3S along the axis of rotation ZZ, this surface being the surface 11S of the axial chamber 11 and of the radial bore 21 . The edge 22 of the passage of the radial bore 21 to the axial chamber 11, projecting from the surface 21S, is polished, thereby creating a jacket line with vertices S, Sv located on the axis ZZ. Characterized in that produced through, processing method. Method according to claim 1, characterized in that the vertex (S), which is the intersection of the axis (ZZ) and the jacket line (31G), is fixed. Method according to claim 1, characterized in that the vertex (Sv), which is the intersection of the axis (ZZ) and the jacket line (31gv), is adjusted at the edge (22). The connecting rim (3) according to claim 1, wherein the connecting rim (3) is produced via a jacket line (31g, 31gv, 41g, 51g, 61g, 71g), in which jacket line
- one end 32a is a point located on the surface 21S of the radial bore 21,
- the other end 33a is a point on the surface 21S of the axial chamber 21,
- the relative position of the end 32a on the surface 21S of the radial bore 21 and the end 33a on the surface 11S of the axial chamber 11 is the surface 21S of the radial bore 21 and Process method, characterized in that it determines the respective influence of the connecting rim (3) on the surface (11S) of the axial chamber (11). 5. The jacket line according to claim 4, wherein the jacket lines (31g, 41g, 51g, 61g, 71g) are arcs convex about the axis (ZZ); straight segment; continuous line; a segment having a concave curvature about the axis ZZ; a combination of a convex curved segment and a concave curved segment; Method according to claim 1, characterized in that residual compressive stresses are induced in the surface (3S) of the connecting rim (3). Method according to claim 6, characterized in that the residual stress is induced by the tool creating the connecting rim (3). Method according to claim 1, characterized in that the surface of the connecting rim (3) is produced with a width of at least 0.1 mm to 0.5 mm. Method according to claim 1, characterized in that the jacket line is a straight line with an inclination of from 40° to 55° with respect to the axis (ZZ). 10. A common fuel line of an injection system obtained according to the method according to any one of claims 1 to 9, which fuel line consists of a body (1) provided with an axial chamber (11), to which said axial chamber (11) is provided. In a common fuel line, integral with the body (1), the radial bores (21) of the connections (2) for the branch of the injection nozzle run,
The passage of the radial bore 21 for the branching of the injection nozzle with the chamber 11 of the common fuel line 100 , the axial chamber 11 of the common fuel line 100 and the respective radial bore 21 ), characterized in that it comprises a connecting rim (3) at the integral part of the common fuel line. 11. Common fuel line according to claim 10, characterized in that the surface (3S) of the connecting rim (3) has a residual compressive stress at least locally in the material of the body (1) of the common fuel line (100). 11. The bore (21) according to claim 10, wherein the upper edge (32) and the lower edge (33) of the surface (3S) of the connecting rim (3) are, respectively, the surface (11S) of the grooved bore (11) and the bore (21). ), a common fuel line, characterized in that it meets the surface 21S.

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