Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23C—MILLING
  • B23C3/00—Milling particular work; Special milling operations; Machines therefor
  • B23C3/12—Trimming or finishing edges, e.g. deburring welded corners
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23C—MILLING
  • B23C3/00—Milling particular work; Special milling operations; Machines therefor
  • B23C3/02—Milling surfaces of revolution
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M55/00—Fuel-injection apparatus characterised by their fuel conduits or their venting means; Arrangements of conduits between fuel tank and pump F02M37/00
  • F02M55/02—Conduits between injection pumps and injectors, e.g. conduits between pump and common-rail or conduits between common-rail and injectors
  • F02M55/025—Common rails
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23C—MILLING
  • B23C2215/00—Details of workpieces
  • B23C2215/24—Components of internal combustion engines
  • B23C2215/247—Components of diesel engines
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M2200/00—Details of fuel-injection apparatus, not otherwise provided for
  • F02M2200/03—Fuel-injection apparatus having means for reducing or avoiding stress, e.g. the stress caused by mechanical force, by fluid pressure or by temperature variations
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M2200/00—Details of fuel-injection apparatus, not otherwise provided for
  • F02M2200/80—Fuel injection apparatus manufacture, repair or assembly
  • F02M2200/8069—Fuel injection apparatus manufacture, repair or assembly involving removal of material from the fuel apparatus, e.g. by punching, hydro-erosion or mechanical operation

Definitions

• the present invention relates to a method for producing a common fuel line of an injection system, which consists in producing a fuel line body by hot forging and drilling the chamber along the main axis and producing radial bores for the branching of the injection nozzles, according to the method the opening of the Holes in the chamber of the common fuel line is deburred.
• the object of the present invention is to develop a method which makes it possible to improve the fatigue behavior of the common fuel line of an injection system.
• the invention also has the object to develop a fuel line of an injection system, which is obtained by such a method.
• the present invention relates to a method for machining the edge of the radial bores of the connecting pieces for branching the injection nozzles with the axial chamber of a common fuel line of an injection system of an internal combustion engine, the method according to the method of opening the radial bores into the chamber of the common
• Fuel line is deburred.
• this method is characterized in that a connecting ring is made in the form of a surface comparable to a rotating surface along the axis of the bore, which is created by a surface line with a vertex lying on the axis of rotation by the edge the mouth of the radial bores in the axial
• Chamber is ground, which protrudes from the surface of the axial chamber and that of the radial bores.
• the surface of the connecting ring at the mouth of each radial bore into the common fuel line chamber enables the effects of the cyclical pressure variations in the fuel line to be distributed by avoiding concentrating these effects on the edge, as is the case with a single deburred edge the prior art is the case.
• the processing method is also characterized in that the connecting ring is generated by a surface line, in which:
• the other end is a point on the surface of the axial chamber
• the relative position of the ends on the surface of the radial bore and on that of the axial chamber determines the respective influence of the connecting ring on the surface of the radial bore and on the surface of the axial chamber.
• the surface line thus encloses a certain angle with respect to the axis of the radial bore, it creates a globally frustoconical shape
• the surface line is an arc of a circle with respect to the axis of the radial bore, a straight segment, a line, a segment with a concave curvature with respect to the axis, a combination of concave and convex curved segments.
• a residual compressive stress is induced at least locally in the surface of the connecting ring. This residual compressive stress is particularly induced with the tool that the
• Connection ring a width between at least 0.1 and 0.5 mm.
• This residual voltage in turn depends on the material of the fuel line and on the operating conditions and in particular it depends on the
• the surface line is a straight line with an inclination between 40 ° and 55 ° with respect to the axis of rotation.
• Connecting ring creates the remaining compressive stress in the surface of the ring in the course of the same operation. This residual compressive stress reduces the fatigue effect of the strong cyclical pressure variations in the common fuel line.
• the global angle of the connecting ring is advantageously between 40 ° and 55 °, which leads to an optimal distribution of the cyclic tension which is exerted on the surface of the ring during operation of the fuel line. This distribution is optimal in terms of the residual resistance and the risk of pre-damage to this zone, which is machined on the connection of the radial bores and the bore of the axial chamber.
• the invention also relates to a common fuel line of an injection system obtained by the method as described above, said fuel line consisting of a body provided with an axial chamber into which the radial bores of the nozzles open are integrated in the body and serve for the branching of the injection nozzles or other equipment of the fuel line.
• the opening of the radial bores for branching the injection nozzles with the chamber of the common fuel line comprises a connecting collar at the junction of each radial bore and the axial chamber of the common fuel line.
• FIG. 2 in its parts 4A, 4B sectional views corresponding to the sectional planes of FIG. 2, another embodiment of the connecting ring at the edge of the radial bore and the axial chamber with a surface line in the form of a convex line with two segments, 5 in its parts 5A, 5B and according to sectional planes which are identical to those in FIG. 2, another embodiment of a connecting ring according to the invention, which is produced by a convex curved surface line,
• FIG. 6 shows in its parts 6A, 6B a sectional view according to the sectional planes which are identical to those of FIG. 2, another embodiment of one
• Connecting ring which is produced by a generatrix which combines a shape in a concave curved arc and a shape in a convex curved arc, and
• FIG. 7 in its parts 7A, 7B is a sectional view according to the sectional planes, which are identical to those of FIG. 2, showing another embodiment of a connecting ring with a surface line in the form of a concave line which is formed from two segments.
• the invention relates to a method which makes it possible to improve the fatigue behavior of a common fuel line 100 of an injection system according to FIG. 1.
• Fuel line 100 consists of a hot-forged body 1, into which an axial chamber 11 is drilled, which receives the fuel which has to be put under very high pressure in order to supply the injection nozzles.
• the fuel line comprises integrated nozzles 2 with radial bores 21 which open into the axial chamber 11 of the body 1 in order to receive the end of the lines which are connected to the injection nozzles.
• the fuel line 100 comprises a number of integrated nozzles 2, which depend on the number of injection nozzles to be supplied and on the number of
• One end 101 generally includes the pressure sensor; its other end 102 receives the pressure limiter or pressure regulator, which sends the excess fuel back through outlet port 103 to the reservoir. If one or the other of the above components is not required or otherwise the ends 101 and 102 can also be a stopper or an additional interface connector that is identical to the connector 2,
• part 2A is a cross section through a plane containing the axis ZZ and the axis XX of the axial bore 11,
• - Fig. 2B is a cross section through a plane, the axis ZZ and the
• Transverse axis YY which is perpendicular to the axis XX of the direction of the axial bore 11, contains.
• intersection of the radial bore 21 with the axial bore 11, both of which are considered cylindrical surfaces with a circular cross-section 21S, IIS, is a three-dimensional intersection curve 22 (X, Y, Z) of the fourth degree. Since the diameter of the radial bore 21 is smaller than that of the axial bore 11, the radial bore 21 "sinks" into the axial bore 11 in the side sectional view of FIG. 2A, while in the sectional view of FIG. 2B the cutting curve 22 in the surface IIS of the axial bore 11 is "contained” and fuses with the circular arc of the cross section of the surface IIS of the chamber 11.
• the "highest" surface line of the IIS surface (cylindrical surface generated by a straight line) bears the reference symbol XoXo.
• FIG. 3 shows two embodiments of the method, which consists in producing a connecting ring 3 in the form of a surface which is comparable to a rotating surface 3S (according to the axis ZZ), which also
• Axis of rotation of the radial bore 21 is called by grinding the edge 11 of the mouth of the surface IIS into the axial chamber 11.
• This connecting ring 3 is produced as a surface which is produced by a straight or curved surface line, as will be explained, and whose apex S lies on the axis ZZ.
• the vertex S is fixed on the axis of rotation ZZ.
• the connecting ring is produced, for example, by a tool that schematically has an edge that is formed by the surface line and that rotates about the axis ZZ.
• the rotational surface line is regulated at the cutting edge 22; this regulation can be done by physically following the edge 22, or by command based on the theoretical intersection curve 22 of the two surfaces IIS, 21S, the cylindrical surfaces with circular
• the "vertex" Sv of the surface is that of the The intersection of the surface line and the axis ZZ is not fixed, but shifts on the axis of rotation ZZ according to a path that corresponds to the height difference (e) of the edge 22.
• Surface 21S is a circle, in the second case the geometric location of this intersection with surface 21S is a curve that is shifted from the curve that represents edge 22. Since the difference in height (e) is small, the ground surface is similar to a rotating surface.
• 3A, 3B show the first embodiment of a connecting ring 3, which is a rotating surface 3S, which is generated by a surface line 31g, which rotates about the axis ZZ and is delimited by an upper point 32P and a lower point 33P.
• the surface line 31G intersects the
• Rotation axis ZZ at point S which forms the apex of the rotation cone that it creates.
• the upper point 32 P describes a circle 32 on the surface 21S
• the lower point 33P describes a circle in a plane perpendicular to the axis ZZ.
• this circle 33 is not the lower edge 34 of the connecting ring 3 and it only coincides with the lower edge 34 in the plane ZZ / XX (FIG. 3A).
• This surface line 31g of the rotating surface 3S is, for example, the active surface (cutting edge) of a turning tool of the milling cutter type, which is brought into engagement with the radial bore 21 and then unfolded therein, around the cutting curve 22 of the radial one
• the surface line 31g engages the surface 21S of the radial bore 21 by forming the circular upper edge 32 of the connecting ring 3, which is described by the point 32 P.
• the lower edge 34 of the surface 31S of the connecting ring 3 is the curve described by the cut (current point 34P) of the surface line 31g and the surface IIS of the axial bore 11, since this cut lies by definition on the surface IIS, whatever the angular position is the generatrix 31g about the axis of rotation ZZ.
• the lower end 33P of the surface line 31g describes a circle in a plane perpendicular to the ZZ axis, whereas during this rotation of the surface line 31g (assumed contained in a plane which passes through the ZZ axis) about the ZZ axis, the current point 34 P lies at the intersection of the generatrix 31g and the surface IIS; in the course of the rotation of the generatrix, it moves on the segment 33P-34Po of the generatrix 31g between the lowest point 33P and the uppermost intersection 34Po.
• the curve 34 appears in section in the side view of FIG. 3A. It corresponds to a kind of a three-dimensional ellipse with two planes of symmetry; in the projection in the plane XX, ZZ (Fig. 3A) it is very compressed at the lowest points (33Po) and at the uppermost points (34Po) (Fig. 3A).
• 3A, 3B are divided into two parts by the axis ZZ, around the
• FIG. 3A shows the cross section of the surface 3S with the surface line 31g in the plane XX / ZZ, the circular shape of the upper edge 32 and the three-dimensional curve 34 of the lower edge thereof
• FIG. 3A shows the surface line 31g in the plane XX / ZZ with its two ends 32P and 33P and the current point 34P at the highest
• the cut edge 22 has been shown to reduce the spread of the
• FIG. 3B shows the sectional view before the edge 22 is ground off. Since the edge 22 is cut in the surface IIS, its projection in the plane YY / ZZ is an arc of a circle which is delimited by the lower points 22B and reaches the two upper points 22H which are united on the surface line XOXO.
• FIG. 3B shows the generatrix 31g and its end 32P on the surface 21S and its end 33P on the surface IIS. In these two extreme positions, the point 33P is 33Po.
• the right part of FIG. 3B shows the departure of the edge 22 in the plane YY / ZZ.
• the two curved arrows indicate the progress of the current point 34P on the surface IIS, which rises up to the upper straight line XoXo due to the rotation of the surface line 31g.
• 3C, 3D show sectional views corresponding to the second embodiment of the method, according to which the section Sv of the surface line 31gv is regulated with the axis of rotation ZZ at the cutting edge 22.
• This can be schematized in that the section Sv is displaced on the axis ZZ over a distance of length (e) which is equal to the difference in height of the curve of the edge 22.
• intersection 34P of the generatrix 31gv with the surface IIS describes a curve 34v which is contained between the curve 22 and the curve 34 of the generatrix 31G of the first embodiment; this curve 34 was sketched in Fig. 3C for comparison.
• the surface area of the ring 3Sv obtained is thus slightly reduced in relation to that of the ring 3S of a surface line 31g with a fixed apex S.
• the difference between these two surfaces is reduced all the more, since the practical production of these surfaces on a very small scale in comparison to that of Figures 3A-3D.
• 4A, 4B show the case of a surface line 41g in the form of a line convex with respect to the axis ZZ, which consists of two straight line segments 41gl, 41g2 which meet at point 41g3 under the same display conditions as above.
• the surface line 41g intersects the edge 22 in accordance with a rotating double cone about the axis ZZ; the two parts 3S1, 3S2 of this double cone, which the
• Connection point 41g3 lies below the upper straight line XoXo and circulates on the IIS surface.
• the curve described in this case by point 41g3 is formed from a circular arc around the axis ZZ, starting from the position shown in FIG. 4B, until point 41g3 touches the surface IIS and the segment (41g3-41gl) begins into the surface To penetrate IIS. Starting from this position, the curve is part of the curve of a surface line (41g4-32P), which is described by the current point 41g4 (the current point 41g4 is therefore the equivalent of the point 33P of the surface line 31g) and thus a shape analogous to that the curve of curve 34 of FIGS. 3A, 3B, but smaller.
• This combination of curves, which are generated by the point 41g3, is symmetrical with respect to the two cutting planes XX / ZZ and YY / ZZ like all curves of the different figures.
• Positions 44Po on this side of the points 34Po which are shown as orientation points, and arrive inside the curve 34 by being tangential to the lowest two points 33 Po on the surface IIS.
• FIG. 5 shows in its parts 5A, 5B the case of a surface line 51g which is delimited by the same upper and lower points 32P, 33P as the surface line 31 described above, which intersects the edge 22.
• 5A shows the surface lines 51g and 511g and the curves 54 and 541 for comparison.
• the surface 3S is a conical surface which is generated by a curved surface line around the ZZ axis, the convexity being defined here with respect to the ZZ axis.
• FIG. 6 shows in its parts 6A, 6B a surface line 61g which consists of two curved arches 61gl, 61g2, one of which is convex and the other concave with respect to the axis of rotation ZZ.
• This surface line creates a conical surface 3S with double curvature.
• FIG. 7 shows in its parts 7A, 7B a rotating surface 3S which is generated by a concave surface line 71g, a composition of two straight segments 71gl, 71g2 meeting at point 71g3.
• the surface 3S obtained is, as in the preceding examples, by an upper edge 32 in the form of an arc in the surface 21S and a lower edge 74 which is formed by a 3D curve of the fourth degree, which lies beyond the curve 34 of the generatrix 31g, which is shown for comparison.
• the raised edges for example the upper edge 32 and the lower edge 34, 44, 54, 64, 74 of the surface 3S, can be weakened by a fillet.
• the global angle of a surface line that is, the angle of the straight line that meets the ends 32P, 33P of the surface lines, is preferably an angle between 40 and 55 °.
• the angle of a surface line segment is advantageously between 25 ° and 40 °.
• the width of the surface 3S which is generated by the surface line behind the bore edge 22, is advantageously on the order of 0.1-0.5 mm between the narrowest parts and the widest parts. This width is the distance between points 32P and 34P (current points), which is the segment of the generatrix of variable length that creates the surface 3S of the connecting ring.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• General Engineering & Computer Science (AREA)
• Fuel-Injection Apparatus (AREA)

Priority Applications (3)

Applications Claiming Priority (2)

Publications (1)

Family

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Family Applications (1)

Country Status (5)

Citations (5)

• 2018
  • 2018-10-12 FR FR1859475A patent/FR3087140B1/fr active Active
• 2019
  • 2019-09-30 KR KR1020217013775A patent/KR20210071059A/ko not_active Application Discontinuation
  • 2019-09-30 WO PCT/EP2019/076386 patent/WO2020074296A1/de unknown
  • 2019-09-30 EP EP19773871.9A patent/EP3863787A1/de not_active Withdrawn
  • 2019-09-30 CN CN201980067073.3A patent/CN112823072B/zh active Active

Patent Citations (5)

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