Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
  • F02B23/00—Other engines characterised by special shape or construction of combustion chambers to improve operation
  • F02B23/02—Other engines characterised by special shape or construction of combustion chambers to improve operation with compression ignition
  • F02B23/06—Other engines characterised by special shape or construction of combustion chambers to improve operation with compression ignition the combustion space being arranged in working piston
  • F02B23/0618—Other engines characterised by special shape or construction of combustion chambers to improve operation with compression ignition the combustion space being arranged in working piston having in-cylinder means to influence the charge motion
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
  • F02B23/00—Other engines characterised by special shape or construction of combustion chambers to improve operation
  • F02B23/02—Other engines characterised by special shape or construction of combustion chambers to improve operation with compression ignition
  • F02B23/06—Other engines characterised by special shape or construction of combustion chambers to improve operation with compression ignition the combustion space being arranged in working piston
  • F02B23/0696—W-piston bowl, i.e. the combustion space having a central projection pointing towards the cylinder head and the surrounding wall being inclined towards the cylinder wall
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
  • F02B23/00—Other engines characterised by special shape or construction of combustion chambers to improve operation
  • F02B23/02—Other engines characterised by special shape or construction of combustion chambers to improve operation with compression ignition
  • F02B23/06—Other engines characterised by special shape or construction of combustion chambers to improve operation with compression ignition the combustion space being arranged in working piston
  • F02B23/0645—Details related to the fuel injector or the fuel spray
  • F02B23/0648—Means or methods to improve the spray dispersion, evaporation or ignition
  • F02B23/0651—Means or methods to improve the spray dispersion, evaporation or ignition the fuel spray impinging on reflecting surfaces or being specially guided throughout the combustion space
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
  • F02B23/00—Other engines characterised by special shape or construction of combustion chambers to improve operation
  • F02B23/02—Other engines characterised by special shape or construction of combustion chambers to improve operation with compression ignition
  • F02B23/06—Other engines characterised by special shape or construction of combustion chambers to improve operation with compression ignition the combustion space being arranged in working piston
  • F02B23/0645—Details related to the fuel injector or the fuel spray
  • F02B23/0669—Details related to the fuel injector or the fuel spray having multiple fuel spray jets per injector nozzle
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
  • F02B23/00—Other engines characterised by special shape or construction of combustion chambers to improve operation
  • F02B23/02—Other engines characterised by special shape or construction of combustion chambers to improve operation with compression ignition
  • F02B23/06—Other engines characterised by special shape or construction of combustion chambers to improve operation with compression ignition the combustion space being arranged in working piston
  • F02B23/0672—Omega-piston bowl, i.e. the combustion space having a central projection pointing towards the cylinder head and the surrounding wall being inclined towards the cylinder center axis
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
  • F02B23/00—Other engines characterised by special shape or construction of combustion chambers to improve operation
  • F02B23/02—Other engines characterised by special shape or construction of combustion chambers to improve operation with compression ignition
  • F02B23/06—Other engines characterised by special shape or construction of combustion chambers to improve operation with compression ignition the combustion space being arranged in working piston
  • F02B23/0678—Unconventional, complex or non-rotationally symmetrical shapes of the combustion space, e.g. flower like, having special shapes related to the orientation of the fuel spray jets
  • F02B23/0684—Ring like bowl, e.g. toroidal
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
  • F02B23/00—Other engines characterised by special shape or construction of combustion chambers to improve operation
  • F02B23/02—Other engines characterised by special shape or construction of combustion chambers to improve operation with compression ignition
  • F02B23/06—Other engines characterised by special shape or construction of combustion chambers to improve operation with compression ignition the combustion space being arranged in working piston
  • F02B23/0678—Unconventional, complex or non-rotationally symmetrical shapes of the combustion space, e.g. flower like, having special shapes related to the orientation of the fuel spray jets
  • F02B23/0687—Multiple bowls in the piston, e.g. one bowl per fuel spray jet
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
  • F02B23/00—Other engines characterised by special shape or construction of combustion chambers to improve operation
  • F02B23/02—Other engines characterised by special shape or construction of combustion chambers to improve operation with compression ignition
  • F02B23/06—Other engines characterised by special shape or construction of combustion chambers to improve operation with compression ignition the combustion space being arranged in working piston
  • F02B23/0678—Unconventional, complex or non-rotationally symmetrical shapes of the combustion space, e.g. flower like, having special shapes related to the orientation of the fuel spray jets
  • F02B23/0693—Unconventional, complex or non-rotationally symmetrical shapes of the combustion space, e.g. flower like, having special shapes related to the orientation of the fuel spray jets the combustion space consisting of step-wise widened multiple zones of different depth
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
  • F02B23/00—Other engines characterised by special shape or construction of combustion chambers to improve operation
  • F02B23/08—Other engines characterised by special shape or construction of combustion chambers to improve operation with positive ignition
  • F02B23/10—Other engines characterised by special shape or construction of combustion chambers to improve operation with positive ignition with separate admission of air and fuel into cylinder
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
  • F02B23/00—Other engines characterised by special shape or construction of combustion chambers to improve operation
  • F02B23/08—Other engines characterised by special shape or construction of combustion chambers to improve operation with positive ignition
  • F02B23/10—Other engines characterised by special shape or construction of combustion chambers to improve operation with positive ignition with separate admission of air and fuel into cylinder
  • F02B23/101—Other engines characterised by special shape or construction of combustion chambers to improve operation with positive ignition with separate admission of air and fuel into cylinder the injector being placed on or close to the cylinder centre axis, e.g. with mixture formation using spray guided concepts
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02F—CYLINDERS, PISTONS OR CASINGS, FOR COMBUSTION ENGINES; ARRANGEMENTS OF SEALINGS IN COMBUSTION ENGINES
  • F02F3/00—Pistons 
  • F02F3/26—Pistons  having combustion chamber in piston head
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T10/00—Road transport of goods or passengers
  • Y02T10/10—Internal combustion engine [ICE] based vehicles
  • Y02T10/12—Improving ICE efficiencies

Definitions

• the invention relates to an air-compressing internal combustion engine, in particular for spin-free or spin-poor combustion, with at least one reciprocating piston having a substantially rotationally symmetrical to a piston axis combustion bowl, which has a trough bottom with a substantially cone-like elevation and a circumferential trough wall, wherein the trough wall a first torus-like first section adjoining the tray bottom and having a maximum inner first bowl diameter thereafter forming a throat forming second section having a minimum inner second bowl diameter smaller than the inner first bowl diameter and thereafter a third forming a bowl rim region Section forms, wherein - viewed in a meridian section - the first portion has a concave first radius of curvature and the second portion has a convex second radius of curvature, and wherein the third portion forms a first annular surface adjoining the second portion and a second annular surface terminating in the piston end surface, which second annular surface subtends an angle with the first annular surface, the first annul
• the invention relates to an air-compressing internal combustion engine having at least one such piston, wherein in the region of the piston axis, an injection device is arranged so that at least one fuel jet in at least one stroke position of the piston meets the second portion and the fuel jet through the second portion in one to the first Section directed first beam part and a third section directed to the second beam part is divisible.
• a diesel engine piston with a combustion chamber which has a profile surface which protrudes from its inner wall to a central axis of the combustion chamber and on the inner wall has a projection which extends with a predetermined length from the inner wall.
• the projection divides an injection fuel sprayed and atomized onto the projection into a fuel flow in an upper portion and a fuel flow into a lower portion of the combustion chamber.
• the combustion bowl on a core formed by a central elevation which activates a swirl, vortex or vortex, the flow in the combustion chamber forms. Thereby, the mixture of the fuel and the air flowing into the combustion chamber is improved and the mixing ratio can be increased.
• DE 103 92 141 B4 describes a piston for an internal combustion engine which comprises a combustion bowl with a fuel guide structure for diverting at least a portion of the fuel leaving the combustion bowl.
• the piston includes a sharp edge disposed on the outer surface of the piston adjacent the access to the combustion bowl and a rounded fuel receiving lip located within the combustion bowl.
• EP 2 708 714 A2 discloses a combustion chamber for a diesel engine having a combustion bowl having a concave shape so that an injected fuel jet generates a swirl or a squish flow for mixing with air.
• DE 10 2006 020 642 A1 describes a method for operating a direct-injection, self-igniting internal combustion engine, which has pistons each with a piston recess formed in a piston recess, which merges into a substantially annular step space in the transitional region to the piston.
• Injection jets of an injector are directed to the step room and deflected there such that a first subset of fuel in an axial direction and in a radial direction is deflected into the piston recess, that a second subset of fuel in the axial direction and the radial direction deflected via the piston head into the combustion chamber and that a third subset of fuel is deflected in a circumferential direction, wherein the respective third subsets of adjacent injection jets meet in the circumferential direction and are then directed inward in the radial direction.
• the wall of the step room is formed by an axially straight, cylindrical peripheral wall, by a straight in the radial direction, flat bottom, and by a concave curved transition wall.
• peripheral wall may be tilted from + 10 ° to -30 ° with respect to the axial direction and the bottom may be inclined from the radial direction in a range of + 30 ° to -40 °, no explanation is given about the purpose and effect of this measure.
• CN 103 046 997 A shows a similar piston for a diesel internal combustion engine having a step room with an inclined bottom and a wall, wherein the bottom with respect to a normal plane on the piston axis at an angle between 8 ° and 12 ° and the wall is inclined with respect to the piston axis between 80 ° and 100 °. This results in the area of the step room a directed towards the combustion chamber ceiling and then to the piston axis vortex of the injected fuel.
• the pistons described are especially designed for spin-burning processes.
• the object of the invention is to avoid these disadvantages and to reduce soot formation phenomena on the piston in particular in spin-free combustion in internal combustion engines of the type mentioned.
• the formation of a fat zone during combustion is prevented, which otherwise results, in particular when swirling flows occur.
• the formation of soot is thus significantly reduced.
• the resulting vortex zones lead to a thermal relief of the cylinder head, since a lower heat input takes place.
• meridian section of the piston is meant a section along the piston axis of the piston, which is normal to the combustion bowl.
• the meridian section thus yields a meridian plane that is normal to the combustion bowl and that is parallel to or coincident with the piston axis.
• the second annular surface with the piston axis a third angle between about 15 ° and 25 °, preferably 21 °, spans.
• the fuel jet is guided along the second annular surface in the direction of the cylinder wall, wherein the direct contact with the cylinder wall can be avoided.
• the fuel pulse generates a charge movement, which forms in the form of a rotation opposite to the injection jet. This is done both in the area between the piston and the combustion chamber ceiling formed by the fire deck of the cylinder head, and between the piston and the trough bottom.
• the resulting rotating rollers are further fueled by the fuel jets and thereby allow an approximately homogeneous fuel / air mixture. This allows a good and low-emission combustion can be achieved.
• the first and second annular surfaces form a step which deflects the fuel flow from the radial direction in an axial direction.
• the deflection between the first and second annular surface takes place abruptly.
• the abrupt flow deflection in the axial direction causes an increase in speed and a strong swirling or rolling movement about a tangential axis, which immediately travels with depositing fuel or even makes deposition impossible.
• At least one injected fuel jet initiates a vortex or roller movement consisting in each case of two opposing vortex rolls of air and fuel.
• it is advantageous if - based on a largest diameter of the piston - the third radius of curvature is 0.012 ⁇ 50%.
• the inner second bowl diameter is at most about 95% of the diameter of the inner first bowl diameter.
• the second radius of curvature is 0.02 ⁇ 50%.
• the first radius of curvature is 0.06 ⁇ 50% (ie, 0.06 times the largest diameter of the piston) ,
• a directed to the cylinder head pronounced second vortex roll is made possible when the first annular surface and / or the second annular surface are formed as a conical surface.
• the stepped third section and the angled annular surfaces reduce the thermal load of the fire deck of the cylinder head. Since the inlet channels generate no swirl and thus have lower flow losses, it can be entered by a higher charge mass in the combustion chamber. If the air / fuel ratio remains the same, more fuel can thus be supplied, which makes it possible to increase the maximum power for a given displacement.
• the piston design allows a reduced heat transfer to the piston and thus reduced heat losses on the piston.
• the third radius of curvature based on a largest diameter of the piston, is 0.012 ⁇ 50% (i.e., 0.012 times the largest diameter of the piston).
• the piston is suitable in particular for internal combustion engines having a swirl-free or low-swirl inlet channel structure, wherein a swirl number of the flow in the combustion chamber around the piston axis is at most 1.
• inlet structure is meant the shape and arrangement of the intake passages in the cylinder head designed as low-twist passages, which are designed so that little or no swirl is generated when the air flows into the combustion chamber.
• the internal combustion engine operates according to a twist-free combustion process.
• a twist-free combustion process This is to be understood as meaning a combustion method in which no or only a small inlet twist is permitted or necessary, and which has substantially no charge rotation about the piston axis.
• a swirl-free or swirl-poor inlet structure has the advantage that flow losses can be reduced and thus the degree of delivery can be improved. This allows a higher maximum power for a given displacement.
• the inlet channels can be made simpler and shorter.
• At least one jet axis of the injection device divides the piston recess into a lower region adjoining the trough bottom of the piston and upper region adjoining it in the direction of the combustion chamber top wherein the lower region is about 54% to 62%, preferably 56%, and the upper region is about 38% to 46%, preferably 44%, of the entire combustion bowl.
• a particularly good mixing of the injection jets with fresh air can be achieved if the trough wall has a nose-like projection on the second portion at least in an impact area of the fuel jet, wherein preferably the projection continues into the region of the first portion and / or third portion.
• the nose-like projection is preferably formed substantially symmetrically to a piston axis containing the radial plane of the piston.
• the fuel jet is divided by the nose-like projection into a first beam arm and a second beam arm, wherein two mixture vortices arise with different directions of rotation.
• the beam splitting allows optimal utilization of the existing fresh air for combustion. Due to the convexly rounded nose-like projection, the kinetic energy of the fuel jet can be deflected with as little loss as possible in the combustion bowl on both sides of the radial plane.
• the jet pulse of the fuel jet and the shape of the nose-like projection of the trough wall produce a double vortex movement in the combustion bowl, in addition to the double roll movement through the rib-like circumferential projection in the second section. All this together allows optimal utilization of the fresh air.
• the step-shaped design between the first annular surface and the second annular surface in the direction of the cylinder head formed by the cylinder head distributes the impact of the hot combustion zone on the cylinder head to a larger area, thereby a locally very high thermal load peak is prevented or reduced whereby the thermal Load on the cylinder head can be reduced.
• Show: 1 shows a piston of an internal combustion engine according to the invention in a meridian section in a first embodiment
• Fig. 2 is a detail of this piston
• Fig. 3 shows this piston in a plan view
• FIG. 4 shows a swirl-free or swirl-poor inlet channel structure in a plan view
• Figure 7 shows the flow situation in the combustion chamber of the piston at 20 ° after the top dead center.
• FIG. 9 the soot formation situation in the combustion chamber of the piston in its top dead center
• FIG. 10 shows the soot formation situation in the combustion chamber of the piston at 10 ° after its top dead center
• FIG. 11 shows the soot formation situation in the combustion chamber of the piston at 20 ° after its top dead center
• FIG. 12 the soot formation situation in the combustion chamber of the piston at 40 ° after its top dead center
• FIG. 13 shows the flow situation in the combustion chamber of the piston at 10 ° after its top dead center
• FIG. 15 shows a piston of an internal combustion engine according to the invention in a second embodiment in a meridian section according to the line XV - XV in FIG. 16;
• Fig. 16 shows this piston in section along the line XVI- XVI in FIG.
• Fig. 1 shows a piston 1 of an air-compressing internal combustion engine, not shown.
• the piston 1 is particularly suitable for internal combustion engines with spin-free or low-twist inlet channel structure 20, in particular for internal combustion engines with a swirl number in the combustion chamber of a maximum of 1, based on the piston axis 2.
• An example of a possible low-swirl or twist-free inlet structure formed as a low-twist channels inlet channels 21, 22 is shown in FIG. 4.
• the two inlet channels 21, 22 are formed symmetrically, so that cancel the swirl components of the two inlet channels 21, 22.
• combustion chamber trough 3 is formed in the piston 1 .
• the combustion chamber trough 3 of the piston 1 forming at least a large part of the combustion chamber consists of a trough bottom 4 with a conical central elevation 5 and a circumferential trough wall 6.
• the trough wall 6 has a first section 6a, a second section 6b adjoining it and a third section 6c adjoining the second section 6b, wherein the third section 6c adjoins the piston end face 7 facing the cylinder head (not shown) and forms a trough edge region 12.
• the trough wall 6 is at least partially circular-shaped, wherein - viewed in a meridian section of the piston 1 - the concave first radius of curvature Rl of the first section 6a is about 0.06 ⁇ 50% of the largest diameter D of the piston 1.
• the combustion bowl 3 has an inner first diameter d1 which is approximately 0.7 ⁇ 20% of the maximum diameter D of the piston 1.
• the trough wall 6 is retracted and formed overhanging, wherein measured in the region of the second portion 6b inner second bowl diameter d2 is at most about 95% of the inner first bowl diameter dl. Based on the maximum piston diameter D, the inner first bowl diameter d 1 is about 0.65 ⁇ 20%.
• the trough wall 6 is convexly curved in the second section 6 b and has a second radius of curvature R 2 of approximately 0.02 ⁇ 50% of the largest diameter D of the piston 1 ,
• the trough wall 6 is designed to extend between the first section 6a and the second section 6b, it also being possible for a straight section 8 to be formed between the first radius of curvature R1 and the second radius of curvature R2.
• the first radius of curvature Rl can pass directly over a turning point in the second radius of curvature R2.
• the third section 6c of the trough wall 6 consists of a first annular surface 8 and a second annular surface 9, wherein the first annular surface 8 connects directly, ie running and transitionless, to the second radius of curvature R2 of the second section 6b and ends in the piston end face 7.
• the section line between the second annular surface 9 and the piston end face 7 in the exemplary embodiment has a diameter 16 which is approximately 80% of the largest diameter of the piston 1.
• the first annular surfaces 8 and second annular surfaces 9 are formed by conical surfaces.
• the first annular surface 8 with a normal plane ⁇ clamps on the piston axis 2 a first angle ⁇ between approximately 10 ° and 20 °, preferably 15.2 °.
• the adjoining the first annular surface 8 second annular surface 9 is designed to be inclined to the first annular surface 8, wherein the first annular surface 8 with the second annular surface 9 a second angle ß between about 100 ° and 150 °, preferably about 125 °, includes.
• the second annular surface 8 is inclined by a third angle ⁇ between about 15 ° and 25 °, preferably of about 21 °. Between the first annular surface 8 and the second annular surface 9, a defined edge 11 is formed.
• the maximum bowl depth 13 is approximately 0.16 times the maximum diameter D of the piston 1 and the minimum bowl depth 14 measured in the region of the central elevation 5 is approximately 0.061 times the maximum diameter D of the piston 1.
• the distance from the piston end face 7 in the direction The height of the second section 6b measured from the piston axis 2 is approximately 4% of the maximum diameter D of the piston 1.
• the conical projection 5 clamps a normal plane of the piston axis 2 at an angle ⁇ of about 20 ° to 30 ° - in the example about 23 ° - on.
• the survey has a fourth radius of curvature R4, which is about 6% of the largest diameter D of the piston 1.
• fuel is injected via an injection device 10 arranged centrally in the cylinder, the fuel impinging on the second section 6b of the well wall 6 in at least one stroke position of the piston 1. Due to the missing or greatly reduced swirl there is no danger that the Fuel jets are blown into each other, which would lead to high soot formation. As a result, more blasting can be provided in the present swirl-reduced method than in comparable known swirl-bearing methods, for example more than nine, which additionally supports the mixture formation of fuel / air.
• the geometry of the piston 1 and the injection direction of the injection device 10 are coordinated so that - viewed in a meridian section of the located at top dead center OT piston 1 - at least one beam axis Sa of an injection jet S of the injector 10, the combustion bowl 3 in a lower region 3a and an upper region 3b, the lower region 3a being approximately 54% to 62%, preferably 56%, and the upper region 3b being approximately 38% to 46%, preferably 44%, of the entire region of the combustion bowl 3 (FIG. 1). ,
• the start of the fuel injection in the range of -6 ° to 0 ° crank angle is to be selected before the top dead center OT of the piston 1.
• the injection duration is in the range of 35 ° to 42 ° crank angle.
• the fuel jet S is divided by the rib-like projection of the second section 6b into a lower first beam part Sl and an upper second beam part S2, wherein a first turbulence roller T1 and a second turbulet roller T2 arise with different directions of rotation.
• the beam splitting allows ideal utilization of the available fresh air for combustion. Due to the convexly rounded overhanging second section 6b, the kinetic energy of the fuel jet S can be deflected into the combustion bowl 3 with as little loss as possible. Beam pulse of the fuel jet S and shape of the trough wall 6 generate a double vortex or roller movement in the combustion bowl 3, which allows optimum utilization of the fresh air.
• the stepped design between the first annular surface 8 and the second annular surface 9 in the direction the cylinder head distributes the impact of the hot combustion zone on the cylinder head to a larger area, thereby a locally very high thermal load peak is prevented or reduced whereby the thermal load on the cylinder head can be reduced.
• FIGS. 5 to 8 show the flow situation in the piston recess 3 for different crankshaft angles, with velocity vectors v for the air flow and the fuel flow being shown.
• the air / fuel ratio is indicated by gray scale, the fuel concentration f is higher, the darker the gray levels are colored.
• 5 shows the flow situation in the region of top dead center of piston 1, FIG. 6 at 10 ° after top dead center, FIG. 7 at 20 ° after top dead center and FIG. 8 at 40 ° after top dead center of piston 1 It can clearly be seen that in FIG. 8 only a relatively small fuel concentration f can be determined by a marked mixture leaning within the combustion bowl 3.
• FIGS. 9 to 12 show the soot formation situation in the piston recess 3 for different crankshaft angles, the soot concentration ST being indicated by gray scales. The darkening of the gray levels ST is the higher, the darker the gray levels are colored. 9 shows the soot situation in the region of top dead center of piston 1, FIG. 10 at 10 ° after top dead center, FIG. 11 at 20 ° after top dead center and FIG. 12 at 40 ° after top dead center of piston 1 In Fig. 12, virtually no soot concentration ST is more noticeable within the combustion bowl 3.
• FIGS. 13 and 14 very clearly demonstrate the effect of the inventive selection of the third angle ⁇ defined between the piston axis 2 and the second annular surface 9 - between approximately 15 ° and 25 °, preferably 21 °.
• ⁇ defined between the piston axis 2 and the second annular surface 9 - between approximately 15 ° and 25 °, preferably 21 °.
• FIGS. 15 and 16 show a second embodiment of the invention wherein the trough wall 6 has additional nose-like projections 30 or scoop-like or dome-like depressions 31 in the second region 6b, in addition to the rib-like circumferential projection.
• a nose-like projection 30 is provided per injection jet S or injection hole of the injection device 10.
• the nose-like projections 30 protrude in the radial direction into the combustion bowl 3 and are advantageously formed substantially symmetrically to a plane defined by the piston axis 2 and the injection axis Sa radial plane ⁇ .
• the effect of the mass distribution is supplemented in the circumferential direction by the expression of two recesses 31 per injection hole or injection jet S.
• the removal of the nose-like projections from the piston axis 2 is denoted by El, the removal of the recesses 31 by E2.
• the ratio El to E2 is advantageously 0.75 to 0.95, with 8.88 has shown to be particularly favorable.
• the other geometric characteristics are identical to the first embodiment. This geometric arrangement divides the fuel jet S in the circumferential direction in equal parts in beam arms AI and A2 and thus supports the formation of two counter-rotating mixture vortices Wl and W2. As a result, the available atmospheric oxygen is ideally fed to the combustion, which is reflected in a very low soot formation and specific fuel consumption. Fig.
• the nose-like projection 30 is curved convexly similar to the circumferential projection in the second section 6b, wherein the radius of curvature R5 of the nose-like projection 30 may be, for example, 0.02 to 0.03 +/- 50% of the diameter D of the piston 1.
• the fuel spray S is introduced into a lower first beam arm AI and a second beam arm A2 through the nose-like projection 30, which in the exemplary embodiment shown in FIGS. 15 and 16 extends from the first section 6a via the second section 6b to the third section 6c split, wherein a first mixture vortex Wl and a second mixture vortex W2 arise with different directions of rotation.
• the beam splitting allows optimal utilization of the existing fresh air for combustion. Due to the convexly rounded nose-like projection 30, the kinetic energy of the fuel jet S can be deflected as low as possible in the combustion bowl 3 on both sides of the radial plane ⁇ .
• the jet pulse of the fuel jet S and the shape of the nose-like projection 30 of the trough wall 6 produce a double vortex movement in the combustion chamber trough 3, added to the double roll movement by the rib-like circumferential projection in the second section 6b. All this together allows optimal utilization of the fresh air.
• the step-shaped design between the first annular surface 8 and the second annular surface 9 in the direction of the combustion chamber ceiling 29 formed by the cylinder head distributes the impact of the hot combustion zone on the cylinder head to a larger area, thereby preventing or reducing a locally very high thermal load peak whereby the thermal load on the cylinder head can be reduced.
• the piston 1 allows in internal combustion engines with swirl-free intake structure optimum mixture formation and smoke-free combustion of the fuel.

Landscapes

• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Dispersion Chemistry (AREA)
• Combustion Methods Of Internal-Combustion Engines (AREA)
• Pistons, Piston Rings, And Cylinders (AREA)

Priority Applications (5)

Applications Claiming Priority (2)

Publications (1)

Family

ID=58191190

Family Applications (1)

Country Status (7)

Cited By (7)

Families Citing this family (9)

Citations (9)

Family Cites Families (5)

• 2016
  • 2016-03-10 AT ATA50201/2016A patent/AT518516B1/de not_active IP Right Cessation
• 2017
  • 2017-02-21 JP JP2018547973A patent/JP2019507848A/ja active Pending
  • 2017-02-21 US US16/083,686 patent/US20200340391A1/en not_active Abandoned
  • 2017-02-21 DE DE112017000251.6T patent/DE112017000251A5/de not_active Withdrawn
  • 2017-02-21 CN CN201780015977.2A patent/CN108779704A/zh active Pending
  • 2017-02-21 KR KR1020187025991A patent/KR20180120698A/ko not_active Withdrawn
  • 2017-02-21 WO PCT/AT2017/060035 patent/WO2017152203A1/de not_active Ceased

Patent Citations (9)

Also Published As

Similar Documents

Legal Events