CN113958628A - Reverse braking power generation mechanism on reinforced hydraulic retarder - Google Patents
Reverse braking power generation mechanism on reinforced hydraulic retarder Download PDFInfo
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- 238000004519 manufacturing process Methods 0.000 abstract description 7
- 239000012530 fluid Substances 0.000 description 5
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D57/00—Liquid-resistance brakes; Brakes using the internal friction of fluids or fluid-like media, e.g. powders
- F16D57/02—Liquid-resistance brakes; Brakes using the internal friction of fluids or fluid-like media, e.g. powders with blades or like members braked by the fluid
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Abstract
The invention relates to a reverse braking power generation mechanism on a reinforced hydraulic retarder, and belongs to the technical field of vehicle manufacturing. The reverse power generation mechanism comprises a shell, a gear spline shaft, a front fixed turbine, an intermediate turbine and a rear fixed turbine, wherein the center positions of the front and rear end faces of the shell are respectively provided with a through hole, the gear spline shaft is arranged along the axis of the shell, the front and rear end ends of the gear spline shaft respectively penetrate through the through holes in the two sides of the shell and are respectively connected with the gear spline shaft through a bearing, the front side of the shell is fixedly provided with the front fixed turbine, the rear side of the shell is fixedly provided with the rear fixed turbine, the middle of the gear spline shaft is connected with the intermediate turbine through a spline, the intermediate turbine is a double-faced turbine, and a turbine cavity is respectively formed between the front fixed turbine and the rear fixed turbine. The reverse braking force generating mechanism designed by the invention is provided with two layers of turbine cavities, can generate larger reverse braking force and meets the speed reducing requirement of a large-scale commercial vehicle.
Description
Technical Field
The invention relates to the technical field of vehicle production, in particular to a reverse power generation mechanism on a reinforced hydraulic retarder.
Background
The automobile retarder reduces the downhill running speed of a vehicle through the hydraulic device in use, and a large commercial truck uses exhaust brake for a long time when going down a long slope, so that the hub of a truck is promoted to generate heat and rise temperature, the braking effect of the truck is poor, the braking force is lost seriously, and the running safety is influenced. The hydrodynamic retarder can play a good auxiliary role in long-distance braking of the commercial truck. The existing hydrodynamic retarder on the market at present generally consists of a stator, a rotor, an oil pump, an oil storage tank and a heat exchanger. The stator is a retarder shell and is connected with the rear end of the speed changer or a frame, the rotor is connected with a transmission shaft of a vehicle through a hollow shaft, and blades are cast on the rotor and the stator. When the rotor is in operation, pressure is applied to the oil storage tank through the operation of the control valve, so that the working fluid is filled in the working cavity between the rotor and the stator. When the rotor rotates, a torque is applied to the stator by the working fluid, and the reaction torque of the stator becomes the braking torque of the rotor. The kinetic energy of the automobile is consumed by the friction of the working fluid and the impact on the stator and converted into heat energy, so that the temperature of the working fluid is increased. The working fluid is introduced into the heat exchanger to circulate, transfers heat to the cooling water, and is then discharged through the engine cooling system.
At present, the hydraulic retarder which is marketed and reported in public at home has the following defects: 1. the retarder is assembled on the truck with a large rear axle speed ratio, the reverse braking force (reverse torque) generated by the normal operation of the retarder is less than 3500N.m, the retarder is assembled on the truck with a small rear axle speed ratio, and the reverse braking force (reverse torque) generated by the normal operation of the retarder is less than 3000 N.m. 2. The normal running of a part of freight commercial vehicles on the slope with the running speed exceeding 80Km/H and the downhill gradient exceeding 6 percent cannot be met.
Disclosure of Invention
In order to solve the problems in the prior art, the invention designs a reverse braking force generating mechanism on a reinforced hydraulic retarder, which can output larger directional braking force and meet the retarding requirements of high speed, steep downward slope and the like of a commercial vehicle.
The technical scheme adopted by the invention is as follows: the reverse braking power generation mechanism comprises a shell, a gear spline shaft, a front fixed turbine, a middle turbine and a rear fixed turbine, wherein through holes are respectively formed in the center positions of the front side end face and the rear side end face of the shell;
the inner side surface of the end surface of the front side of the shell is a fixed turbine fixing seat, the fixed turbine is fixedly arranged on the fixed turbine fixing seat, the front part of the gear spline shaft penetrates through a central through hole of the fixed turbine and is hermetically connected with the fixed turbine;
the rear side end face of the shell is a rear fixed turbine fixing seat, the rear fixed turbine fixing seat is provided with an oil passing passage, the rear fixed turbine is installed and fixed on the rear fixed turbine fixing seat, the rear part of the gear spline shaft penetrates through a central hole of the rear fixed turbine, and a gap is reserved between the rear fixed turbine and the rear fixed turbine;
the middle of the gear spline shaft is connected with a middle turbine through a spline, the middle turbine is a double-faced turbine, turbine cavities are formed between the middle turbine and the front fixed turbine and between the middle turbine and the rear fixed turbine respectively, a transmission gear is arranged at the front side end of the gear spline shaft, and a rotary shifting head is arranged at the rear side end of the gear spline shaft.
Furthermore, the front fixed turbine comprises a front fixed turbine outer edge, a front fixed turbine inner edge, a plurality of thick front fixed turbine blades and a front fixed concave ring, the front fixed turbine outer edge is a cylindrical surface on the maximum diameter of the front fixed turbine and an entity formed by an outer ring part of the front fixed concave ring, the front fixed turbine outer edge forms a mounting and positioning surface matched with the front fixed turbine fixing seat, the front fixed turbine inner edge is an annular structure of an inner ring part of the front fixed concave ring, the ring center of the front fixed turbine inner edge is a central through hole of the front fixed turbine, a plurality of sinking type front fixed turbine fixing holes are symmetrically formed in the ring structure of the front fixed turbine inner edge, the front fixed turbine passes through the front fixed turbine fixing holes through bolts to be connected and fixed with the front fixed turbine fixing seat, the plurality of front fixed turbine blades are uniformly distributed along the circumferential direction of the front fixed concave ring, and the front fixed turbine blades are arranged along the radial direction of the front fixed concave ring, the inner side edge of the turbine blade is fixedly connected to the curved surface of the front fixed concave circular ring, the outer side edge is a straight edge which is flush with the end face of the front fixed turbine, two ends of the turbine blade are respectively connected with the outer edge of the front fixed turbine and the inner edge of the front fixed turbine, and the whole front fixed turbine blade is inclined along the axial direction.
Further, the rear fixed turbine comprises a rear fixed turbine outer edge, a rear fixed turbine inner edge, a plurality of thick rear fixed turbine blades and a rear fixed inner concave ring, the rear fixed turbine outer edge is a cylindrical surface on the maximum diameter of the rear fixed turbine and an entity formed by an outer ring part of the rear fixed inner concave ring, the rear fixed turbine outer edge forms a positioning surface for mounting the rear fixed turbine, the rear fixed turbine inner edge is an inner ring part of the rear fixed inner concave ring, the center of the ring of the rear fixed turbine inner edge is a center hole of the rear fixed turbine, the aperture of the center hole is larger than the shaft diameter of a corresponding position of a gear spline shaft, the plurality of rear fixed turbine blades are uniformly distributed along the circumferential direction of the rear fixed inner concave ring, the rear fixed turbine blades are arranged along the radial direction of the rear fixed inner concave ring, the inner side edge of the rear fixed inner concave ring is fixedly connected to a curved surface of the rear fixed inner concave ring, the outer side edge is a straight edge and flush with the rear fixed turbine end surface, and two ends are respectively connected with the rear fixed turbine outer edge and the rear fixed turbine inner edge, the rear fixed turbine blade is integrally inclined in the axial direction, and the inclination direction of the rear fixed turbine blade is opposite to that of the front fixed turbine blade.
Further, the highest protruding department circumference equipartition of dorsal part of turbine is decided to the back is connected with a plurality of turbine fixing bases, the center department of turbine fixing base is opened along the axial has the internal thread fixed orifices, the turbine fixing base passes through bolted connection with the turbine fixing base of deciding after with and fixes.
Furthermore, a turbine exhaust hole which penetrates through is formed in the center of the inner side edge of one turbine blade close to the center of the inner side edge of the corresponding turbine blade on each concave circular ring of the front fixed turbine and the rear fixed turbine, the turbine exhaust hole is a folded hole formed by butting two sections of straight holes, and an annular sealing ring assembling groove which is concentric with the hole is formed in the back face of the front fixed turbine of the turbine exhaust hole of the front fixed turbine.
Further, the intermediate turbine comprises an outer edge of the intermediate turbine, an inner edge of the intermediate turbine and a double-faced inwards-concave ring, the outer edge of the intermediate turbine is an entity part formed by a cylindrical surface on the maximum diameter of the intermediate turbine and outer annular surfaces of the double-faced inwards-concave ring, the inner edge of the intermediate turbine is an annular structure connected with the inner annular surface and the outer annular surface of the double-faced inwards-concave ring, a plurality of oil through holes uniformly distributed along the circumferential direction are formed in the annular structure of the inner edge of the intermediate turbine, an involute tooth profile spline matched with a spline on a gear spline shaft is arranged on the inner annular surface of the inner edge of the intermediate turbine, an A-face turbine blade group and a B-face turbine blade group are respectively arranged on annular inwards-concave curved surfaces on two sides of the double-faced inwards-concave ring, the A-face turbine blade group and the B-face turbine blade group are respectively formed by a plurality of thick intermediate turbine blades which are arranged along the circumferential direction of the annular inwards-concave curved surfaces on two sides of the double-faced inwards-concave ring and are arranged radially, the middle turbine blade inclines along the axial direction, and elastic retainer rings are arranged on two sides of the joint of the middle turbine blade and the gear spline shaft respectively for fixing.
Further, the axial direction of inclination of the intermediate turbine blades of the A-surface turbine blade group and the B-surface turbine blade group is opposite, and the axial direction of inclination of the intermediate turbine blades of the A-surface turbine blade group and the B-surface turbine blade group is opposite to the inclination direction of the turbine blades of the front turbine or the rear turbine which are respectively opposite.
Furthermore, the middle turbine blades of the A-surface turbine blade group and the B-surface turbine blade group are alternately arranged in the circumferential direction, the number of the middle turbine blades of the two side blade groups is the same, and the thicknesses of the middle turbine blades are the same.
Furthermore, the outer side edges of the middle turbine blades of the A-surface turbine blade group and the B-surface turbine blade group are respectively flush with the end surfaces of two sides of the turbine, two ends of the middle turbine blades are respectively connected with the outer edge of the middle turbine and the inner edge of the middle turbine, and the end surfaces of the outer side edges of the front fixed turbine blade, the rear fixed turbine blade and the middle turbine blade are all inclined surfaces.
Further, the perforation of casing front end face passes through lip-type sealing washer and gear spline shaft sealing connection, main bearing and counter bearing are provided with respectively and tight round nut, and tight nut adjustment main bearing and counter bearing and gear spline shaft's work play, and tight nut is provided with lock washer and elastic washer, lock washer is the metal material for it is not hard up after the long-time use of tight round nut to prevent, the elastic washer material is the spring steel, is used for eliminating main bearing and the produced clearance of counter bearing in the use to and the inside contact stress of bearing.
Compared with the prior art, the invention discloses a reverse power generation mechanism on a reinforced hydraulic retarder, which has the advantages that: the gear is meshed with the gear of the external gear transmission mechanism to transmit the external rotary power to the middle turbine which is connected with the spline spindle in a spline fit mode through the gear spline shaft, the front side and the rear side of the middle turbine are respectively provided with the front fixed turbine and the rear fixed turbine, the middle turbine rotates to drive the retarded oil in the turbine cavity to rotate, the retarded oil generates reaction power under the action of the fixed turbines on the two sides, the reaction power firstly acts on the middle turbine and acts on the gear spline shaft matched with the spline spindle through the middle turbine, and finally the gear of the front side end of the gear spline shaft is meshed with the gear of the external gear transmission mechanism to transmit the reaction power to the external transmission mechanism to output the generated reaction power to the external transmission mechanism.
The gear spline shaft of the mechanism is integrally formed, the structure is stable, the requirement on manufacturing precision is relatively low, batch production is easy, and the production cost is low; the middle turbine is a double-faced turbine, can rotate relative to the front fixed turbine and the rear fixed turbine respectively to generate counter braking power after being assembled, has large torque output, and is suitable for the slow braking of large-sized load-carrying vehicles. The three turbines form a blade vortex cavity by a plurality of thick turbine blades, the end surfaces of the outer side edges of the turbine blades are inclined planes, so that the retarder oil can be conveniently and smoothly flushed into the blade vortex cavity, and the bending resistance and the shearing strength are high.
The service life is long: the reaction power generating mechanism is used for the reinforced hydraulic retarder, and the relative motion between the movable turbine and the fixed turbine is non-contact, so the service life of the reaction power generating mechanism is almost lifelong. Only gears and bearings of the whole mechanism are slightly worn during working, and the rest of the mechanism is almost not worn.
Safe and reliable: the whole mechanism of the invention has no vibration, no impact and no pollution under working or non-working state, and has no damage to external devices or environment.
The reverse braking force (reverse torque) is large: compared with other similar products, the reverse braking force generating mechanism is used for the reinforced hydraulic retarder, and the reaction torque of the retarder on an external device can reach more than 6000N.m at most and is far more than that of other similar products.
The energy consumption is low under the non-working state: the reverse braking force generating mechanism is used for enhancing the hydraulic retarder, and almost does not generate energy loss to external devices after the retarder is out of operation.
The production cost is low: the reverse braking force generating mechanism has the advantages of simple structure, easy production and assembly and higher production efficiency.
The installation and the maintenance are convenient: the reverse braking force generating mechanism has a simple structure, is not easy to wear, and is simple to mount and convenient to maintain.
Drawings
Fig. 1 is a schematic view of a tangential structure of a reaction power generating mechanism on the enhanced hydrodynamic retarder.
FIG. 2 is a schematic view of the structure of the gear spline shaft.
FIG. 3 is a front view of the front turbine
FIG. 4 is a rear view of the front turbine
FIG. 5 is a front perspective view of a rear fixed turbine
FIG. 6 is a rear perspective view of the rear fixed turbine
FIG. 7 is a perspective view of an intermediate turbine
In the figure, 1 machine shell, 2 gear spline shafts, 3 front fixed turbines, 4 rear fixed turbines, 5 middle turbines, 11 front fixed turbine fixing seats, 12 rear fixed turbine fixing seats, 13 through holes, 14 turbine cavities, 15 lip-shaped sealing rings, 21 transmission gears, 22 main bearings, 23 auxiliary bearings, 24 rotating shifting blocks, 25 splines, 26 tightening nuts, 27 stop washers, 28 elastic washers, 29 elastic check rings and 31 front fixed turbines are externally added, 32 front fixed turbine inner edges, 33 front fixed turbine blades, 34 front fixed concave circular rings, 35 fixing holes, 36 sealing ring assembling grooves, 37 central through holes, 41 back fixed turbine outer edges, 42 back fixed turbine inner edges, 43 back fixed turbine blades, 44 back fixed concave circular rings, 45 fixing seats, 46 central holes, 51 middle turbine outer edges, 52 middle turbine inner edges, 53 middle turbine blades, 54 double-sided concave circular rings, 55 oil through holes, 56 involute tooth profile splines and 6 turbine exhaust holes.
Detailed Description
The invention is further described with reference to the following figures and specific embodiments. The technical solutions in the embodiments of the present invention are clearly and completely described, and the described embodiments are only some embodiments, but not all embodiments of the present invention. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments of the present invention without any creative effort belong to the protection scope of the present invention.
As shown in fig. 1, the present invention discloses an embodiment of a reverse braking force generating mechanism for enhancing a hydrodynamic retarder, in which the reverse braking force generating mechanism includes a casing 1, a gear spline shaft 2, a front fixed turbine 3, an intermediate turbine 4 and a rear fixed turbine 5. The center positions of the front and rear end surfaces of the casing 1 are respectively provided with a through hole 13. The gear spline shaft 2 is disposed along the axis of the casing 1, and has a front end passing through the through hole 13 in the front end surface of the casing 1 and connected thereto by the main bearing 22, and a rear end passing through the through hole 13 in the rear end surface of the casing 1 and connected thereto by the sub bearing 23.
The medial surface of casing 1 front side end face is leading turbine fixing base 11, and leading turbine installation 3 is fixed on leading turbine fixing base 11. The front part of the gear spline shaft 2 passes through the central through hole 37 of the front turbine 3, and the two are hermetically connected.
The rear end face of the casing 1 is a rear fixed turbine fixing seat 12, and the rear fixed turbine fixing seat 12 is provided with an oil passage for connecting a high-pressure oil cavity of a retarder. The rear fixed turbine 4 is fixed on the rear fixed turbine fixing seat 12, and the rear part of the gear spline shaft 2 passes through a central hole 46 of the rear fixed turbine 4, and a gap is reserved between the two. The front end face of the machine shell 1 is an outward connecting flange, and the rear side is a flange connected with a high-pressure oil cavity.
As shown in fig. 2, the middle of the gear spline shaft 2 is connected with an intermediate turbine 5 through a spline 25, the intermediate turbine 5 is a double-sided turbine, turbine cavities 14 are respectively formed between the intermediate turbine and the front fixed turbine 3 and between the intermediate turbine and the rear fixed turbine 4, a transmission gear 21 is arranged at the front end of the gear spline shaft 2, a rotary shifting head 24 is arranged at the rear end of the gear spline shaft, and the gear spline shaft is made of metal alloy. A lip-shaped sealing ring 15 is arranged in a through hole 13 on the front end face of the machine shell 1 and is in sealing connection with the gear spline shaft 1, and the lip-shaped sealing ring 15 is a rubber sealing element formed by thermoplastic molding of high-temperature-resistant and oil-resistant rubber and a metal framework. The main bearing 22 and the secondary bearing 23 are respectively provided with tightening round nuts 26, and the tightening nuts 26 adjust the working clearances of the main bearing 22 and the secondary bearing 23 with the gear spline shaft 1. The jam nut 26 is provided with a stop washer 27 and an elastic washer 28. The lock washer 27 is made of metal and prevents the round nut 26 from loosening after long-term use. The elastic washer 28 is made of spring steel, and is used for eliminating a clearance generated by the main bearing 22 and the secondary bearing 23 during use and contact stress inside the bearings.
As shown in fig. 3 and 4, the front fixed turbine 3 includes a front fixed turbine outer rim 31, a front fixed turbine inner rim 32, a plurality of thick front fixed turbine blades 33, and a front fixed inner concave ring 34. The outer edge 31 of the front fixed turbine is a cylindrical surface on the maximum diameter of the front fixed turbine 3 and an entity formed by the outer ring part of the front fixed concave ring 34, and the outer edge 31 of the front fixed turbine forms a mounting and positioning surface matched with the fixed seat 11 of the front fixed turbine. The front fixed turbine inner edge 32 is an annular structure of an inner ring part of the front fixed concave circular ring 34, and the circular ring center of the front fixed turbine inner edge 32 is a central through hole 37 of the front fixed turbine 3. The annular structure of the inner edge 32 of the front fixed turbine is symmetrically provided with 6 sinking type front fixed turbine fixing holes 35, and the front fixed turbine 3 penetrates through the front fixed turbine fixing holes 35 through bolts to be connected and fixed with the front fixed turbine fixing seat 11. A plurality of front fixed turbine blades 33 are uniformly distributed along the circumferential direction of the front fixed concave ring 34, the front fixed turbine blades 33 are arranged along the radial direction of the front fixed concave ring 34, the inner side edges of the front fixed turbine blades are fixedly connected to the curved surface of the front fixed concave ring 34, the outer side edges are straight edges and flush with the end surface of the front fixed turbine 3, two ends of the outer side edges are respectively connected with the outer edge 31 and the inner edge 32 of the front fixed turbine, and the whole front fixed turbine blades 33 are inclined along the axial direction.
As shown in fig. 5 and 6, the rear fixed turbine 4 includes a rear fixed turbine outer rim 41, a rear fixed turbine inner rim 42, a plurality of thick rear fixed turbine blades 43 and a rear fixed inner concave ring 44. The outer edge 41 of the rear fixed turbine is a cylindrical surface on the maximum diameter of the rear fixed turbine 4 and an entity formed by the outer ring part of the rear fixed concave circular ring 44, and the outer edge 41 of the rear fixed turbine forms a positioning surface for mounting the rear fixed turbine 4. The inner edge of the rear fixed turbine 4 is an inner ring part of a rear fixed concave ring 44, the center of the ring of the inner edge 42 of the rear fixed turbine is a central hole 46 of the rear fixed turbine 4, the aperture of the central hole 46 is larger than the shaft diameter of the corresponding position of the gear spline shaft 2, a plurality of rear fixed turbine blades 43 are uniformly distributed along the circumferential direction of the rear fixed concave ring 44, the rear fixed turbine blades 43 are arranged along the radial direction of the rear fixed concave ring 44, the inner side edge of the rear fixed turbine blades is fixedly connected to the curved surface of the rear fixed concave ring 44, the outer side edge is a straight edge which is flush with the end surface of the rear fixed turbine 4, and the two ends of the rear fixed turbine blades are respectively connected with the outer edge 41 of the rear fixed turbine and the inner edge 42 of the rear fixed turbine. The rear fixed turbine blades 43 are inclined in the axial direction as a whole in the direction opposite to the direction in which the front fixed turbine blades 33 are inclined.
The turbine exhaust holes 6 which penetrate through are respectively formed in the concave circular rings of the front fixed turbine 3 and the rear fixed turbine 4 and close to the center of the inner side edge of one turbine blade, the turbine exhaust holes 6 are folding holes formed by butting two sections of straight holes, and the turbine exhaust holes 6 of the front fixed turbine 3 are provided with annular sealing ring assembling grooves 36 which are concentric with the holes on the back surface of the front fixed turbine 3. The turbine exhaust holes 6 on the two turbines are respectively butted with the exhaust holes on the turbine fixing seats at two sides.
As shown in connection with fig. 7, the intermediate turbine 5 includes an intermediate turbine outer rim 51, an intermediate turbine inner rim 52, and a double-sided concave circular ring 54. The outer edge 51 of the middle turbine is a solid part formed by a cylindrical surface on the maximum diameter of the middle turbine 5 and the outer ring surface of the double-sided inward concave circular ring 54, the inner edge 52 of the middle turbine is an annular structure connected with the inner ring surface and the outer ring surface of the double-sided inward concave circular ring 54, and the annular structure of the inner edge 52 of the middle turbine is provided with a plurality of oil through holes 55 which are uniformly distributed along the circumferential direction. The inner ring surface of the inner edge 52 of the middle turbine is provided with involute tooth profile splines 56 which are matched with the splines 25 on the spline shaft 2 of the gear. The two side annular concave curved surfaces of the double-sided concave circular ring 54 are respectively provided with an A-side turbine blade group and a B-side turbine blade group, the A-side turbine blade group and the B-side turbine blade group are respectively composed of a plurality of thick middle turbine blades 53 which are circumferentially arranged and radially arranged along the two side annular concave curved surfaces of the double-sided concave circular ring 54, and the middle turbine blades 53 are axially inclined. The outer edges of the intermediate turbine blades 53 on both sides are flush with the end faces on both sides of the intermediate turbine 5, respectively, and both ends are connected to the intermediate turbine outer edge 51 and the intermediate turbine inner edge 52, respectively. The intermediate turbine blades 53 of the a-surface turbine blade group and the B-surface turbine blade group are alternately arranged in the circumferential direction, and the intermediate turbine blades 53 of the both-side blade groups are equal in number and equal in thickness.
The intermediate turbine blades 53 of the a-side turbine blade group and the B-side turbine blade group are inclined in the opposite axial directions, and are inclined in the opposite directions to the turbine blades of the front turbine 3 or the rear turbine 4. The end surfaces of the outer sides of the front fixed turbine blades 33, the rear fixed turbine blades 43, and the intermediate turbine blades 53 are all inclined surfaces.
The front fixed turbine 3, the rear fixed turbine 4 and the middle turbine 5 are all made of metal alloy materials through casting molding and then reprocessing. The middle turbine 5 and the gear spline shaft 2 are closely connected through spline fit, and elastic check rings 29 are respectively arranged on two sides of the connection part for fixing.
The reverse braking power generating mechanism is characterized in that after the retarder starts to work, the reverse braking power generating mechanism is meshed with an external gear through a transmission gear on a gear spline shaft for mutual transmission, external rotating power (torsion) is transmitted to a middle turbine which is assembled on the gear spline shaft in a spline fit mode from the gear spline shaft, the middle turbine is arranged between a front fixed turbine and a rear fixed turbine in a cavity and drives special oil for the retarder in the cavity to rotate to generate reverse braking force (reverse torsion), the reverse braking force is respectively acted between the front fixed turbine and the rear fixed turbine and the middle turbine, the front fixed turbine and the rear fixed turbine are respectively stressed by the same magnitude and opposite directions, the middle turbine rotates under the tangential torsion because the front fixed turbine and the rear fixed turbine are fixed, the middle turbine and the gear spline shaft are mutually matched through an internal spline and an external spline, and the tangential torsion borne by the middle turbine is transmitted to the gear spline shaft, and then the gear on the gear spline shaft and an external gear are mutually transmitted to the outside, namely the mechanism realizes the purpose of utilizing the rotary power (torsion) of external motion to generate the counter power to the outside.
The above description is only for the preferred embodiment of the present invention, and should not be taken as limiting the scope of the invention, which is defined by the appended claims and the description of the invention.
Claims (10)
1. A kind of reverse braking power generating mechanism on the reinforced hydraulic retarder, characterized by that, the said reverse braking power generating mechanism includes the chassis, spline shaft of the gear, front fixed turbine, middle turbine and rear fixed turbine, there are perforations separately in the front, central position of both sides end surface of back of the chassis, the said spline shaft of the gear is set up along axle center of the chassis, its front side end crosses the perforation of the front side end surface of the chassis and connects with it through the main bearing, the back side end crosses the perforation of the back side end surface of the chassis and connects with it through the auxiliary bearing;
the inner side surface of the end surface of the front side of the shell is a fixed turbine fixing seat, the fixed turbine is fixedly arranged on the fixed turbine fixing seat, the front part of the gear spline shaft penetrates through a central through hole of the fixed turbine and is hermetically connected with the fixed turbine;
the rear side end face of the shell is a rear fixed turbine fixing seat, the rear fixed turbine fixing seat is provided with an oil passing passage, the rear fixed turbine is installed and fixed on the rear fixed turbine fixing seat, the rear part of the gear spline shaft penetrates through a central hole of the rear fixed turbine, and a gap is reserved between the rear fixed turbine and the rear fixed turbine;
the middle of the gear spline shaft is connected with a middle turbine through a spline, the middle turbine is a double-faced turbine, turbine cavities are formed between the middle turbine and the front fixed turbine and between the middle turbine and the rear fixed turbine respectively, a transmission gear is arranged at the front side end of the gear spline shaft, and a rotary shifting head is arranged at the rear side end of the gear spline shaft.
2. The mechanism of claim 1, wherein the front turbine includes a front turbine outer rim, a front turbine inner rim, a plurality of thick front turbine blades and a front concave circular ring, the front turbine outer rim is a cylindrical surface on the maximum diameter of the front turbine and is a solid body formed by the outer ring portion of the front concave circular ring, the front turbine outer rim forms a mounting and positioning surface matched with the front turbine fixing seat, the front turbine inner rim is an annular structure of the inner ring portion of the front concave circular ring, the center of the circular ring of the front turbine inner rim is a central through hole of the front turbine, a plurality of sinking front turbine fixing holes are symmetrically formed in the annular structure of the front turbine inner rim, and the front turbine is connected and fixed with the front turbine fixing seat by bolts passing through the front turbine fixing holes, a plurality of front fixed turbine blades are uniformly distributed along the circumferential direction of the front fixed concave circular ring, the front fixed turbine blades are arranged along the radial direction of the front fixed concave circular ring, the inner side edges of the front fixed turbine blades are fixedly connected to the curved surface of the front fixed concave circular ring, the outer side edges of the front fixed turbine blades are parallel and level with the end surface of the front fixed turbine, two ends of the front fixed turbine blades are respectively connected with the outer edge of the front fixed turbine and the inner edge of the front fixed turbine, and the front fixed turbine blades are integrally inclined along the axial direction.
3. The mechanism of claim 2, wherein the rear fixed turbine includes an outer rim of the rear fixed turbine, an inner rim of the rear fixed turbine, a plurality of thick rear fixed turbine blades and a rear fixed concave ring, the outer rim of the rear fixed turbine is a cylindrical surface on the maximum diameter of the rear fixed turbine and an entity formed by an outer ring portion of the rear fixed concave ring, the outer rim of the rear fixed turbine forms a positioning surface for mounting the rear fixed turbine, the inner rim of the rear fixed turbine is an inner ring portion of the rear fixed concave ring, a center of the ring of the inner rim of the rear fixed turbine is a center hole of the rear fixed turbine, an aperture of the center hole is larger than an axial diameter of a gear spline shaft at a position corresponding to the center hole, the plurality of rear fixed turbine blades are uniformly distributed along the circumferential direction of the rear fixed concave ring, the rear fixed turbine blades are arranged along the radial direction of the rear fixed concave ring, and inner side edges of the rear fixed turbine blades are fixedly connected to a curved surface of the rear fixed concave ring, the outer side edge is a straight edge flush with the end face of the rear fixed turbine, two ends of the outer side edge are respectively connected with the outer edge of the rear fixed turbine and the inner edge of the rear fixed turbine, the whole rear fixed turbine blade is inclined along the axial direction, and the inclination direction of the whole rear fixed turbine blade is opposite to that of the front fixed turbine blade.
4. The mechanism of claim 3, wherein a plurality of turbine fixing seats are circumferentially and uniformly distributed at the highest protruding position of the back side of the rear fixed turbine, an internal thread fixing hole is axially formed in the center of each turbine fixing seat, and the turbine fixing seats and the rear fixed turbine fixing seats are fixedly connected through bolts.
5. The mechanism of claim 4, wherein the turbine exhaust hole is a folded hole formed by two straight holes in butt joint, and the turbine exhaust hole of the front fixed turbine is provided with an annular sealing ring assembly groove concentric with the hole on the back of the front fixed turbine.
6. The mechanism as claimed in claim 5, wherein the intermediate turbine includes an outer rim of the intermediate turbine, an inner rim of the intermediate turbine, and a double-sided indent ring, the outer rim of the intermediate turbine is a solid portion formed by a cylindrical surface of the intermediate turbine at the maximum diameter and an outer circumferential surface of the double-sided indent ring, the inner rim of the intermediate turbine is an annular structure connected to the inner and outer circumferential surfaces of the double-sided indent ring, the annular structure of the inner rim of the intermediate turbine has a plurality of oil through holes uniformly arranged along the circumferential direction, an involute tooth profile spline matched with a spline on a gear spline shaft is disposed on the inner circumferential surface of the inner rim of the intermediate turbine, the annular indent surfaces at two sides of the double-sided indent ring are respectively provided with an A-side turbine blade set and a B-side turbine blade set, the A-side turbine blade set and the B-side turbine blade set are respectively circumferentially arranged by a plurality of annular indent surfaces at two sides of the double-sided indent ring, The turbine blade structure comprises a thick middle turbine blade arranged in the radial direction, wherein the middle turbine blade is inclined along the axial direction, and elastic retainer rings are respectively arranged on two sides of the joint of the middle turbine and the gear spline shaft for fixing.
7. A reaction power generating mechanism on an enhanced hydraulic retarder according to claim 6, characterized in that the axial inclination directions of the middle turbine blades of the A-surface turbine blade set and the B-surface turbine blade set are opposite, and are opposite to the inclination directions of the turbine blades of the front turbine or the rear turbine which are respectively opposite.
8. The mechanism of claim 7, wherein the intermediate turbine blades of the surface A turbine blade set and the surface B turbine blade set are alternately arranged in the circumferential direction, and the number of the intermediate turbine blades of the two side blade sets is the same, and the thicknesses of the intermediate turbine blades are the same.
9. The mechanism of claim 8, wherein the outer side edges of the middle turbine blades of the A-surface turbine blade set and the B-surface turbine blade set are flush with the end surfaces of the two sides of the turbine respectively, the two ends of the middle turbine blades are connected with the outer edge of the middle turbine and the inner edge of the middle turbine respectively, and the end surfaces of the outer side edges of the front turbine blade, the rear turbine blade and the middle turbine blade are all inclined surfaces.
10. The mechanism as claimed in claim 9, wherein the through hole on the front end of the housing is sealed with the spline shaft by a lip-shaped sealing ring, the main bearing and the secondary bearing are respectively provided with a tightening nut, the tightening nut adjusts the working clearances between the main bearing and the secondary bearing and the spline shaft, the tightening nut is provided with a stop washer and an elastic washer, the stop washer is made of metal material and is used for preventing the tightening nut from loosening after long-term use, and the elastic washer is made of spring steel and is used for eliminating the clearances generated during the use of the main bearing and the secondary bearing and the contact stress inside the bearing.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111262581.2A CN113958628B (en) | 2021-10-28 | 2021-10-28 | Mechanism for generating reverse braking force on enhanced hydraulic retarder |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111262581.2A CN113958628B (en) | 2021-10-28 | 2021-10-28 | Mechanism for generating reverse braking force on enhanced hydraulic retarder |
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| CN113958628A true CN113958628A (en) | 2022-01-21 |
| CN113958628B CN113958628B (en) | 2024-07-19 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102689596A (en) * | 2011-07-19 | 2012-09-26 | 沈勇 | Retarder for water eddy automobile |
| CN203023351U (en) * | 2013-01-25 | 2013-06-26 | 徐显营 | Stator and rotor structure of hydrodynamic retarder |
| CN204113969U (en) * | 2014-09-30 | 2015-01-21 | 苏州雷姆斯汽车工程有限公司 | Two-chamber three turbo type hydrodynamic retarder |
| CN113531080A (en) * | 2021-08-13 | 2021-10-22 | 山东泰鑫汽车科技有限公司 | Enhanced hydraulic retarder for commercial vehicle |
-
2021
- 2021-10-28 CN CN202111262581.2A patent/CN113958628B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102689596A (en) * | 2011-07-19 | 2012-09-26 | 沈勇 | Retarder for water eddy automobile |
| CN203023351U (en) * | 2013-01-25 | 2013-06-26 | 徐显营 | Stator and rotor structure of hydrodynamic retarder |
| CN204113969U (en) * | 2014-09-30 | 2015-01-21 | 苏州雷姆斯汽车工程有限公司 | Two-chamber three turbo type hydrodynamic retarder |
| CN113531080A (en) * | 2021-08-13 | 2021-10-22 | 山东泰鑫汽车科技有限公司 | Enhanced hydraulic retarder for commercial vehicle |
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| CN113958628B (en) | 2024-07-19 |
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