CN117365672A - Low-exciting-force variable-section nozzle blade and matching device thereof - Google Patents
Low-exciting-force variable-section nozzle blade and matching device thereof Download PDFInfo
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- CN117365672A CN117365672A CN202311624838.3A CN202311624838A CN117365672A CN 117365672 A CN117365672 A CN 117365672A CN 202311624838 A CN202311624838 A CN 202311624838A CN 117365672 A CN117365672 A CN 117365672A
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- shifting fork
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- nozzle blade
- nozzle vane
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- 230000005540 biological transmission Effects 0.000 claims abstract description 33
- 238000009423 ventilation Methods 0.000 claims abstract description 14
- 230000033001 locomotion Effects 0.000 claims description 6
- 238000005096 rolling process Methods 0.000 claims description 3
- 230000000712 assembly Effects 0.000 claims description 2
- 238000000429 assembly Methods 0.000 claims description 2
- 238000002347 injection Methods 0.000 claims 5
- 239000007924 injection Substances 0.000 claims 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims 5
- 230000005284 excitation Effects 0.000 claims 3
- 230000013011 mating Effects 0.000 claims 3
- 239000007789 gas Substances 0.000 description 5
- 230000001276 controlling effect Effects 0.000 description 4
- 230000007246 mechanism Effects 0.000 description 4
- 239000002912 waste gas Substances 0.000 description 4
- 230000004043 responsiveness Effects 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 239000000779 smoke Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
- Control Of Turbines (AREA)
Abstract
The invention belongs to the technical field of engine turbochargers, and discloses a low-exciting-force variable-section nozzle blade and a matching device thereof, wherein the low-exciting-force variable-section nozzle blade comprises a shifting fork shaft, one end of the shifting fork shaft is provided with a connecting shaft section, one end, far away from the connecting shaft section, of the shifting fork shaft is integrally connected with a nozzle blade, and the nozzle blade is provided with a ventilation assembly which is convenient for converging high-low pressure air flows; the invention can greatly reduce the exciting force of the turbine, improve the reliability and the transmission efficiency of products, and simultaneously can meet the requirements of certain special products on the appearance and the reliability.
Description
Technical Field
The invention belongs to the technical field of engine turbochargers, and particularly relates to a low-exciting-force variable-section nozzle blade and a matching device thereof.
Background
Turbochargers of different structural forms, which are different from the points of interest in engine matching; the supercharger with the fixed cross-section structure has the matching attention points that the supercharging pressure is difficult to ensure under the medium and high speed working conditions, the low speed and the partial load working conditions of the engine; the supercharger with the waste gas bypass structure has the following attention points that under the conditions of medium and low speed and partial load of an engine, the waste gas energy of a part of high-speed working conditions is sacrificed through the waste gas bypass under the conditions of medium and high speed and full load, and the safe working limit value of the supercharger is ensured so as to meet the reliability requirement.
The turbocharger with the variable cross-section structure is characterized in that a nozzle ring assembly structure is additionally arranged between a volute flow passage of a turbine and the turbine, the area of a nozzle passage is changed by adjusting the angle of a nozzle blade, and the pressure and the flow of engine waste gas are controlled, so that the good matching of the full working condition of the engine is realized.
The structure of a conventional variable cross-section turbocharger is shown in fig. 1 to 4: the main structure comprises: a volute inlet channel 1; a volute throat 2; a nozzle vane 3; turbine blades 4; an active shifting fork positioning pin 5; a driving fork 6; a driven fork 7; a fork pulling disc 8; the volute is matched with an inner hole 9 of the shifting fork disc; a fork shaft 10; a sleeve 11; a transmission plate 12; a drive pin 13; an actuator transmission lever 14; and a middle shell locating pin 15.
When the engine is in a high-speed working condition, the opening degree of the nozzle blade 3 is adjusted and increased, the flow of passing gas is increased, the exhaust pressure is reduced, and the energy of the engine exhaust gas is fully utilized; in the middle-low speed and small load working conditions, the opening of the nozzle vane 3 is regulated and reduced, the flow of passing gas is reduced, the exhaust pressure is increased, the rotating speed of the supercharger is increased, the proper increase of the pressure ratio is realized, in addition, the air supply response of the engine in low speed and acceleration can be improved, the acceleration smoke degree is reduced, and the torque characteristic of the engine in low speed is improved.
The variable section turbocharger can realize the matching with the full working condition of the engine, so that the variable section turbocharger can be applied to the engines of the pickup, the light pickup, the multifunctional vehicle and the like in a large batch; with the wide application of the variable-section supercharger, the reliability problem and the failure mode of the variable-section supercharger are more and more concerned; in the existing failure mode, when the air flow entering the volute passes through the channel formed by the nozzle vane 3, the pressure surface and the suction surface of the nozzle vane 3 cause difference in the flow velocity of the air exiting from the tail edge of the nozzle vane 3, and pressure fluctuation is generated at the air inlet front end of the turbine vane 4, so that air flow exciting force is formed.
In order to realize good flow and pressure adjustment, the number of the nozzle blades 3 arranged at the periphery of the turbine blade 4 is generally more than 10, namely, the number of the nozzle blades 3 is also more than 10 in the circumferential direction, when the turbine blade 4 rotates for one circle, each nozzle blade 3 can have more than 10 exciting force applied and unloaded, and if the control is not good, the high cycle fatigue failure mode of the turbine blade 4 can be directly caused.
The prior variable-section turbocharger mainly comprises the following defects:
when the air flow passes through the nozzle vane 3, the air flow exciting force of the air at the tail edge of the nozzle vane 3 is enhanced due to the pressure lifting and the structure of the nozzle vane 3, so that the turbine vane 4 is more easily damaged due to high-cycle fatigue, and the supercharger fails.
The opening of the nozzle vane 3 is adjusted by driving the shifting fork 6 to drive the shifting fork disc 8, the shifting fork disc 8 drives the driven shifting fork 7, and the driven shifting fork 7 drives the opening of the nozzle vane 3, because the periphery is a high-temperature environment, larger fit gaps are needed between parts in the middle transmission process, and the control precision of the opening of the nozzle vane 3 can be reduced due to the gaps.
The actuator rod 14 and the drive plate 12 are coupled in the axial direction of the supercharger by means of drive pins, requiring a large space for the reversing mechanism, requiring a large space outside the intermediate housing between the turbine housing and the compressor, and being difficult to arrange in some superchargers of specific profile requirements.
In the variable-section turbocharger, the opening of the nozzle vane 3 is limited by adopting the active shifting fork locating pin 5 and the middle shell locating pin 15 which are distributed on the middle shell, and because the processing errors of the active shifting fork locating pin hole and the middle shell locating pin are not accurately controlled, the opening deviation of different turbochargers is larger, and the consistency is difficult to ensure.
The positioning of the shifting fork disc 8 in the circumferential direction is performed in a mode that the volute is matched with the shifting fork disc matched inner hole 9, and meanwhile, a three-point or multi-point supporting structure is adopted, so that the friction contact area is reduced, the transmission efficiency is still low, and the risk of clamping stagnation still exists.
The above problems are a number of technical problems associated with conventional variable section turbochargers for mass applications at present, and are particularly evident in particular applications, such as those in which the turbine wheel and the compressor wheel are compactly arranged.
In order to solve the above problems, a variable cross-section turbocharger with low exciting force needs to be developed specifically, and products meeting specific requirements in the aspects of appearance, reliability, efficiency and the like can be produced while high cycle fatigue failure of a turbine impeller is reduced.
Disclosure of Invention
The invention aims to solve the main technical problem of providing the low-exciting-force variable-section nozzle blade and the matching device thereof, which can greatly reduce the exciting force of a turbine, improve the reliability and the transmission efficiency of products and meet the requirements of certain special products on the appearance and the reliability.
In order to solve the technical problems, the invention provides the following technical scheme:
the utility model provides a low exciting force variable cross-section nozzle blade, includes the shift fork axle, and the one end of shift fork axle is provided with the connecting axle section, and the last one end an organic whole that keeps away from the connecting axle section of shift fork is connected with nozzle blade, is provided with the subassembly of ventilating that makes things convenient for high low pressure air current to carry out the confluence on the nozzle blade.
The following is a further optimization of the above technical solution according to the present invention:
the nozzle blade is provided with a nozzle blade pressure surface and a nozzle blade suction surface, and a nozzle blade tail edge is arranged at the tail end of the nozzle blade, which is positioned between the nozzle blade pressure surface and the nozzle blade suction surface.
Further optimizing: the ventilation assembly comprises a plurality of inclined holes which are formed in the nozzle blade and are close to the tail edge of the nozzle blade, the axes of the inclined holes are obliquely distributed, and an included angle alpha 1 between the axes of the inclined holes and the horizontal plane is 35-50 degrees.
Further optimizing: the ventilation assembly comprises a stepped groove which is formed in the nozzle blade and is close to the tail edge of the nozzle blade, and one side surface of the stepped groove, which is far away from the shifting fork shaft, penetrates through the outer surface of the nozzle blade; the height L1 of the stepped groove accounts for 10% -60% of the total height L of the nozzle vane; one side of the stepped groove, which is close to the middle part of the nozzle blade, is an inclined surface arranged along the airflow direction at the tail edge of the nozzle blade; the included angle alpha 2 between the inclined surface of the stepped groove and the horizontal plane is 35 degrees to 50 degrees.
Further optimizing: the ventilation assembly comprises a chute which is arranged on the nozzle blade and is close to the tail edge of the nozzle blade, and the outer side surface of the chute penetrates through the tail edge of the nozzle blade; the chute is at least two and is distributed at intervals; the included angle alpha 3 between the central line of the chute and the horizontal plane is 35 degrees to 50 degrees.
Further optimizing: the ventilation assembly comprises space direction twisting surfaces arranged on the upper surface and the lower surface of the nozzle blade, and the two space direction twisting surfaces are symmetrically distributed.
The utility model provides a low exciting force variable cross section nozzle blade cooperation device, includes the turbine shell, and one side that the turbine shell kept away from its export is provided with the supporting disk, has offered a plurality of mounting holes for annular and interval arrangement on the supporting disk, installs the axle sleeve in the mounting hole respectively, all installs the driving fork axle of above-mentioned low exciting force variable cross section nozzle blade in each axle sleeve, and the back of supporting disk is provided with the shifting fork dish, is provided with the support bearing subassembly between shifting fork dish and the supporting disk.
Further optimizing: the connecting shaft section is fixedly provided with a driven shifting fork, and the other ends of the driven shifting forks are respectively arranged in corresponding arc-shaped grooves on the shifting fork disc; a driving shifting fork is fixedly arranged on the uppermost connecting shaft section, and one end of the driving shifting fork, which is far away from the connecting shaft section, is arranged in a corresponding arc-shaped groove on the shifting fork disc; the upper end of the driving shifting fork is in transmission connection with a driving adjusting component.
Further optimizing: the driving adjusting assembly comprises an actuator transmission rod arranged above the driving shifting fork, and one end of the actuator transmission rod is connected with an actuator; the two sides of the actuator transmission rod, which are positioned at the upper end part of the driving shifting fork, are respectively and fixedly provided with shifting fork blocks, and the two shifting fork blocks are matched with the upper end part of the driving shifting fork; limiting components used for limiting the movement limit position of the shifting fork block are respectively arranged on the outer sides of the shifting fork blocks on the supporting plates.
Further optimizing: the support bearing assembly comprises a central hole formed in the center of the shifting fork disc, a first bearing rolling way is formed in the inner surface of the central hole, a bearing inner ring body is coaxially arranged in the central hole, and the bearing inner ring body is fixedly arranged on the support disc; the outer surface of the bearing inner ring body is provided with a second bearing raceway, a bearing retainer is arranged between the second bearing raceway and the first bearing raceway, and a plurality of ball bearings are arranged on the bearing retainer.
The invention adopts the technical scheme and has the following beneficial effects:
1. according to the invention, the nozzle blade is creatively designed in a plurality of schemes, and single or a plurality of inclined holes and inclined grooves are processed on the nozzle blade, or the structures such as stepped grooves with different air outlet angles are arranged, so that high-pressure and high-temperature air passing through the pressure surface and the suction surface of the nozzle blade is exchanged with partial air flow with high and low pressure before the tail edges of the nozzle blade meet, the peak value of turbine exciting force generated when the tail edges of the nozzle blade finally enter the turbine blade is reduced, the probability of high cycle fatigue failure of the supercharger turbine is reduced, and the reliability of the turbine in use is improved.
2. The invention can adjust the positions and the number of the inclined grooves and the inclined holes according to actual requirements so as to adapt to the requirements of different engines and superchargers.
3. According to the invention, the nozzle blades are twisted to form the space direction twisted surface 19, the high-pressure airflow direction is changed after the nozzle blades pass through the space direction twisted surface 19, so that the peak value of turbine exciting force generated by entering the turbine blades is finally reduced, the high cycle fatigue failure probability of the booster turbine is reduced, and the reliability of the turbine in use is improved.
4. According to the invention, the driving shifting fork and the driven shifting fork are designed into a whole, so that the influence of a gap when the driving shifting fork is transmitted to the driven shifting fork is eliminated, and the transmission is more accurate.
5. According to the invention, the shifting fork block for controlling the opening of the nozzle blade is designed to be controlled by a linear distance, and the shifting fork block and the actuator transmission rod are welded into a whole by adopting processing guarantee, so that the opening of the nozzle blade can be accurately controlled.
6. According to the invention, the actuator transmission rod, the transmission block and the active shifting fork are arranged on the same plane, so that the space of a reversing mechanism required in the conventional variable-section turbocharger is avoided, and the problem that part of machine types cannot arrange the actuator transmission mechanism because the external space of the middle shell is small is solved.
7. According to the invention, the connection part of the shifting fork disc and the supporting disc is connected by adopting the supporting bearing assembly, and the shifting fork disc can be supported to rotate through the supporting bearing assembly, so that the transmission efficiency is higher, the required driving force is smaller, and the responsiveness is higher.
8. The invention adopts the bearing retainer to keep proper distance between the ball bearings, thereby reducing friction moment of the bearings and heat generated by friction.
The invention will be further described with reference to the drawings and examples.
Drawings
FIG. 1 is a schematic cross-sectional view of a scroll end of a variable area turbocharger of the prior art;
FIG. 2 is a schematic view of a structure of a variable cross-section turbocharger at a fork pan in the background art;
FIG. 3 is a schematic view of a structure of a variable cross-section turbocharger actuator lever in the background art;
FIG. 4 is a partial side view of an actuator drive rod of the prior art;
FIG. 5 is a schematic view showing the structure of a nozzle vane in embodiment 1 of the present invention;
FIG. 6 is a side view of a nozzle vane of example 1 of the present invention;
FIG. 7 is a schematic view showing the structure of a nozzle vane in embodiment 2 of the present invention;
FIG. 8 is a side view of a nozzle vane in example 2 of the present invention;
FIG. 9 is a schematic view showing the structure of a nozzle vane in embodiment 3 of the present invention;
FIG. 10 is a side view of a nozzle vane in example 3 of the present invention;
FIG. 11 is a schematic view showing the structure of a nozzle vane in embodiment 4 of the present invention;
FIG. 12 is a side view of a nozzle vane in example 4 of the present invention;
fig. 13 is a schematic view showing the structure of a nozzle vane mounted on a variable cross-section turbocharger in embodiment 5 of the present invention;
FIG. 14 is a cross-sectional view of the fitting device of embodiment 5 of the present invention;
fig. 15 is a schematic view showing the structure of the support bearing assembly in embodiment 5 of the present invention.
In the figure: 1-volute flow channels; 2-volute laryngeal inlet; 3-nozzle vanes; 4-turbine blades; 5-actively shifting the fork positioning pin; 6-an active shifting fork; 7-a driven shifting fork; 8-shifting fork disc; 9-matching the volute with the shifting fork disc to form an inner hole; 10-a shift rail; 11-shaft sleeve; 12-a driving plate; 13-a drive pin; 14-an actuator transmission rod; 15-middle shell locating pins; 16-inclined holes; 17-step groove; 18-chute; 19—a spatially directed twist; 20-an actuator; 21-a shifting fork block; 22-a limiting assembly; 23-a first bearing race; 24-ball bearings; 25-bearing holders; 26-bearing inner ring body; 27-a support plate; 28-nozzle vane trailing edge; 29-nozzle vane pressure face; 30-nozzle vane suction side; 31-connecting shaft sections; 32-turbine shell; 33-mounting holes.
Detailed Description
Example 1: as shown in fig. 5-6: the utility model provides a low exciting force variable cross-section nozzle vane, includes shift rail 10, the one end of shift rail 10 is provided with connecting axle section 31, the one end an organic whole that keeps away from connecting axle section 31 on the shift rail 10 is connected with nozzle vane 3, be provided with the subassembly of ventilating that makes things convenient for high low pressure air current to carry out the confluence on the nozzle vane 3.
In this embodiment 1, a reinforcing portion is provided at the connection portion between the shift rail 10 and the nozzle vane 3, and the reinforcing portion is used for improving the connection strength between the shift rail 10 and the nozzle vane 3, and improving the use effect.
The nozzle vane 3 is provided with a nozzle vane pressure surface 29 and a nozzle vane suction surface 30, and the nozzle vane pressure surface 29 and the nozzle vane suction surface 30 are symmetrically distributed.
The nozzle vane 3 is provided with a nozzle vane trailing edge 28 at the trailing end between a nozzle vane pressure surface 29 and a nozzle vane suction surface 30.
In this embodiment 1, the ventilation assembly includes an inclined hole 16 formed in the nozzle vane 3 and near the trailing edge 28 of the nozzle vane, and the axis of the inclined hole 16 is inclined.
In embodiment 1, the number of the inclined holes 16 is plural, and the plurality of inclined holes 16 are arranged at intervals in the height direction of the nozzle vane 3.
In this embodiment 1, the number of the inclined holes 16 is 3.
In this embodiment 1, the angle α1 between the axis of the inclined hole 16 and the horizontal plane is 35 ° to 50 °.
When the nozzle vane 3 works, a part of high-pressure high-temperature air flow enters a low-pressure area from a high-pressure area of the nozzle vane through the inclined hole 16, and before the air enters the turbine vane 4, the high-pressure air flow and the low-pressure air flow are converged after the nozzle vane tail edge 28, so that the peak value of turbine exciting force generated when the air finally enters the turbine vane 4 through the nozzle vane tail edge 28 is reduced, the probability of high-cycle fatigue failure of the turbocharger turbine is reduced, and the reliability of the turbine in use is improved.
Example 2: as shown in fig. 7 to 8, in this embodiment 2, the ventilation assembly includes a stepped groove 17 provided on the nozzle vane 3 at a position close to the nozzle vane trailing edge 28, and the overall height of the stepped groove 17 is smaller than the overall height of the nozzle vane 3.
In this embodiment 2, the step groove 17 is one, and a side surface of the step groove 17 away from the shift rail 10 penetrates the outer surface of the nozzle vane 3.
In this embodiment 2, the height L1 of the stepped groove 17 is 10% -60% of the total height L of the nozzle vane 3.
In embodiment 2, the side of the stepped groove 17 near the middle of the nozzle vane 3 is an inclined surface, and the inclined surface is disposed along the direction of the air flow at the nozzle vane trailing edge 28.
In the present embodiment 2, the inclined surface of the stepped groove 17 forms an angle α2 of 35 ° to 50 ° with the horizontal plane.
When the nozzle blade 3 works, the direction of partial air flow along the nozzle blade 3 can be changed through the stepped groove 17, and the partial air flow exchange with the air passing through the suction surface 30 of the nozzle blade is carried out before the tail edge 28 of the nozzle blade meets, so that the peak value of turbine exciting force generated when the air finally enters the turbine blade 4 through the tail edge 28 of the nozzle blade is reduced, the high cycle fatigue failure probability of the booster turbine is reduced, and the reliability of the turbine in use is improved.
Example 3: as shown in fig. 9 to 10, in this embodiment 3, the ventilation assembly includes a chute 18 provided on the nozzle vane 3 at a position close to the nozzle vane trailing edge 28, and an outer side surface of the chute 18 penetrates the nozzle vane trailing edge 28.
In this embodiment 3, the number of the inclined grooves 18 is at least two, and two adjacent inclined grooves 18 are arranged at intervals.
In this embodiment 3, the side of the chute 18 near the middle of the nozzle vane 3 is an inclined arc surface, and the inclined direction of the arc surface is set along the direction of the air flow at the trailing edge 28 of the nozzle vane.
In this embodiment 3, the angle α3 between the center line of the chute 18 and the horizontal plane is 35 ° to 50 °.
When the nozzle vane 3 is in operation, the air flow generated by the chute 18 and the air flow passing through the suction surface 30 of the nozzle vane are combined to form high-low pressure air flow, so that the peak value of turbine exciting force generated by the final entering of the turbine vane 4 through the tail edge 28 of the nozzle vane is reduced, the probability of high-cycle fatigue failure of the booster turbine is reduced, and the reliability of the turbine in use is improved.
Example 4: as shown in fig. 11 to 12, in this embodiment 4, the ventilation assembly includes space-direction torsion curves 19 provided on the upper and lower surfaces of the nozzle vane 3, and the two space-direction torsion curves 19 are symmetrically arranged.
By the design, when the nozzle blade 3 works, the high-pressure airflow direction can be changed after the nozzle blade 3 passes through the space direction twisted surface 19, so that the peak value of turbine exciting force generated by entering the turbine blade 4 is finally reduced, the high-cycle fatigue failure probability of the booster turbine is reduced, and the reliability of the turbine in use is improved.
In embodiment 5, as shown in fig. 13-15, the invention further provides a low exciting force variable section nozzle vane matching device, which comprises a turbine shell 32, wherein a support disc 27 is arranged on one side of the turbine shell 32 far away from an outlet of the turbine shell, a plurality of mounting holes 33 are formed in the support disc 27, the plurality of mounting holes 33 are annular and distributed at intervals, shaft sleeves 11 are respectively arranged in the mounting holes 33, fork shafts 10 of the low exciting force variable section nozzle vanes are respectively arranged in the shaft sleeves 11, a fork disc 8 is arranged on the back surface of the support disc 27, and a support bearing assembly is arranged between the fork disc 8 and the support disc 27.
In embodiment 5, a scroll flow passage 1 is provided in the turbine housing 32, and turbine blades 4 are mounted in the turbine housing 32.
In this embodiment 5, the fork shaft 10 of the low exciting force variable section nozzle vane is mounted in the corresponding mounting hole 33 on the support plate 27, and the nozzle vane 3 is located inside the turbine housing 32, and the connecting shaft section 31 on the fork shaft 10 penetrates the mounting hole 33 and extends to the outside of the support plate 27.
A plurality of arc-shaped grooves are formed in the outer surface of the shifting fork disc 8, and the arc-shaped grooves are distributed in an annular mode at intervals along the center line of the shifting fork disc 8.
The driven shifting fork 7 is fixedly installed on the connecting shaft section 31, one end, far away from the connecting shaft section 31, of the driven shifting fork 7 is an arc-shaped part, and the arc-shaped parts are respectively installed in corresponding arc-shaped grooves on the shifting fork disc 8.
The driven shifting fork 7 can be driven to swing through the cooperation of the arc-shaped groove and the arc-shaped part by rotating the shifting fork disc 8, and the driven shifting fork 7 can drive the nozzle blades 3 to swing synchronously through the connecting shaft section 31 and the shifting fork shaft 10, so that the opening degree among the plurality of nozzle blades 3 is adjusted.
It can be seen that by adjusting the axial position of the shift collar 8, it is possible to finally achieve adjustment of different opening degrees of the nozzle vanes 3, which can then be used to control the vortex end air flow.
The uppermost connecting shaft section 31 is fixedly provided with a driving shifting fork 6, one end of the driving shifting fork 6 far away from the connecting shaft section 31 is also an arc-shaped part, and the arc-shaped part is arranged in a corresponding arc-shaped groove on the shifting fork disc 8.
The upper end transmission of initiative shift fork 6 is connected with the drive adjusting component that is used for controlling initiative shift fork 6 to swing.
The driving adjusting assembly comprises an actuator transmission rod 14 arranged above the driving shifting fork 6, the actuator transmission rod 14 is horizontally arranged, and one end of the actuator transmission rod 14 is connected with an actuator 20.
In this embodiment 5, the actuator 20 may adopt a positive pressure air source to control, or may also adopt a negative pressure air source to control according to the requirement, and may also adopt an electric control signal to control, so as to realize more accurate control of the opening degree of the nozzle vane 3.
The two sides of the actuator transmission rod 14, which are positioned at the upper end part of the driving shifting fork 6, are respectively and fixedly provided with shifting fork blocks 21, and the two shifting fork blocks 21 are matched with the upper end part of the driving shifting fork 6.
In this way, the actuator 20 pushes the actuator transmission rod 14 to axially move under the control of external air pressure or an electric control signal, and at this time, the actuator transmission rod 14 drives the shifting fork block 21 welded with the actuator transmission rod into a whole to perform linear motion, and finally drives the driving shifting fork 6 to perform circumferential rotary motion, so that the shifting fork disc 8 rotates to drive the matched driven shifting fork 7 to swing.
It follows that different positions of the actuator transmission rod 14 ultimately achieve different opening degrees of the nozzle vanes 3, thereby controlling the vortex end air flow.
And limiting assemblies 22 used for limiting the movement limit position of the shifting fork block 21 are respectively arranged on the outer sides of the shifting fork block 21 on the supporting plates 27.
In this embodiment 5, the limiting component 22 is used to limit the limiting position of the shift block 21 during movement, and the limiting component 22 is a prior art, and may use a limiting groove, a limiting block, etc.
The support bearing assembly comprises a central hole formed in the center of the shifting fork disc 8, a first bearing rolling way 23 is formed in the inner surface of the central hole, a bearing inner ring body 26 is coaxially arranged in the central hole, and the bearing inner ring body 26 is fixedly mounted on a support disc 27.
A second bearing raceway is formed on the outer surface of the bearing inner ring body 26, and the second bearing raceway is correspondingly arranged with the first bearing raceway 23.
A bearing retainer 25 is installed between the second bearing race and the first bearing race 23, and a plurality of ball bearings 24 are installed on the bearing retainer 25, and the ball bearings 24 are matched with the second bearing race and the first bearing race 23.
By means of the design, the supporting bearing assembly can be assembled through the first bearing roller path 23, the bearing inner ring body 26, the second bearing roller path, the ball bearings 24 and the bearing retainer 25, and is installed between the supporting disc 27 and the shifting fork disc 8, and then the shifting fork disc 8 can be rotatably installed on the supporting disc 27, so that the assembly and the installation are convenient.
And can be used for supporting shifting fork disk 8 through this support bearing assembly and rotate, facilitate the use, and then make shifting fork disk 8 required drive power when rotating littleer, the responsiveness is higher, improves the result of use.
In embodiment 5, the ball bearings 24 are provided with the bearing holders 25 so that the ball bearings 24 are kept at a proper distance from each other, thereby reducing the friction torque of the ball bearings 24 and the heat generated by friction.
By adopting the technical scheme, the invention improves the nozzle blade 3 innovatively, and is divided into four modes: the first is to machine the angled holes 16 at the nozzle vane trailing edge 28; the second is to process the stepped groove 17 on the upper part of the tail edge 28 of the nozzle vane along the air flow direction; thirdly, the middle part of the tail edge 28 of the nozzle vane is provided with a removal chute 18; the three structures enable high-pressure and high-temperature gas passing through the nozzle blade pressure surface 29 and the nozzle blade suction surface 30 to exchange partial high-low-pressure gas flow before the nozzle blade tail edge 28 meets, reduce the peak value of turbine exciting force generated by the turbine blade 4 finally entering through the nozzle blade tail edge 28, reduce the probability of high cycle fatigue failure of the booster turbine, and improve the reliability of the turbine in use.
Fourthly, the nozzle blades 3 are twisted to form a space direction twisted surface 19, the high-pressure airflow direction after passing through the nozzle blades is changed through the space direction twisted surface 19, the peak value of turbine exciting force generated by entering the turbine blades 4 is finally reduced, the high cycle fatigue failure probability of the supercharger turbine is reduced, and the reliability of the turbine in use is improved; the turbine exciting force can be reduced by the four structures, and the reliability of the supercharger is improved.
The adjustable mechanism part of the nozzle blade 3 is subjected to structural innovation and design optimization, and the driving shifting fork 6 and the driven shifting fork 7 are designed into an integrated structure, so that the transmission is more accurate; the position of the shifting fork block 21 for controlling the opening of the nozzle blade 3 is designed to be linear distance control, and the limit component 22 is processed and ensured, so that the opening of the nozzle blade 3 can be accurately controlled; the actuator transmission rod 14, the shifting fork block 21, the driving shifting fork 6 and the driven shifting fork 7 are arranged on the same plane, so that the problem that the space is small and the arrangement is difficult is solved; the junction of shift fork dish 8 and supporting disk 27 adopts the support bearing subassembly to rotate and connects for transmission efficiency is higher, can make shift fork dish 8 less, the responsiveness of required drive force when rotating higher, improves the result of use.
Alterations, modifications, substitutions and variations of the embodiments herein will be apparent to those of ordinary skill in the art in light of the teachings of the present invention without departing from the spirit and principles of the invention.
Claims (10)
1. A low exciting force variable cross section nozzle vane is characterized in that: the air conditioner comprises a shifting fork shaft (10), wherein a connecting shaft section (31) is arranged at one end of the shifting fork shaft (10), a nozzle blade (3) is integrally connected to one end, far away from the connecting shaft section (31), of the shifting fork shaft (10), and an air ventilation assembly convenient for converging high-pressure air and low-pressure air flows is arranged on the nozzle blade (3).
2. The assembly fixture for a water injection valve according to claim 1, wherein: the nozzle vane (3) is provided with a nozzle vane pressure surface (29) and a nozzle vane suction surface (30), and a nozzle vane tail edge (28) is arranged at the tail end of the nozzle vane (3) between the nozzle vane pressure surface (29) and the nozzle vane suction surface (30).
3. The assembly fixture for the water injection valve according to claim 2, wherein: the ventilation assembly comprises a plurality of inclined holes (16) which are formed in the nozzle blade (3) and are close to the tail edge (28) of the nozzle blade, the axes of the inclined holes (16) are obliquely distributed, and an included angle alpha 1 between the axes of the inclined holes (16) and the horizontal plane is 35-50 degrees.
4. The assembly fixture for the water injection valve according to claim 2, wherein: the ventilation assembly comprises a step groove (17) which is formed in the nozzle blade (3) and is close to the tail edge (28) of the nozzle blade, and one side surface of the step groove (17) far away from the shifting fork shaft (10) penetrates through the outer surface of the nozzle blade (3); the height L1 of the stepped groove (17) accounts for 10% -60% of the total height L of the nozzle vane (3); one side of the step groove (17) close to the middle part of the nozzle blade (3) is an inclined surface arranged along the airflow direction at the tail edge (28) of the nozzle blade; the included angle alpha 2 between the inclined surface of the stepped groove (17) and the horizontal plane is 35 degrees to 50 degrees.
5. The assembly fixture for the water injection valve according to claim 2, wherein: the ventilation assembly comprises a chute (18) which is arranged on the nozzle blade (3) and is close to the tail edge (28) of the nozzle blade, and the outer side surface of the chute (18) penetrates through the tail edge (28) of the nozzle blade; the chute (18) is at least two and is arranged at intervals; the included angle alpha 3 between the central line of the chute (18) and the horizontal plane is 35 degrees to 50 degrees.
6. The assembly fixture for the water injection valve according to claim 2, wherein: the ventilation assembly comprises space direction twisting surfaces (19) arranged on the upper surface and the lower surface of the nozzle blade (3), and the two space direction twisting surfaces (19) are symmetrically distributed.
7. A low exciting force variable cross section nozzle blade cooperation device is characterized in that: the low-excitation-force variable-section nozzle vane comprises a turbine shell (32), a supporting disc (27) is arranged on one side, far away from an outlet, of the turbine shell (32), a plurality of annular mounting holes (33) which are distributed at intervals are formed in the supporting disc (27), shaft sleeves (11) are respectively arranged in the mounting holes (33), the fork shafts (10) of the low-excitation-force variable-section nozzle vanes according to any one of claims 1 to 6 are respectively arranged in the shaft sleeves (11), a fork disc (8) is arranged on the back surface of the supporting disc (27), and a supporting bearing assembly is arranged between the fork disc (8) and the supporting disc (27).
8. The low excitation force variable cross-section nozzle vane mating device of claim 7, wherein: a driven shifting fork (7) is fixedly arranged on the connecting shaft section (31), and the other ends of the driven shifting fork (7) are respectively arranged in corresponding arc-shaped grooves on the shifting fork disc (8); a driving shifting fork (6) is fixedly arranged on the uppermost connecting shaft section (31), and one end of the driving shifting fork (6) far away from the connecting shaft section (31) is arranged in a corresponding arc-shaped groove on the shifting fork disc (8); the upper end of the driving shifting fork (6) is in transmission connection with a driving adjusting component.
9. The low excitation force variable cross-section nozzle vane mating device of claim 8, wherein: the driving adjusting assembly comprises an actuator transmission rod (14) arranged above the driving shifting fork (6), and one end of the actuator transmission rod (14) is connected with an actuator (20); two sides of the actuator transmission rod (14) positioned at the upper end part of the driving shifting fork (6) are respectively and fixedly provided with shifting fork blocks (21), and the two shifting fork blocks (21) are matched with the upper end part of the driving shifting fork (6); limiting assemblies (22) used for limiting the movement limit position of the shifting fork block (21) are respectively arranged on the outer sides of the shifting fork block (21) on the supporting plates (27).
10. The low excitation force variable cross-section nozzle vane mating device of claim 9, wherein: the support bearing assembly comprises a central hole formed in the central position of the shifting fork disc (8), a first bearing rolling way (23) is formed in the inner surface of the central hole, a bearing inner ring body (26) is coaxially arranged in the central hole, and the bearing inner ring body (26) is fixedly arranged on the support disc (27); a second bearing raceway is formed on the outer surface of the bearing inner ring body (26), a bearing retainer (25) is arranged between the second bearing raceway and the first bearing raceway (23), and a plurality of ball bearings (24) are arranged on the bearing retainer (25).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311624838.3A CN117365672A (en) | 2023-11-30 | 2023-11-30 | Low-exciting-force variable-section nozzle blade and matching device thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202311624838.3A CN117365672A (en) | 2023-11-30 | 2023-11-30 | Low-exciting-force variable-section nozzle blade and matching device thereof |
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| CN117365672A true CN117365672A (en) | 2024-01-09 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111456843A (en) * | 2020-04-27 | 2020-07-28 | 湖南天雁机械有限责任公司 | Variable cross-section turbocharger |
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2023
- 2023-11-30 CN CN202311624838.3A patent/CN117365672A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111456843A (en) * | 2020-04-27 | 2020-07-28 | 湖南天雁机械有限责任公司 | Variable cross-section turbocharger |
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