CN1372069A - Propeller regulating mechanism for power changeable turbine and assembling method thereof - Google Patents
Propeller regulating mechanism for power changeable turbine and assembling method thereof Download PDFInfo
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- CN1372069A CN1372069A CN 01111984 CN01111984A CN1372069A CN 1372069 A CN1372069 A CN 1372069A CN 01111984 CN01111984 CN 01111984 CN 01111984 A CN01111984 A CN 01111984A CN 1372069 A CN1372069 A CN 1372069A
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Abstract
The present ivnention provides a blade-regulating mechanism for controlling exhaust quantity, said mechanism has a base element, said base element includes internal and external base element, the internal base element has first and second flanges, they are pressed into the external base element, and on the inner surface of internal or external base element there are several U-shaped notches which are spaced in the mode of equal angle and distributed from first flange to second flange, and when the internal base element is pressed into the external base element and the U-shaped notches are blocked, the U-shaped notches are formed into blade shaft holes for mounting blade control bar elements.
Description
The present invention relates to be used for the propeller regulating mechanism of power changeable turbine with the control air displacement.Compared with prior art parts are still less, structure is simpler for this propeller regulating mechanism, and this propeller regulating mechanism can stable operation and the life-span longer.The invention still further relates to the assembly method of this propeller regulating mechanism.
Exhaust is more cleaned, and promptly how reducing the harmful nitrogen oxide (Nox) in the exhaust and the content of particulate is an environmental problem, especially for diesel engine.The power power of diesel engine, i.e. its moment of torsion and output can improve by turbosupercharger is installed.In turbosupercharger, the turbine power that exhaust produces is used for the drive pressure mechanism of qi, and this function of calming the anger is supplied with a large amount of air inlets to motor.More air is pressed into motor the velocity of combustion of motor is increased, thereby increase its output.
Because the concrete condition of turbosupercharger is known, just no longer be introduced here; But, the device that a kind of requirement that can satisfy diesel engine also can increase its power power is the turbosupercharger that propeller regulating mechanism is arranged, and this turbosupercharger is equipped with the varying capacity blade, so that the air displacement of control motor.
As shown in Figure 7, the propeller regulating mechanism 51 of control air displacement is arranged in the turbine shroud 61 of turbosupercharger 60, and this turbosupercharger 60 is contained on the suction tude E1 and exhaust conduits E 2 that stretches into motor E.This propeller regulating mechanism 51 is contained in the outside of the turbine blade 63 of axle 62 1 ends.In Fig. 7, the 64th, at the compressor impeller of the other end of turbine shaft 62.
The propeller regulating mechanism of control air displacement is shown in Fig. 8 and 9 in the prior art.The 52nd, by the base element that short pipe fitting forms, an end of this short pipe fitting is base flange 52a.Turbine blade 63 is contained in the inside of base element 52 and coaxial with this base element.
The second flange 52b is formed on the other end base element 52, relative with an end that is formed with flange 52a.The quantity of blade axis hole 52c equals the quantity of turbine nozzle vane element 53, and this turbine nozzle vane element 53 extends to flange 52b from flange 52a.Lid 52d protection turbine nozzle vane element 53 on the flange 52a will briefly introduce this turbine nozzle vane element 53 below.
This turbine nozzle vane element 53 is varying capacity blades, and its sharf 53a can slip in the blade axis hole 52c that cooperates with sharf 53a.Turbine nozzle vane element 53 meets at right angles with respect to the surface of flange 52a and stretches out from this flange.The tilt angle on the surface of turbine nozzle vane element 53 can meet at right angles at the center line with respect to base element 53 and become between the arc round angle (arc angle) and regulate.The end of sharf 53a has turbine nozzle vane element 53, and the other end of sharf 53a is installed in by riveted joint among the boring 54a of controlling rod 54, and this controlling rod 54 will briefly introduce below.
The 54th, the controlling rod at flange 52b top.The quantity of controlling rod 54 equals the quantity of turbine nozzle vane element 53.End at controlling rod 54 has through hole 54a, and the sharf 53a of turbine nozzle vane element 53 passes base element 52 by this through hole 54a.On another controlling rod 54 the other ends, relative with the turbine nozzle vane element 53 surfaces of living in surfaces protruding 54b is arranged, this projection 54b cooperates with a hole 55a of land 55, and this land 55 will briefly introduce below.
The tip of the axis riveted joint among the hole 54a of controlling rod 54 is promptly inserted in the riveted joint of the end of the sharf 53a of turbine nozzle vane element 53, and therefore, this turbine nozzle vane element 53 and controlling rod 54 form parts.Like this, turbine nozzle vane element 53 is connected by base element 52 with controlling rod 54.Because the riveted joint of the end of sharf 53a, the motion of controlling rod 54 will change the angle direction on turbine nozzle vane element 53 surfaces.
The 55th, land.The central circular shaped section of land 55 cooperates with the outer surface of base element 52.Eccentric opening 55a is arranged on the circular arc of this circular portion, and the protruding 54b of controlling rod 54 cooperates with this eccentric opening 55a.This land also has attachment portion 55b at its outer peripheral portion, and this attachment portion 55b cooperates with the driver element.
The propeller regulating mechanism 51 of the control air displacement of aforementioned structure is driven by the driver (not shown) that is connected with the attachment portion 55b of land 55.When land 55 turns over given angle of rotation, the protruding 54b rotation of controlling rod 54, the other end of the controlling rod 54 of stator blade axle 53a also rotates.Like this, sharf 53a rotates as axle, and the angle of turbine nozzle vane element 53 is changed.The propeller regulating mechanism 51 of Qu Donging can be regulated the air displacement of turbosupercharger 60 by this way, thus the performance of energy optimization motor.
Shown in Fig. 8 and 9, the propeller regulating mechanism 51 of control air displacement need be with the blade axis hole 52c of accurate dimension brill in base element 52 in the prior art, and this blade axis hole 52c is used to install the sharf 53a of turbine nozzle vane element 53.In the manufacture process of propeller regulating mechanism 51, must very carefully form this hole 52c.Also have, because sharf 53a must closely cooperate with blade axis hole 52c, therefore, the particulate that is bonded in its lip-deep exhaust will make insertion axle and the fusion of blade axis hole 52c surface, thereby to adverse effect is arranged working life.
The sharf 53a that controlling rod 54 is arranged in the propeller regulating mechanism 51 of prior art and be riveted together with this controlling rod 54.This needs a plurality of parts, for example sharf 53a (turbine nozzle vane element 53) and controlling rod 54, and this had both increased number of spare parts, had also increased installation step.As noted earlier, these parts also must carry out high accuracy mechanical processing.Assurance is contained in turbine nozzle vane element 53 with tram (being correct angle) also needs very high precision on the controlling rod 54.
In the propeller regulating mechanism 51 of prior art, between the hole 55a of land 55 and the protruding 54b of controlling rod 54 same problem is arranged also.
In the prior art, the control air displacement is so that the propeller regulating mechanism that can use under the various states in turbosupercharger need carry out high accuracy mechanical processing, and this has increased its required during fabrication man-hour and cost.In addition, it has a lot of parts, and the complex structure that this makes it has increased manufacturing time, has reduced manufacturing efficiency and has increased cost.
The present invention is in order to address the above problem.The purpose of this invention is to provide a kind of propeller regulating mechanism of controlling air displacement, the number of components of this propeller regulating mechanism still less, design is simpler, and its can stable operation and good serviceability is arranged.
In order to realize these purposes, propeller regulating mechanism of the present invention has following major character.In the propeller regulating mechanism of prior art, the hole of base element and land all is that boring forms, and the present invention adopts the U-shaped recess, thereby omits the boring step that forms through hole.In the mechanism of the control air displacement of prior art, the parts of adjusting vane and controlling rod comprise a plurality of parts, and the present invention adopts single parts, so that reduce the number of part.In the mechanism of the control air displacement of prior art, the insertion axle that inserts in the blade controlling rod element is linear, and the diameter of insertion passage of the present invention diminishes along its length direction, so that reduce to make the required machining accuracy of axle.By selecting part or all of these improved procedures for use, MANUFACTURER can reduce required number of spare parts, simplifies mechanical structure, improves its working stability and working life, and can improve the assembly method of this propeller regulating mechanism.
The propeller regulating mechanism that the application is disclosed to be used to control air displacement comprises: one has the base element of short tube shape, and this base element has first flange on the outer surface of discharge directions, in the inboard of discharge directions second flange is arranged; Be positioned at a plurality of blades on every side of base element, these blade adjustments air displacemenies; Land on second flange of base element, the inner circumference limit of this land cooperates by this way with the outer periphery of base element, and promptly this land can rotate freely; And a plurality of blade controlling rod elements that link to each other with land with a plurality of blades, these blade controlling rod elements pass the blade axis hole in the base element.
There is following difference structure characteristic in this mechanism.Base element and outer frame element in base element comprises, should first and second flanges be arranged interior base element, should be pressed in this outer frame element by interior base element, and a plurality of from first flange to second flange, equal angles U-shaped recesses are at interval arranged on the internal surface of interior base element or outer frame element, like this, when interior base element is pressed into the outer frame element so that when can free rotation mode stopping up the U-shaped recess with blade controlling rod element, this U-shaped recess forms the blade axis hole that blade controlling rod element is installed.In assembly method of the present invention, also identical with above-mentioned feature with the feature of prior art difference.
When interior pedestal was pressed in the outer frame like this, the part of each recess was blocked, and therefore, this recess plays the effect of blade axis hole.In other words, when there is recess in the outside inboard or interior base element of outer frame element, do not need perforation step.And, need still less with the accurately machined zone of counterbore cutter head, therefore, the work of making this mechanism is simpler.
Blade and blade controlling rod element form a single piece.In the practical structures, it comprises: be positioned at the blade element of first flange top, each blade element comprises the blade of its Surface Vertical in first ledge surface; And controlling rod, each controlling rod comprises: sharf, and this sharf extends to second flange from blade element, and engages in the recess; With the connector that this sharf links to each other, this connector is parallel to the surface of second flange; And projection, this projection links to each other with this connector and extends perpendicular to the surface of second flange.This blade and controlling rod form a single piece.
By making blade element and controlling rod form single parts, we can reduce number of spare parts, have reduced the quantity of installation step simultaneously.In addition, we also do not need to determine the correct angle between the surface of controlling rod and blade element, and this has reduced required man-hour.
Land has U-shaped otch or recess at its whole periphery, this otch of bump bonds or the recess of blade controlling rod element.Compare with the method that forms the hole on land, the present invention has good thermal distortion intensity, and is easy to make.
The intermediate portion of the sharf of blade controlling rod element has a small, and the diameter of this small can reduce sharf and the surface area that the U-shaped recess contacts like this less than the diameter of sharf end, prevents that this sharf is stuck in the U-shaped recess.The intermediate portion of sharf is diminished can not make contacting still less of sharf and recessed surfaces, this will not need to carry out fine finishing, shorten manufacturing time thus.This can also prevent that part is stuck.
Fig. 1 is the schematic representation of the propeller regulating mechanism of power changeable turbine pressurized machine of the present invention; Figure 1A is the view of seeing from land, and Figure 1B is the enlarged view of blade controlling rod;
Fig. 2 is the sectional drawing along Fig. 1 center line B-B of the propeller regulating mechanism of power changeable turbine pressurized machine of the present invention;
Figure 3 shows that the base element of the mechanism of adjusting air displacement of the present invention.Fig. 3 A is the view of seeing from second flange, and Fig. 3 B is the sectional drawing of C-C along the line, and expression is inserted interior base element in the outer frame element;
Figure 4 shows that the actuator blade connecting element of the mechanism of adjusting vane angle of the present invention; Fig. 4 A is the view of seeing from projection, and Fig. 4 B is the view of seeing from the side of Fig. 4 A;
Figure 5 shows that the land of propeller regulating mechanism of the present invention.Fig. 5 A is the view of seeing from the top, and Fig. 5 B is the sectional drawing of D-D along the line;
Figure 6 shows that the land of the propeller regulating mechanism of another preferred embodiment of the present invention; Fig. 6 A is the view of seeing from the top, and Fig. 6 B is the sectional drawing of E-E along the line;
Fig. 7 represents in the prior art, the position of propeller regulating mechanism in the motor that the power changeable turbine pressurized machine is housed;
Fig. 8 is the schematic representation of propeller regulating mechanism of the power changeable turbine pressurized machine of prior art; Fig. 8 A is the view of seeing from land, and Fig. 8 B is the sectional drawing along the line A-A among the 8A;
Fig. 9 is the schematic representation of propeller regulating mechanism of the power changeable turbine pressurized machine of prior art; Fig. 9 A is the enlarged view of expression variable-vane and controlling rod, and Fig. 9 B is the blade protecting cover of seeing from blade side.
In these accompanying drawings, the 1st, propeller regulating mechanism, the 2nd, base element, 2A is interior base element, and 2B is the outer frame element, and 2a is first flange, 2b is second flange, and 2c is a recess, the 3rd, and blade controlling rod element, 3A is a blade, and 3B is a controlling rod, and 3a is a sharf, 3b is a connector, and 3c is a projection, and 3d is the part of dwindling, the 4th, land, 4a are U-shaped otch or recess, and 4b is a drive part.
In this part, we will introduce several preferred embodiments of the present invention with reference to the accompanying drawings.The shape of the parts of being introduced, relative position and others are not clearly to limit of the present invention in these embodiments, and scope of the present invention is not limited to illustrated parts, and illustrated parts only is in order to clearly demonstrate.
Introduce a preferred embodiment of the propeller regulating mechanism of control air displacement of the present invention below with reference to Fig. 1 to 6.
Fig. 1 and 2 is depicted as the structural representation of the propeller regulating mechanism of control power changeable turbine pressurized machine air displacement of the present invention.Figure 3 shows that the base element of the mechanism of control air displacement of the present invention.Figure 4 shows that blade controlling rod element in the mechanism of control air displacement of the present invention, that be used for the adjusting vane angle.Fig. 5 and 6 is depicted as the land in the mechanism of control air displacement of the present invention.
Among Fig. 1 to Fig. 6, the 1st, the propeller regulating mechanism of control air displacement of the present invention, it has the blade of control air displacement, and this exhaust makes the turbine blade rotation.This mechanism is loaded in the unshowned turbosupercharger, and its structure will be introduced below.
The 2nd, base element, it is shaped as short tubular.As shown in Figure 2, base element 2A and outer frame element 2B in this base element 2 comprises, base element 2A forms the inside part of base element in this, and interior base element 2A is pressed in this outer frame element 2B.
As shown in Figure 3, when interior base element 2A was pressed into outer frame element 2B, the opening end of the recess 2c on the outer frame element 2B was covered by the outer surface of interior base element 2A.Therefore, after interior base element 2A and outer frame element 2B assembled, recess 2c formed the blade axis hole.Such mechanical structure does not need to carry out drilling operating.
As shown in Figure 4, the 3rd, blade controlling rod element.End at it is blade 3A, and the other end is the controlling rod 3B that changes the angle on blade 3A surface.These two ends form as single parts.In blade controlling rod element 3, the blade 3A that forms an end of blade controlling rod element places the top of flange 2a, and like this, blade surface is perpendicular to this flange.The angle of blade surface is passed through controlling rod 3B and rotation change.
In blade controlling rod element 3, comprise at the controlling rod 3B of an end of this element: sharf 3a, this sharf 3a pack among the recess 2c and extend to flange 2b from flange 2a; Connector 3b, this connector 3b extends in flange 2b from the end parts parallel of sharf 3a; And protruding 3c, this projection 3c extends perpendicular to flange 2b from the end of connector 3b.
At the middle part of sharf 3a is the part 3d that dwindles, and the diameter of this part 3d is less than the diameter of shaft end.The part 3d that dwindles has reduced axle and the contacted area of contact of recess 2c, and can prevent that this axle is stuck in the recess.This variable-vane controlling rod 3 is formed with sharf 3a, connector 3b and the protruding 3c among blade 3A and the controlling rod 3B, and they all form as an one piece.
The 4th, land, its inner circumference limit can free rotation mode cooperate with this land with the outward edge of interior base element 2A.For example, this land 4 has the U-shaped otch 4a that extends to opposite side from a side in its whole outer periphery as shown in Figure 5, and protruding 3c inserts among this U-shaped otch 4a.
For another preferred embodiment, in land shown in Figure 64, insert the U-shaped recess 4a of protruding 3c, punching is made by exerting pressure at the back side of this dish.There is drive part 4b the outer periphery of land 4, and this drive part 4b cooperates with the driver (not shown), so that make land 4 rotations.
In land 4 shown in Figure 5, porose on the part that forms drive part 4b, rather than otch 4a.But, when drive part 4b is placed on the part of the dish that does not have otch 4a, otch can be arranged in the whole outer periphery of land 4.
The 5th, the protecting cover of blade 3A.(see figure 2) protecting cover 5 angled shapes.Be contained on the flange 2a by connecting hardware 5a, and between protecting cover and flange spacing arranged, this spacing is less times greater than the width of blade 3a.
When the structure of the propeller regulating mechanism of control turbosupercharger air displacement as mentioned above the time, because its assembly method, so its working procedure is as follows.As drive part 4b during by driver (not shown) rotary driving several angle, land 4 will rotate same angle.
When land 4 rotations, the protruding 3c on the controlling rod 3B of blade controlling rod element 3 inserts among the recess 4a of land 4, therefore also rotation.Connector 3b also will rotate, and make sharf 3a around its rotation.When sharf 3a around its when rotation axle, will change the angle on the blade 3A surface in the blade controlling rod element 3.Air displacement in this will regulate and flow among the base element 2A.
Below, we will be according to the propeller regulating mechanism 1 of the control air displacement of the embodiment of the invention, introduces effect of the present invention with the difference of prior art mechanism 51 shown in Fig. 8 and 9.
(1) in the propeller regulating mechanism 51 of the control air displacement of prior art, blade axis hole 52c be adopt diameter be slightly less than turbine nozzle vane element 53 sharf 53a diameter drill bit and on base element 52, form.Like this, the mechanism 51 of the control air displacement of prior art needs the quantity of the blade axis hole 52c of brill to equate with the quantity of turbine nozzle vane element 53, and this needs considerable man-hour.Because the surface of the sharf 53a that cooperates with hole 52c needs high-precision processing, this in addition need more man-hour.
On the contrary, the propeller regulating mechanism 1 of control air displacement of the present invention has the recess 2c that extends to flange 2b from flange 2a on the outer frame element 2B of base element 2.When interior base element 2A was pressed into outer frame element 2B, the opening end of recess 2c was stopped up by the outer surface of interior base element 2A.Therefore, this recess can play the effect of blade axis hole, and it is at the sharf 3a of three-point support blade controlling rod element 3.
Therefore, in the propeller regulating mechanism 1 of control air displacement of the present invention, recess 2c can be by making blank pulling eye or cold forging.As previously mentioned, when interior base element 2A was pressed into outer frame element 2B, recess 2c can play the effect of blade axis hole, and it is at the three-point support sharf.This has reduced the man-hour of processing, and the possibility that makes sharf 3a be stuck in the blade axis hole that is made of interior base element 2A and recess 2c reduces.
(2) in the propeller regulating mechanism 51 of the control air displacement of prior art, the sharf 53a of turbine nozzle vane element 53 is linear, they and controlling rod 54 riveted joints.Like this, in the propeller regulating mechanism 51 of the control air displacement of prior art, (turbine nozzle vane element 53) sharf 53a and controlling rod need a plurality of parts.This had both increased number of spare parts, had also increased the quantity of installation step.And as mentioned above, the processing of axle needs very highi degree of accuracy, has increased man-hour and the cost made.
On the contrary, when the blade controlling rod element 3 of the propeller regulating mechanism 1 of making control air displacement of the present invention, each sharf 3a, connector 3b in blade 3A and controlling rod 3B and protruding 3c can forge and form a single-piece.Like this, the required number of spare parts of the propeller regulating mechanism of control air displacement of the present invention 1 still less, thereby reduced installation step.And the work of the setting angle of lever for adjusting oil 3B and blade 3A also can be omitted, and this has significantly reduced required man-hour.
(3) in the propeller regulating mechanism 51 of the control air displacement of prior art, the hole of land 55 is real holes, and the protruding 54b of controlling rod 54 packs in this hole.Like this, the mechanism 51 of the control air displacement of prior art need have the hole 55a with the equal number of turbine nozzle vane element 53, and this needs considerable machining period.Because the surface of protruding 54b and hole 55a contacts with each other, and need carry out high-precision fine finishing, therefore, they need produce more man-hour.
On the contrary, the propeller regulating mechanism 1 of control air displacement of the present invention has the equidistant recess 4a around land 4, and the protruding 3c of the controlling rod 3B of blade controlling rod element 3 inserts this recess 4a.Because the protruding 3c in the mechanism 1 of control air displacement of the present invention is fitted among the recess 4a of land 4, rather than in the real boring of packing into, so these parts heat-resistant deforming more, be easier to machining simultaneously.
Therefore, the propeller regulating mechanism 1 of control air displacement of the present invention compared with prior art, the part that needs still less, structure is simpler, and required fine finishing step is still less.Therefore can be with less time, higher productivity and lower cost production.
The present invention is not limited to described embodiment, but various versions can be arranged.For example, in the above-described embodiments, on the inner periphery of base element 2B, interior base element 2A is pressed into the mounting portion to recess 2c outside.But, recess 2c also can be on the outer periphery of interior base element 2A, and base element 2A is pressed into inner periphery in this does not have among the outer frame element 2B of recess 2c.This can obtain the work effect identical with aforementioned structure.
As previously mentioned, the propeller regulating mechanism of control air displacement of the present invention has along being equal to apart from the U-shaped recess of arranging on the outer periphery of the inner periphery of mounting portion or interior base element.When interior base element was pressed into this mounting portion, this recess played the effect of blade axis hole.Can save the required man-hour of holing like this, and need accurately machined zone littler.Therefore, process easier finishing, and the jammed possibility of part that controlling rod inserts in the recess is very little.
In the propeller regulating mechanism of control air displacement of the present invention, comprise the whole single parts of making of blade of blade-section, axle, connector and projection, this blade-section is as variable-vane, and the surface with the Surface Vertical of first flange is arranged.So just reduced the quantity of number of spare parts and installation step.Also saved the required man-hour of relative angle of adjusting vane and controlling rod.
In the propeller regulating mechanism of control air displacement of the present invention, the U-shaped recess is arranged on the outer periphery of land, this U-shaped recess extends to the opposite side surface from a side surface of land, in this U-shaped recess of the bump bonds of the controlling rod in the blade controlling rod element.This has saved the man-hour of boring on dish, and the product that generates is not easy to occur thermal distortion, and is easy to processing.
In the propeller regulating mechanism of control air displacement of the present invention, the intermediate portion of the sharf of each blade controlling rod element passes recess, and this intermediate portion diminishes.This has reduced the surface area that axle contacts with recess, has shortened the required time of Finishing Parts Machining, and prevents that two parts from producing stuck phenomenon.
Claims (6)
1. one kind is used for power changeable turbine to control the propeller regulating mechanism of air displacement, comprising:
One has the base element of short tube shape, and this base element has first flange on the outer surface of discharge directions, in the inboard of discharge directions second flange is arranged;
Be positioned at a plurality of blades on every side of described base element, these blade adjustments air displacemenies;
Land on described second flange of described base element, the inner circumference limit of this land and the outer periphery of described base element can free rotation mode cooperate with this land;
With a plurality of blade controlling rod elements that described a plurality of blades link to each other with described land, these blade controlling rod elements pass the blade axis hole in the described base element;
Wherein, base element and outer frame element in described base element comprises, base element has described first and second flanges in this, and described interior base element 2A is pressed in this outer frame element; And
In described on the internal surface of base element or outer frame element, a plurality of from first flange to second flange, equal angles U-shaped recesses are at interval arranged, like this, base element is pressed into described outer frame element so that when can free rotation mode stopping up described U-shaped recess with described blade controlling rod element in described, and described U-shaped recess forms the described blade axis hole that described blade controlling rod element is installed.
2. propeller regulating mechanism according to claim 1, the external peripheral surface of wherein said interior base element and the central circular shaped section of described land can free rotation mode cooperate with described land.
3. propeller regulating mechanism according to claim 1, wherein said blade and described blade controlling rod element form a single piece.
4. propeller regulating mechanism according to claim 1, wherein said land has U-shaped otch or recess on its whole outer periphery, and the bump bonds of described blade controlling rod element is gone into this otch or recess.
5. propeller regulating mechanism according to claim 1, the intermediate portion of the sharf of wherein said blade controlling rod element has a small, the diameter of this small is less than the diameter of described sharf end, can reduce sharf and the surface area that described U-shaped recess contacts like this, prevent that described sharf is stuck in the described U-shaped recess.
6. assembly method of propeller regulating mechanism that is used for power changeable turbine with the control air displacement, described propeller regulating mechanism comprises:
One has the base element of short tube shape, and this base element has first flange on the outer surface of discharge directions, in the inboard of discharge directions second flange is arranged;
Be positioned at a plurality of blades on every side of described base element, these blade adjustments air displacemenies;
Land on described second flange of described base element, the inner circumference limit of this land and the outer periphery of described base element can free rotation mode cooperate with this land;
With a plurality of blade controlling rod elements that described a plurality of blades link to each other with described land, these blade controlling rod elements pass the blade axis hole in the described base element;
Described assembly method may further comprise the steps:
Described base element is provided, base element and outer frame element in this base element comprises, base element has first and second flanges in this, and described interior base element 2A is pressed in this outer frame element;
A plurality of from first flange to second flange, equal angles U-shaped recesses at interval are provided on the internal surface of base element or outer frame element in described, and like this, described U-shaped recess forms the described blade axis hole that described blade controlling rod element is installed; And
Base element in described is pressed into described outer frame element, so that can free rotation mode stop up described U-shaped recess with described blade controlling rod element.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01111984 CN1292149C (en) | 2001-02-27 | 2001-02-27 | Propeller regulating mechanism for power changeable turbine and assembling method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01111984 CN1292149C (en) | 2001-02-27 | 2001-02-27 | Propeller regulating mechanism for power changeable turbine and assembling method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1372069A true CN1372069A (en) | 2002-10-02 |
| CN1292149C CN1292149C (en) | 2006-12-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 01111984 Expired - Lifetime CN1292149C (en) | 2001-02-27 | 2001-02-27 | Propeller regulating mechanism for power changeable turbine and assembling method thereof |
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| CN (1) | CN1292149C (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1854469B (en) * | 2005-04-29 | 2010-09-01 | 斯奈克玛公司 | Control bar for vane declination angle of turbine |
| CN107208539A (en) * | 2015-02-24 | 2017-09-26 | 三菱重工业株式会社 | Variable nozzle mechanism and variable capacity type exhaust turbine supercharger |
| CN113614345A (en) * | 2019-03-28 | 2021-11-05 | 三菱重工发动机和增压器株式会社 | Nozzle device and exhaust turbocharger |
-
2001
- 2001-02-27 CN CN 01111984 patent/CN1292149C/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1854469B (en) * | 2005-04-29 | 2010-09-01 | 斯奈克玛公司 | Control bar for vane declination angle of turbine |
| CN107208539A (en) * | 2015-02-24 | 2017-09-26 | 三菱重工业株式会社 | Variable nozzle mechanism and variable capacity type exhaust turbine supercharger |
| US10851706B2 (en) | 2015-02-24 | 2020-12-01 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Variable nozzle mechanism and variable displacement type exhaust turbocharger |
| CN113614345A (en) * | 2019-03-28 | 2021-11-05 | 三菱重工发动机和增压器株式会社 | Nozzle device and exhaust turbocharger |
| CN113614345B (en) * | 2019-03-28 | 2023-10-13 | 三菱重工发动机和增压器株式会社 | Nozzle device and exhaust turbocharger |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1292149C (en) | 2006-12-27 |
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