WO2016199600A1 - 可変容量型過給機 - Google Patents
可変容量型過給機 Download PDFInfo
- Publication number
- WO2016199600A1 WO2016199600A1 PCT/JP2016/065797 JP2016065797W WO2016199600A1 WO 2016199600 A1 WO2016199600 A1 WO 2016199600A1 JP 2016065797 W JP2016065797 W JP 2016065797W WO 2016199600 A1 WO2016199600 A1 WO 2016199600A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- drive ring
- turbine
- support member
- ring
- compressor
- Prior art date
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- 238000006073 displacement reaction Methods 0.000 claims description 25
- 230000002093 peripheral effect Effects 0.000 claims description 20
- 230000001105 regulatory effect Effects 0.000 claims description 7
- 230000007246 mechanism Effects 0.000 description 7
- 238000004519 manufacturing process Methods 0.000 description 6
- 238000002485 combustion reaction Methods 0.000 description 5
- 239000002184 metal Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
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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
- 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
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
- F02B37/12—Control of the pumps
- F02B37/24—Control of the pumps by using pumps or turbines with adjustable guide vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
- F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/128—Nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/90—Variable geometry
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/50—Kinematic linkage, i.e. transmission of position
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Definitions
- the present disclosure relates to a variable displacement feeder.
- variable displacement turbocharger includes a nozzle drive mechanism for driving a nozzle of a turbine.
- a nozzle drive mechanism for driving a nozzle of a turbine.
- a plurality of roller pins are arranged in the circumferential direction and fixed to a nozzle mount.
- a rotatable roller is attached to each of the roller pins, and each roller is in contact with the inner peripheral edge of the drive ring.
- the drive ring is a member for transmitting the driving force to the nozzle, and is supported by the plurality of rollers described above.
- variable displacement supercharger the drive ring is supported by a relatively complicated component group such as installing a plurality of roller pins and a plurality of rollers on the nozzle mount.
- the present disclosure describes a variable displacement turbocharger that simplifies the structure of the mechanism that drives the nozzle and improves manufacturability.
- a variable displacement supercharger includes a turbine wheel, a turbine housing that forms a scroll flow passage disposed around the turbine wheel, and a gas inflow from the scroll flow passage to the turbine wheel.
- a turbine having a variable nozzle unit including a plurality of movable nozzle vanes disposed around a turbine wheel in a road, and a turbine wheel connected to the turbine wheel via a rotation shaft and rotating about the same rotation axis as the turbine wheel
- a variable nozzle unit which is supported by a turbine housing and rotatably supports a plurality of nozzle vanes, and rotates around a rotation axis with respect to the unit main body Drive ring for transmitting the driving force to multiple nozzle vanes, Fixed to the unit body and rotatable the drive ring A ring support member for supporting the ring support member, the ring support member being formed of one member, a radial direction restricting portion for restricting the radial movement of the drive ring, and a rotational axis of the drive ring to the
- variable displacement turbocharger of the present disclosure the structure of the mechanism for driving the nozzle can be simplified, and the ease of manufacture can be improved.
- FIG. 4 It is a sectional view of a variable displacement turbocharger according to an embodiment. It is an exploded perspective view of a variable nozzle unit.
- A) is a top view of a drive ring support member
- (b) is a top view of a drive ring. It is a perspective view which shows the state which attached the drive ring to the drive ring support member.
- (A) is sectional drawing containing the hook part in FIG. 4,
- (b) is sectional drawing containing a projection part,
- (c) is the figure which looked at the vicinity of a projection from the radial direction outer side.
- a variable displacement supercharger includes a turbine wheel, a turbine housing that forms a scroll flow passage disposed around the turbine wheel, and a gas inflow from the scroll flow passage to the turbine wheel.
- a turbine having a variable nozzle unit including a plurality of movable nozzle vanes disposed around a turbine wheel in a road, and a turbine wheel connected to the turbine wheel via a rotation shaft and rotating about the same rotation axis as the turbine wheel
- Drive ring for transmitting the driving force to multiple nozzle vanes, Fixed to the unit body and rotatable the drive ring A ring support member for supporting the ring support member, the ring support member being formed of one member, a radial direction restricting portion for restricting the radial movement of the drive ring, and a rotational axis of the drive ring to the compressor
- the drive ring is supported by the ring support member formed of one member, and the movement of the drive ring in the radial direction, the compressor side, and the turbine side is restricted.
- the structure of the mechanism for driving the nozzle is simplified and manufactured by realizing the functions of the radial movement restriction necessary for supporting the drive ring, the movement restriction to the compressor side, and the movement restriction to the turbine side with a single member. The ease can be improved.
- the ring support member includes a plurality of hooks disposed on a circumference centered on the rotation axis and engaged with an edge on the inner peripheral side of the drive ring, and the hooks are of the drive ring As having a radial direction restricting portion positioned radially inward of an edge portion on the inner circumferential side, and a compressor side restricting portion extending radially outward from the radial direction restricting portion and facing an end face of the drive ring on the compressor side It is also good.
- the turbine-side regulating portion may be provided on a circumference centered on the rotation axis, and may have a plurality of protrusions projecting toward the compressor and facing the end face of the drive ring on the turbine side.
- the hook portion and the turbine side regulating portion may be provided at mutually different positions in the circumferential direction.
- variable displacement turbocharger According to the present disclosure, an embodiment of a variable displacement turbocharger according to the present disclosure will be described with reference to the drawings.
- the characteristic of a component may be exaggerated and described, the dimensional ratio of each part on a drawing does not necessarily correspond with a real thing.
- variable displacement supercharger 1 shown in FIG. 1 is applied to, for example, an internal combustion engine of a ship or a vehicle.
- the variable displacement supercharger 1 includes a turbine 2 and a compressor 3.
- the turbine 2 includes a turbine housing 4 and a turbine wheel 6 housed in the turbine housing 4.
- the turbine housing 4 has a scroll passage 16 extending circumferentially around the turbine impeller 6.
- the compressor 3 includes a compressor housing 5 and a compressor wheel 7 housed in the compressor housing 5.
- the compressor housing 5 has a scroll passage 17 extending circumferentially around the compressor wheel 7.
- the turbine wheel 6 is provided at one end of the rotating shaft 14, and the compressor wheel 7 is provided at the other end of the rotating shaft 14.
- a bearing housing 13 is provided between the turbine housing 4 and the compressor housing 5.
- the rotating shaft 14 is rotatably supported by the bearing housing 13 via a bearing 15, and the rotating shaft 14, the turbine wheel 6 and the compressor wheel 7 rotate around the rotation axis H as an integral rotating body 12.
- the turbine housing 4 is provided with an exhaust gas inlet (not shown) and an exhaust gas outlet 10. Exhaust gas exhausted from an internal combustion engine (not shown) flows into the turbine housing 4 through an exhaust gas inlet. Then, the exhaust gas flows into the turbine wheel 6 through the scroll passage 16 to rotate the turbine wheel 6. Thereafter, the exhaust gas flows out of the turbine housing 4 through the exhaust gas outlet 10.
- the compressor housing 5 is provided with a suction port 9 and a discharge port (not shown). As described above, when the turbine wheel 6 rotates, the compressor wheel 7 rotates via the rotation shaft 14. The rotating compressor wheel 7 sucks the external air through the suction port 9, compresses the air, and discharges the air from the discharge port through the scroll passage 17. The compressed air discharged from the discharge port is supplied to the aforementioned internal combustion engine.
- the turbine 2 is a variable displacement turbine.
- a movable nozzle vane 23 is provided in the gas inflow path 21 connecting the scroll flow path 16 and the turbine wheel 6.
- a plurality of nozzle vanes 23 are disposed circumferentially about the rotation axis H. Each nozzle vane 23 pivots about an axis parallel to the axis of rotation H.
- the turbine 2 includes a variable nozzle unit 25 as a drive mechanism for rotating the nozzle vanes 23 as described above.
- the variable nozzle unit 25 is fitted inside the turbine housing 4 and is fixed by being sandwiched between the turbine housing 4 and the bearing housing 13.
- variable nozzle unit 25 when simply referring to “axial direction”, “radial direction”, “circumferential direction”, etc., it means the rotational axis H direction, rotational radial direction, rotational circumferential direction of the turbine wheel 6, respectively. .
- upstream when saying "upstream”, “downstream” etc., it shall mean the upstream of the exhaust gas in the scroll flow path 16, and the downstream.
- the side near the turbine 2 left side in FIG. 2
- the side near the compressor 3 (right side in FIG. 2) may be simply referred to as the “compressor side”.
- the variable nozzle unit 25 includes the plurality of (11 in the illustrated example) nozzle vanes 23, a first nozzle ring 31, and a second nozzle ring 32.
- the first nozzle ring 31 and the second nozzle ring 32 are positioned sandwiching the nozzle vanes 23 in the axial direction.
- Each of the first nozzle ring 31 and the second nozzle ring 32 has a ring shape centered on the rotation axis H, and is disposed so as to surround the turbine wheel 6 in the circumferential direction.
- the region sandwiched between the first nozzle ring 31 and the second nozzle ring 32 constitutes the aforementioned gas inflow path 21.
- the second nozzle ring 32 faces the scroll passage 16 (see FIG.
- each nozzle vane 23 is rotatably inserted in the bearing hole 31a of the first nozzle ring 31, and the first nozzle ring 31 supports the nozzle vanes 23 in a cantilever manner.
- the nozzle vanes 23 are arranged at equal intervals on the circumference in the example of the drawing, it is not essential to arrange the nozzle vanes 23 at equal intervals.
- An annular plate-like support ring 41 is fixed to the compressor side of the first nozzle ring 31, and a drive ring support member 43 in a ring shape is fixed to the compressor side of the support ring 41.
- Each of the first nozzle ring 31, the second nozzle ring 32, the support ring 41, and the drive ring support member 43 is provided with a plurality of (three in the illustrated example) pin holes 35 a.
- the first nozzle ring 31, the second nozzle ring 32, the support ring 41, and the drive ring support member 43 are connected to one another by the connection pin 35 being inserted into each of the pin holes 35a.
- the support ring 41 and the drive ring support member 43 are co-caged with the first nozzle ring 31 by a portion of the connection pin 35 on the compressor side.
- two flanges for positioning the first nozzle ring 31 and the second nozzle ring 32 are provided at a portion of the connection pin 35 on the turbine side.
- the dimensional accuracy in the axial direction of the gas inflow path 21 is secured by manufacturing the dimension between the two ridges with high accuracy.
- variable nozzle unit 25 is fixed to the turbine housing 4 and the bearing housing 13 by the peripheral portion of the support ring 41 being axially sandwiched between the turbine housing 4 and the bearing housing 13. That is, the entire variable nozzle unit 25 is held by the turbine housing 4 and the bearing housing 13 by the peripheral portion of the support ring 41 being axially sandwiched between the turbine housing 4 and the bearing housing 13.
- the drive ring 28 is a member that transmits the driving force to the nozzle vanes 23 input from the outside, and is formed of, for example, a metal material as a single member.
- the drive ring 28 has a ring shape extending circumferentially around the rotation axis H, and rotates around the rotation axis H in response to an external driving force.
- the levers 29 are respectively attached to the rotation shafts 23 a of the nozzle vanes 23 and arranged at equal intervals on the circumference inside the drive ring 28.
- Grooves 28 a are formed at equal intervals at positions corresponding to the respective levers 29 on the inner peripheral side of the drive ring 28.
- each lever 29 is engaged with each groove 28 a of the drive ring 28, and the other end of each lever 29 is fixed to the pivot shaft 23 a of each nozzle vane 23.
- the drive ring 28 pivots around the rotation axis H.
- the levers 29 engaged with the grooves 28a rotate, and the nozzle vanes 23 rotate via the rotation shaft 23a.
- One input groove 28b is formed on the inner peripheral side of the drive ring 28, and the input groove 28b is disposed between a pair of grooves 28a and 28a.
- the driving force from the outside to the driving ring 28 described above is input as an external force in the circumferential direction with respect to the input groove 28 b.
- variable nozzle unit 25 the portion consisting of the first nozzle ring 31, the second nozzle ring 32, the support ring 41, and the connecting pin 35 is fixed to the turbine housing 4 so that the plurality of nozzle vanes 23 can rotate.
- a unit main body 51 for pivotally supporting is configured. That is, the unit body 51 is supported by the turbine housing 4 and rotatably supports the plurality of nozzle vanes 23.
- the drive ring support member 43 constitutes a ring support member fixed to the unit main body 51 and rotatably supporting the drive ring 28.
- the method of fixing the drive ring support member 43 to the unit main body 51 is not limited to the configuration in which the first nozzle ring 31 is co-caged with the support ring 41, and various fixing methods may be adopted. it can.
- FIG. 3A is a plan view of the drive ring support member 43 viewed from the side of the compressor 3 with a line of sight parallel to the rotation axis H.
- FIG. 3B is a plan view of the drive ring 28 as viewed from the compressor 3 with a line of sight parallel to the rotation axis H.
- FIG. 4 is a perspective view showing the drive ring 28 attached to the drive ring support member 43.
- FIG. 5A is a cross-sectional view in FIG. 4 that includes hooks 45 and is parallel to the radial direction.
- FIG. 5 (b) is a cross-sectional view taken on a cross section parallel to the radial direction including the projection 47 a in FIG. 4.
- FIG. 5C is a view of the vicinity of the protrusion 47 a viewed from the outer side in the radial direction.
- the drive ring support member 43 has a flat plate ring-shaped member main body 42, a plurality of hooks 45 rising from the outer peripheral part of the member main body 42 to the compressor side, and radially outward from the outer peripheral part of the member main body 42 And a plurality of turbine side receiving parts 47 (third parts) extending.
- the drive ring support member 43 is formed of one member, and is manufactured by, for example, pressing.
- the diameter of the outer periphery of the member main body 42 is slightly smaller than the diameter of the inner periphery of the drive ring.
- the drive ring support member 43 and the drive ring 28 are, for example, members made of metal.
- the hook portion 45 and the turbine side receiving portion 47 are respectively disposed at positions corresponding to portions where the groove 28 a of the drive ring 28 does not exist and the input groove 28 b does not exist. Further, a plurality of hook portions 45 and a plurality of turbine side receiving portions 47 are provided at positions which do not overlap each other on the circumference centering on the rotation axis H.
- a plurality of (six in the illustrated example) hooks 45 are arranged on the circumference of the rotation axis H and are hooked on the inner peripheral edge of the drive ring 28.
- the hook portion 45 has a proximal end portion 45a (first portion) axially extending from the outer peripheral edge of the member main portion 42, and a distal end portion 45b bent from the proximal end portion 45a and extending radially outward. And the second part).
- the hook 45 functions as a radial direction restricting part for restricting the movement of the drive ring 28 in the radial direction. It has it.
- the drive ring support member 43 and the drive ring 28 have the rotation axis H horizontal with, for example, the arrow K direction shown in FIG. It is arranged in the posture to do.
- the hook portion 45 may be arranged as follows.
- a part (three out of six in the example of the drawing) of the hook portion 45 is disposed within the range of 180 ° above the rotation axis H (within the range above the one-dot chain line J in the drawing) It may be done.
- each hook portion 45 is located radially inward of the inner peripheral edge of the drive ring 28 and faces the inner peripheral surface 28 d of the drive ring 28.
- the proximal end portion 45 a may contact the inner peripheral surface 28 d of the drive ring 28.
- the plurality of proximal end portions 45 a circumferentially arranged function as a radial direction restricting portion that restricts the movement of the drive ring 28 in the radial direction.
- the diameter of the imaginary circle passing through the proximal end portions 45a is slightly smaller than the diameter of the imaginary circle passing through the inner peripheral surface 28d of the drive ring 28. Therefore, slight rattling occurs in the radial direction between the drive ring support member 43 and the drive ring 28.
- each hook portion 45 extends radially outward beyond the position of the inner peripheral surface 28d of the drive ring 28, and faces the end surface 28c on the compressor side.
- the tip end portion 45b may be in contact with the end face 28c on the compressor side. According to this configuration, the tip end portion 45 b functions as a compressor-side regulating portion that regulates movement of the drive ring 28 in the direction of the rotation axis H toward the compressor.
- a plurality of (three in the illustrated example) turbine side receiving portions 47 are arranged on a circumference centered on the rotation axis H.
- the turbine side receiving portion 47 extends radially outward beyond the position of the inner peripheral surface 28 d of the drive ring 28.
- Each of the turbine side receiving parts 47 has a projection 47 a provided at the tip end thereof and protruding toward the compressor side.
- the protrusion 47 a is formed by being bent so that the tip of the turbine side receiving portion 47 is pushed out to the compressor side.
- Each protrusion 47 a faces the end face 28 t on the turbine side of the drive ring 28.
- Each protrusion 47 a may be in contact with the end face 28 t on the turbine side of the drive ring 28.
- the turbine side receiving portion 47 functions as a turbine side restricting portion that restricts the movement of the drive ring 28 in the direction of the rotation axis H toward the turbine side. Further, the gap in the axial direction between the tip end portion 45 b and the projection 47 a is formed slightly wider than the thickness of the drive ring 28. For this reason, a slight rattling in the axial direction occurs between the drive ring support member 43 and the drive ring 28.
- the drive ring support member 43 supports the drive ring 28 so as to restrict movement of the drive ring 28 in the radial direction, the compressor side, and the turbine side. Further, in the drive ring support member 43, a portion for restricting the movement of the drive ring 28 in the circumferential direction is not formed. For this reason, the drive ring 28 is rotatable around the rotation axis H while being supported by the drive ring support member 43.
- the arrangement interval of the hook portions 45 in the circumferential direction corresponds to the arrangement interval of the grooves 28a. That is, when the drive ring 28 is rotated about the rotation axis H direction by a predetermined amount with respect to the drive ring support member 43, the circumferential phase of all the hook portions 45 corresponds to any corresponding groove 28a (11 in the illustrated example). Of the six, it corresponds to the circumferential phase of six). Further, the diameter of the imaginary circle passing through the tip of each hook 45 is slightly smaller than the diameter of the imaginary circle passing through the deepest part of the groove 28a. Further, the circumferential width of the tip end portion 45b is slightly smaller than the circumferential width of the groove 28a.
- the size of the distal end side portion 45b of the hook portion 45 is slightly smaller than the size of the groove 28a.
- the hook portion 45, and the turbine side receiving portion 47 are provided at mutually different positions in the circumferential direction. According to this configuration, for example, by pressing a flat metal plate, the drive ring support member 43 can be relatively easily manufactured with one member.
- variable nozzle unit 25 of the variable displacement supercharger 1 the drive ring 28 is supported by the drive ring support member 43 formed of one member, and movement of the drive ring 28 in the radial direction, compressor side, and turbine side is It is regulated.
- the functions of the radial movement restriction, the movement restriction to the compressor side, and the movement restriction to the turbine side necessary for supporting the drive ring 28 are realized by one member. Therefore, the structure of the variable nozzle unit 25 can be simplified and the ease of manufacture can be improved. As a result, the manufacturing cost of the variable displacement turbocharger 1 can be reduced.
- the present invention can be carried out in various forms including various modifications and improvements based on the knowledge of those skilled in the art, including the embodiments described above. Moreover, it is also possible to constitute a modification using the technical matters described in the above-described embodiment.
- the configurations of the respective embodiments may be appropriately combined and used. For example, in the embodiment, an example is described in which the number of hooks 45 disposed in the drive ring support member 43 is larger than the number of turbine side receiving parts 47, but the turbine side receiving parts 47 and the hook parts 45 may have the same number. Alternatively, the number of the turbine side receiving portions 47 may be larger than that of the hook portions 45.
- a plurality of hook portions 45 are disposed within a range of 180 ° above the rotation axis H in the attitude in a state mounted on an internal combustion engine such as a vehicle.
- the phase of the circumferential direction which arranges and the turbine side receiving part 47, respectively may be arbitrary.
- the single hook portion 45 may be disposed within a range of 180 ° above the rotation axis H.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Supercharger (AREA)
- Control Of Turbines (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
2 タービン
3 コンプレッサ
4 タービンハウジング
6 タービン翼車
7 コンプレッサ翼車
14 回転軸
16 スクロール流路
21 ガス流入路
23 ノズルベーン
25 可変ノズルユニット
28 駆動リング
28c コンプレッサ側の端面
28t タービン側の端面
43 駆動リングサポート部材(リング支持部材)
45 フック部
45a 基端側部分(径方向規制部)
45b 先端側部分(コンプレッサ側規制部)
47 タービン側受け部(タービン側規制部)
47a 突起部
51 ユニット本体部
H 回転軸線
Claims (6)
- タービン翼車と、前記タービン翼車の周囲に配置されるスクロール流路を形成するタービンハウジングと、前記スクロール流路から前記タービン翼車へのガス流入路において前記タービン翼車の周囲に配置された複数の可動のノズルベーンを含む可変ノズルユニットと、を有するタービンと、
前記タービン翼車に回転軸を介して接続され前記タービン翼車と同一の回転軸線周りに回転するコンプレッサ翼車を有するコンプレッサと、を備え、
前記可変ノズルユニットは、
前記タービンハウジングに保持され複数の前記ノズルベーンを回動可能に軸支するユニット本体部と、
前記ユニット本体部に対して前記回転軸線周りに回動し複数の前記ノズルベーンへの駆動力を伝達する駆動リングと、
前記ユニット本体部に固定されると共に前記駆動リングを回動可能に支持するリング支持部材と、を有し、
前記リング支持部材は、
一部材で形成されており、
前記駆動リングの径方向への移動を規制する径方向規制部と、
前記駆動リングの前記コンプレッサ側への前記回転軸線方向の移動を規制するコンプレッサ側規制部と、
前記駆動リングの前記タービン側への前記回転軸線方向の移動を規制するタービン側規制部と、を有する、可変容量型過給機。 - 前記リング支持部材は、
前記回転軸線を中心とする円周上に配置され前記駆動リングの内周側の縁部に係合する複数のフック部を備え、
前記フック部は、
前記駆動リングの前記内周側の縁部よりも径方向内側に位置する前記径方向規制部と、
前記径方向規制部から径方向外側に延び前記駆動リングの前記コンプレッサ側の端面に対面する前記コンプレッサ側規制部と、を有する請求項1に記載の可変容量型過給機。 - 前記タービン側規制部は、
前記回転軸線を中心とする円周上に配置され前記コンプレッサ側に突出し前記駆動リングの前記タービン側の端面に対面する複数の突起部を有する請求項1又は2に記載の可変容量型過給機。 - 前記フック部と前記タービン側規制部とは、周方向における互いに異なる位置に設けられている請求項2に記載の可変容量型過給機。
- タービン翼車と、前記タービン翼車の周囲に配置された可動ノズルベーンと、前記可動ノズルベーンに駆動力を伝達する駆動リングと、前記駆動リングを回動可能に保持するリング支持部材と、を備える可変容量型過給機であって、
前記リング支持部材が、
前記駆動リングの内周縁面と接触可能な第1の部分と、
前記駆動リングの軸方向の一方側の端面と接触可能な第2の部分と、
前記駆動リングの前記内周縁面よりも径方向外側まで延伸し、前記駆動リングの前記軸方向の他方側の端面と接触可能な第3の部分と、を備え、
前記駆動リングは、前記周縁面に設けられた溝部を備え、
前記リング支持部材に保持された前記駆動リングを前記リング支持部材に対して所定量回転させたときに、前記リング支持部材の前記第1の部分及び前記第2の部分が、前記駆動リングの前記溝部を前記軸方向に通過可能な状態になる、可変容量型過給機。 - 前記リング支持部材は、屈曲されたフック部を備え、
前記フック部のうち、前記屈曲された部分よりも前記軸方向の前記他方側の部分が前記第1の部分であり、
前記フック部のうち、前記屈曲された部分よりも前記軸方向の前記一方側の部分が前記第2の部分である、請求項5の可変容量型過給機。
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