WO2016031017A1 - 膨張タービン及びターボチャージャ - Google Patents
膨張タービン及びターボチャージャ Download PDFInfo
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- WO2016031017A1 WO2016031017A1 PCT/JP2014/072571 JP2014072571W WO2016031017A1 WO 2016031017 A1 WO2016031017 A1 WO 2016031017A1 JP 2014072571 W JP2014072571 W JP 2014072571W WO 2016031017 A1 WO2016031017 A1 WO 2016031017A1
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- WIPO (PCT)
- Prior art keywords
- turbine
- wall surface
- working fluid
- expansion turbine
- moving blade
- Prior art date
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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
- F01D9/026—Scrolls for radial machines or engines
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- 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
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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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
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- 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
- F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
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- 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
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- 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 an expansion turbine having a variable nozzle and a turbocharger provided with the expansion turbine.
- variable displacement turbocharger having a variable nozzle on the inlet side of the expansion turbine, and the variable displacement turbocharger can adjust the flow rate of the working fluid by adjusting the opening of the variable nozzle.
- the variable displacement turbocharger can adjust the flow rate of the working fluid by adjusting the opening of the variable nozzle.
- the variable capacity turbocharger as shown in FIG. 8, when the opening degree of the variable nozzle is small, the turbine efficiency is greatly reduced compared to the peak point (the nozzle opening is near the middle opening area).
- the turbine efficiency when the nozzle opening is in the small opening region greatly affects the response performance. Therefore, there is a need to improve turbine efficiency in a small opening range.
- the incidence angle of the variable nozzle (the difference between the inflow angle of the working fluid flowing into the variable nozzle and the leading edge blade angle of the variable nozzle). is there. Therefore, in order to reduce the incidence angle, it is conceivable to narrow the scroll portion of the turbine housing (make the scroll portion smaller) in accordance with the leading edge blade angle of the variable nozzle in the small opening range.
- the scroll portion is narrowed, the incidence angle increases when the nozzle opening is in the large opening range, flow separation occurs on the wing surface of the variable nozzle, the actual flow area decreases, and the working fluid flow rate (maximum There is a problem that the flow rate) decreases.
- Patent Document 1 discloses the shroud wall surface of the turbine housing facing the tip of the moving blade.
- a turbine in which an annular guide portion (guide surface) is formed on the inlet side of the moving blade at an angle toward the rear side of the turbine wheel with respect to the radial direction of the turbine.
- the guide portion by forming the guide portion, the working fluid having flowed into the moving blade is moved to the back side of the turbine wheel, and the excitation force by the wake of the variable nozzle is near the blade tip edge. The action is suppressed, and the swing of the moving blade is suppressed.
- the clearance flow through the gap is suppressed.
- At least one embodiment of the present invention suppresses the decrease in turbine efficiency when the variable nozzle is in the small opening range, and at the same time, the flow rate of the working fluid when the variable nozzle is in the large opening range. It is an object of the present invention to provide an expansion turbine and a turbocharger capable of securing and simultaneously achieving desired blade performance and suppressing reduction in turbine efficiency.
- An expansion turbine is an expansion turbine for recovering power from energy possessed by a working fluid, the turbine housing including a scroll portion into which the working fluid is introduced; A plurality of circumferentially spaced-apart circumferential directions of the expansion turbine in the turbine housing, and configured to be rotatable about a rotation axis so as to change a flow passage area of the working fluid passing through the scroll portion.
- a variable nozzle, and a plurality of moving blades located downstream of the variable nozzle, and a turbine wheel rotatably provided in the turbine housing The turbine housing has a first wall surface including a shroud portion facing the tip of the moving blade, and a second wall surface facing the first wall surface across the flow path of the working fluid,
- the blade height on the outlet side of the variable nozzle is greater than the blade height on the inlet side of the moving blade
- the shroud portion protrudes toward the second wall surface so that the flow channel height of the working fluid narrows toward the downstream side on the downstream side of the outlet of the variable nozzle and on the upstream side of the inlet of the moving blade
- the protrusion amount of the protrusion is set such that the tip end of the protrusion does not protrude beyond the tip at the inlet of the moving blade to the second wall surface side.
- the throat area in the working fluid flow path between the variable nozzles can be increased. . Therefore, when the variable nozzle is in the wide opening range, the flow rate (maximum flow rate) of the working fluid flowing into the moving blades can be sufficiently secured.
- the working fluid flowing into the moving blade has a strong swirling component because the nozzle opening is small, while the flow velocity component directed inward in the radial direction is small. Therefore, in the conventional expansion turbine, in the small opening degree region of the variable nozzle, the working fluid is easily pressed to the shroud side (the first wall side) by the centrifugal force caused by the turning component of the working fluid flowing into the moving blade. .
- the working fluid is pressed to the shroud wall surface side, the flow of the working fluid is biased to the shroud side at the blade outlet, the flow velocity is large on the shroud side, and the flow velocity is reduced on the hub side (second wall surface).
- the working fluid spreads so as to eliminate the flow velocity imbalance on the downstream side of the moving blade, and mixing loss is likely to occur.
- the configuration (1) since the projecting portion is provided, the working fluid flows along the projecting portion so as to be brought closer to the second wall side (hub side), and the first wall side (shroud side) The partial flow of the working fluid is suppressed. As a result, uneven flow at the blade exit is alleviated, and mixing loss is reduced, thereby improving turbine efficiency. Therefore, in addition to the merit of securing the maximum flow rate in the wide opening range of the variable nozzle described above, the configuration (1) can also enjoy the merit of improving the turbine efficiency when the variable nozzle is in the small opening range.
- the protrusion amount of the protrusion is set so that the tip end of the protrusion does not protrude to the second wall side beyond the tip of the inlet of the moving blade. Since the working fluid flows into a wide range in the blade height direction, it is possible to suppress a reduction in the effective flow path area at the blade inlet due to the contraction effect by the protrusions. Therefore, desired blade performance can be easily obtained, and high turbine efficiency can be maintained.
- the expansion turbine is a radial turbine in which the working fluid flows into the inlet of the moving blade along a radial direction of the expansion turbine,
- the origin of the axial position of the root of the inlet of the moving blade, when the axial position of the tip in the inlet of the moving blade and the X t, the axial position X p of the tip of the projecting portion is 0 ⁇
- the relation of X t ⁇ X p is satisfied.
- the amount of protrusion of the protrusion is set such that the tip end of the protrusion does not protrude toward the hub side of the moving blade. Therefore, since it is possible to suppress a decrease in the flow passage area at the blade inlet, desired blade performance can be easily obtained, and the turbine efficiency can be maintained high.
- the first wall surface has a tapered surface inclined with respect to the radial direction, and the projecting portion is formed by the tapered surface.
- the angle formed by the tapered surface with respect to the axial direction of the expansion turbine is 40 degrees or less.
- the pressure difference between the pressure surface and the suction surface of the variable nozzle can be reduced, the clearance flow can be suppressed, and the turbine efficiency can be improved.
- the ratio of loss due to the clearance flow to the entire flow loss is high, so the effect by the configuration (4) (effect of improving the turbine efficiency by suppressing the clearance flow) is large.
- the expansion turbine in any of the above configurations (1) to (4), which is configured to be driven by exhaust gas from an internal combustion engine, A compressor driven by the expansion turbine and configured to compress intake air to the internal combustion engine.
- the turbocharger in the turbocharger, it is possible to suppress a decrease in turbine efficiency when the variable nozzle is in the small opening range and secure a flow rate of the working fluid when the variable nozzle is in the large opening range. Can.
- desired blade performance can be easily obtained, and high turbine efficiency can be maintained.
- the decrease in turbine efficiency when the variable nozzle is in the small opening range is suppressed, and the flow rate of the working fluid when the variable nozzle is in the large opening range is secured. It is possible to suppress the decrease in blade performance and to suppress the decrease in turbine efficiency.
- FIG. 3 is a cross-sectional view showing a structure around a variable nozzle and a moving blade of an expansion turbine according to an embodiment.
- FIG. 3 is a cross-sectional view showing a structure around a variable nozzle and a moving blade of an expansion turbine according to an embodiment.
- It is an explanatory view showing the flow of the operation fluid in the expansion turbine concerning one embodiment.
- It is a partially expanded sectional view of the conventional expansion turbine.
- FIG. 6 is a diagram showing the relationship between the flow rate of working fluid of the expansion turbine and the turbine efficiency.
- expressions that indicate that things such as “identical”, “equal” and “homogeneous” are equal states not only represent strictly equal states, but also have tolerances or differences with which the same function can be obtained. It also represents the existing state.
- expressions representing shapes such as quadrilateral shapes and cylindrical shapes not only represent shapes such as rectangular shapes and cylindrical shapes in a geometrically strict sense, but also uneven portions and chamfers within the range where the same effect can be obtained. The shape including a part etc. shall also be expressed.
- the expressions “comprising”, “having”, “having”, “including” or “having” one component are not exclusive expressions excluding the presence of other components.
- turbocharger to which the present invention is applied is not particularly limited as long as it is a supercharger for forcibly feeding intake air into an internal combustion engine, and may be, for example, an automotive turbocharger or a marine turbo charger. It may be a charger.
- FIG. 1 is a diagram showing an entire configuration of a turbocharger according to an embodiment.
- FIG. 2 is a cross-sectional view showing a detailed structure of an exhaust turbine of a turbocharger according to an embodiment.
- the turbocharger 1 shown in FIG. 1 is a turbocharger for a vehicle, and is mounted on an engine 6 for a vehicle.
- the turbocharger 1 is composed of an exhaust turbine 1a, a bearing stand 1b and a compressor 1c.
- the exhaust turbine 1a is constituted by an expansion turbine 10A or an expansion turbine 10B described in detail later.
- the exhaust turbine 1a has a turbine housing 2a, the bearing stand 1b has a bearing housing 2b, and the compressor 1c has a compressor housing 2c.
- a central shaft 3 is provided along the axial direction of the turbocharger 1, and the central shaft 3 is rotatably supported by bearings (not shown).
- the turbine wheel 4 is fixed to one end of the central shaft 3 located on the turbine housing 2 a side, and the compressor wheel 5 is fixed to the other end of the central shaft 3 located on the compressor housing 2 c side.
- An exhaust pipe 7 is connected to the exhaust port 6a of the automobile engine 6, and the other end of the exhaust pipe 7 is connected to the inlet casing 2d of the turbine housing 2a.
- the air supply pipe 8 is connected to the outlet casing 2g of the compressor housing 2c, and the other end of the air supply pipe 8 is connected to the air supply port 6b of the automobile engine 6.
- Exhaust gas e discharged from the exhaust port 6a passes through the exhaust pipe 7 and flows tangentially into the scroll portion of the turbine housing 2a as a working fluid, and after rotating the turbine wheel 4, flows out from the outlet opening 2e.
- the rotation of the turbine wheel 4 is transmitted to the compressor wheel 5 via the central shaft 3, and the rotation of the compressor wheel 5 sucks air a from the inlet opening 2f of the compressor housing 2c.
- the air a sucked from the inlet opening 2 f is compressed by the compressor wheel 5 and discharged from the outlet casing 2 g of the compressor housing 2 c to the air supply pipe 8.
- the high pressure air discharged to the air supply pipe 8 is cooled by the intercooler 9 and then supplied to the combustion chamber (not shown) of the automobile engine 6 from the air supply port 6b.
- the exhaust turbine (expansion turbine) 1a of the turbocharger 1 is driven by only the exhaust gas, but in the other embodiments, the exhaust gas is used as a main drive source.
- the motor may be used as an auxiliary drive source.
- the turbine housing 2 a of the exhaust turbine 1 a and the bearing housing 2 b are coupled by a connector 16.
- the lubricating oil r is supplied from the lubricating oil passage 22 to the bearing 20 provided on the bearing housing 2 b and rotatably supporting the central shaft 3.
- a compressor 2c (see FIG. 1) is provided adjacent to the bearing housing 2b on the opposite side to the exhaust turbine 1a.
- a turbine wheel 4 is fixed to a turbine side end of a central shaft 3 provided in the housing along the axial direction of the turbocharger 1.
- the turbine wheel 4 includes a hub 26 fixed to the central shaft 3 and a plurality of moving blades 28 radially fixed to the outer surface (hub surface 26 a) of the hub 26 in the circumferential direction.
- a scroll portion 30 into which exhaust gas e is introduced as a working fluid is formed, and a spiral shaped space s into which the exhaust gas e is introduced is formed inside the scroll portion 30.
- the turbine housing 2 a has an outer shell 12 that defines the outer shape of the turbine housing 2 a, a nozzle plate 32 provided near the downstream end of the space s, and a nozzle mount 34 provided opposite to the nozzle plate 32.
- a flow passage f communicating with the space s is formed between the nozzle plate 32 and the nozzle mount 34.
- a plurality of variable nozzles 36 are disposed in the flow path f in the circumferential direction of the central axis 3 (the circumferential direction of the exhaust turbine 1 a), and the plurality of variable nozzles 36 are disposed around the moving blades 28 at intervals.
- a pivot shaft 38 is integrally connected to each of the plurality of variable nozzles 36, and the pivot shaft 38 of each variable nozzle 36 is formed on the back side of the nozzle mount 34 from a through hole formed in the nozzle mount 34. It projects into the space.
- each pivot shaft 38 is connected to an actuator (not shown) provided outside the bearing housing 2b via a synchronization mechanism 40 and a conductive shaft (not shown).
- the actuator By operating the actuator, the plurality of variable nozzles 36 can be synchronously rotated about the rotational shaft 38.
- the plurality of variable nozzles 36 By rotating the plurality of variable nozzles 36 synchronously, when the exhaust gas e that has passed through the space s passes through the flow path f and flows into the moving blade 28, the flow path area of the flow path f is changed. Can.
- a part of the nozzle plate 32 constitutes a shroud wall surface 32 a that covers the tip 28 a of the moving blade 28.
- the wall surface of the nozzle plate 32 of the turbine housing 2a constitutes a first wall surface including the shroud wall surface 32a, and the wall surface of the nozzle mount 34 of the turbine housing 2a facing the nozzle plate 32 constitutes a second wall surface.
- the first wall surface and the second wall surface of the turbine housing 2a will be described in detail later.
- the flow path f is formed in a direction orthogonal to the axis C of the central axis 3, that is, along the radial direction of the exhaust turbine 1a, and the exhaust turbine 1a constitutes a radial turbine.
- the exhaust gas e flowing into the flow path f reaches the moving blades 28 to rotate the turbine wheel 4 and the central axis 3, and then flows out from the outlet opening 42 formed on the axis C of the central axis 3.
- FIG. 3 is a cross-sectional view showing the structure around the variable nozzle and the moving blade of the expansion turbine according to one embodiment.
- FIG. 4 is a cross-sectional view showing a structure around a variable nozzle and a moving blade of an expansion turbine according to another embodiment.
- the turbine housing 13 of the expansion turbine 10 (10A, 10B) includes a shroud portion (shroud wall surface 32a) facing the tip 28a of the moving blade 28.
- a wall surface 50 and a second wall surface 52 opposed to the first wall surface 50 across the flow path f of the working fluid w are provided.
- the blade height at the outlet of the variable nozzle 36 is formed larger than the blade height at the inlet of the moving blade 28.
- first wall surface 50 on the downstream side of the outlet of the variable nozzle 36 and on the upstream side of the inlet of the moving blade 28 is configured so that the flow path height of the flow path f narrows toward the downstream side of the working fluid.
- Protrusions 44 and 54 that protrude toward the wall surface 52 are formed.
- the protrusions 44, 54 have planar tapered surfaces 44 a, 54 a that are inclined with respect to the axial direction (the direction of the axis C) of the expansion turbine 10.
- the amount of protrusion of the protrusions 44 and 54 is set so that the tip end of the protrusion 44 does not protrude beyond the tip 28 a at the inlet (front edge 28 b) of the moving blade 28 toward the second wall surface 52. That is, the axial position of the blade base at the leading edge 28 b of the moving blade 28 (the intersection of the leading edge 28 b and the hub surface 26 a of the hub 26 of the turbine wheel 24) is the origin O, and the tip at the leading edge 28 b of the moving blade 28 when the axial position of 28a was X t, the axial position X p of the tip of the protruding portion 44 satisfies the 0 ⁇ X t ⁇ X p.
- the tapered surfaces 44a, 54a of the protrusions 44, 54 are inclined at an angle of 40 degrees or less with respect to the axial direction.
- the ratio to the distance R R )) satisfies the condition of 1.4 ⁇ R S / R R.
- the outlet end of the variable nozzle 36 and the projecting portions 44 and 54 (a tapered surface at the maximum opening degree are allowed to allow expansion due to thermal expansion of the variable nozzle 36).
- An expansion margin h is left between 44a and 54a).
- the flow rate of the working fluid w flowing from the space s into the flow path f is adjusted by adjusting the opening degree of the variable nozzle 36.
- the working fluid flowing in the region near the first wall surface 50 is, as shown by the broken line in FIG. 5, on the outer surfaces (taper surfaces 44a, 54a) of the protrusions 44, 54.
- the second wall surface 52 as it flows along in this state, it flows through the flow path between the moving blades 28 relatively uniformly in the blade height direction of the moving blades 28 and rotates the turbine wheel 24, and then the outlet It flows out to the opening 42.
- the tips of the protrusions 44 and 54 are set so as not to protrude beyond the tip 28 a at the inlet of the moving blade 28 toward the second wall 52 side. That is, the axial position of the moving blade root at the leading edge 28b of the moving blade 28 (the intersection of the leading edge 28b and the hub surface 26a of the hub 26 of the turbine wheel) is taken as the origin O, and the axial direction of the tip 28b (direction of the axis C) ) when the position was defined as X t, the axial position X p of the distal end of the protrusion 44, 54, 0 ⁇ since satisfies X t ⁇ X p, dynamic due to contraction flow effect by protrusion 44, 54 It is possible to suppress a decrease in the effective flow area at the inlet of the wing 28. Therefore, desired blade performance can be easily obtained, and high turbine efficiency can be maintained.
- the working fluid w is directed to the second wall 52 side (hub side) along the tapered surfaces 44a and 54a at the inlet of the moving blade 28 It can be sufficiently brought close to the first wall surface 50. Therefore, uneven flow of the working fluid w to the first wall surface 50 side (shroud wall 32a side) is suppressed. By this, the flow velocity distribution at the blade exit is made uniform, and the mixing loss is suppressed, whereby the turbine efficiency is improved.
- the radial distance R S from the axis C to the axis of the pivot shaft 38, the ratio between the distance R R from the axis C to the inlet tip surface 28b is, because it is 1.4 ⁇ R S / R R
- the clearance flow can be suppressed and the turbine efficiency can be improved. In the small opening region, in particular, the effect of improving the turbine efficiency by suppressing the clearance flow in the entire flow loss is large.
- the outlet side blade height of the variable nozzle 36 by setting the outlet side blade height of the variable nozzle 36 to be larger than the inlet side blade height of the moving blade 28, the throat area in the flow path f of the working fluid w between the adjacent variable nozzles 36 can be obtained. It can be increased. Therefore, when the variable nozzle 36 is in the wide opening range, the flow rate (maximum flow rate) of the working fluid w flowing into the moving blade 28 can be sufficiently secured. Further, the working fluid w is moved to the second wall surface 52 side (hub side) by the projecting portions 44 and 54, and the deviation flow to the first wall surface 50 side (shroud side) is suppressed.
- the nonuniformity of the flow velocity distribution (radial distribution of the flow velocity V) in the radial direction of the expansion turbine 10 (10A, 10B) at the outlet of the moving blade 28 is alleviated, and the mixing loss is reduced. Therefore, even when the variable nozzle 36 is in the small opening range, the turbine efficiency can be maintained high. Thus, the turbine efficiency can be improved when the variable nozzle 36 is in the small opening range without depending on the shape of the scroll portion, and the working fluid w flowing into the moving blade 28 when the variable nozzle 36 is in the large opening range Flow rate (maximum flow rate) can be secured.
- FIGS. 6 and 7 show a conventional expansion turbine, corresponding to FIGS. 3 to 5 showing the present embodiment.
- the variable nozzle 36 when the variable nozzle 36 is in the small opening range, the working fluid w flows into the moving blade 28 with a strong swirling component, and the radial flow velocity component of the working fluid w is small.
- the outlet side blade height of the variable nozzle 36 and the inlet side blade height of the moving blade 28 are equal, and the tapered surface 44a (54a) and the protrusion 44 (54) are not formed. Therefore, as shown in FIG.
- the working fluid w includes the wall surface of the shroud wall 32a by the centrifugal force caused by the turning component of the working fluid w flowing into the moving blade 28. It is easy to be pressed to the 1st wall 50 side. Therefore, when the working fluid w is pressed to the first wall surface 50 side, the flow of the working fluid w is deviated to the first wall surface 50 side at the outlet of the moving blade 28, and the flow velocity V is large on the first wall surface 50 side. The flow velocity decreases on the wall surface 52 side. As a result, the working fluid w spreads on the downstream side of the moving blade 28 so as to eliminate the flow velocity imbalance, and mixing loss tends to occur.
- the embodiment described above is an example in which the present invention is applied to a radial turbine, but the application target of the present invention is not limited to a radial turbine, and is applied to, for example, a mixed flow turbine and a turbocharger having the mixed flow turbine. it can.
- the decrease in turbine efficiency when the variable nozzle is in the small opening range is suppressed, and the flow rate of the working fluid when the variable nozzle is in the large opening range is secured. It is possible to realize an expansion turbine capable of suppressing the decrease in blade performance and suppressing the decrease in turbine efficiency.
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Abstract
Description
しかし、可変容量ターボチャージャの特性として、図8に示すように、可変ノズルの開度が小さいとき、タービン効率は、ピーク点(ノズル開度が中開度域付近)と比べて大きく低下する。ノズル開度が小開度域のときのタービン効率は、レスポンス性能に大きく影響する。このため、小開度域でタービン効率を向上させることが求められている。
一方、スクロール部を絞ると、ノズル開度が大開度域のときのインシデンス角が大きくなり、可変ノズルの翼面で流れの剥離が生じ、実流路面積が低下し、作動流体の流量(最大流量)が低下してしまうという問題がある。
このように、タービンハウジングのスクロール部の形状の工夫だけで、可変ノズルの小開度域におけるタービン効率向上と、可変ノズルの大開度域における最大流量の確保と、を両立することは容易ではない。そこで、スクロール部の形状変更以外の手法も活用することで、これら二つの要求を満たすことが望まれる。
特許文献1に記載のタービンでは、前記ガイド部の形成により、動翼に流入した作動流体をタービンホイールの背面側へ寄せ、可変ノズルの後流(ウェイク)による励振力が動翼先端縁付近に作用することを抑制し、動翼の振れが抑制される。また、前記ガイド部によって動翼とシュラウド壁面との間の隙間を塞ぐことで、該隙間を介したクリアランスフローが抑制されるようになっている。
前記タービンハウジングは、前記動翼のチップに対向するシュラウド部を含む第1壁面と、前記作動流体の流路を挟んで前記第1壁面に対向する第2壁面とを有し、
前記可変ノズルの出口側の翼高さは前記動翼の入口側の翼高さより大きく、
前記シュラウド部は、前記可変ノズルの出口の下流側かつ前記動翼の入口の上流側において、前記作動流体の流路高さが下流側に向かって狭まるように、前記第2壁面に向かって突出する突出部を有し、
前記突出部の突出量は、前記突出部の先端が前記動翼の前記入口の前記チップを越えて前記第2壁面側に突出しないように設定されている。
この点、前記構成(1)によれば、前記突出部を有するので、作動流体は突出部に沿って流れることで第2壁面側(ハブ側)へ寄せられ、第1壁面側(シュラウド側)への作動流体の偏流が抑制される。そのため、動翼出口での不均衡な流れが緩和され、混合損失が低減するため、タービン効率が向上する。
従って、前記構成(1)により、上述した可変ノズルの大開度域における最大流量確保というメリットに加えて、可変ノズルが小開度域のときのタービン効率向上というメリットも享受できる。
前記膨張タービンは、前記膨張タービンの半径方向に沿って前記作動流体が前記動翼の前記入口に流れ込むラジアルタービンであり、
前記動翼の前記入口における根本の軸方向位置を原点とし、前記動翼の前記入口における前記チップの軸方向位置をXtとしたとき、前記突出部の先端の軸方向位置Xpは0<Xt≦Xpの関係を満たしている。
前記構成(2)によれば、ラジアルタービンにおいて、前記突出部の突出量は、前記突出部の先端が動翼のハブ側に突出しないように設定されている。そのため、動翼入口における流路面積の低下を抑制できるので、所期の動翼性能が得られやすくなり、タービン効率を高く維持できる。
前記第1壁面は前記半径方向に対して傾斜したテーパ面を有し、該テーパ面によって前記突出部が形成されており、
前記テーパ面が前記膨張タービンの軸方向に対してなす角度が40度以下である。
前記構成(3)によれば、動翼入口の上流側において前記テーパ面に沿って作動流体を第2壁面側(ハブ側)へ十分に寄せることができ、そのため、第1壁面側(シュラウド側)への作動流体の偏流を抑制できる。これによって、動翼出口における流速分布を均一化し、混合損失を抑制することで、タービン効率が向上する。
前記膨張タービンの中心軸から前記可変ノズルの前記回動軸までの前記半径方向における距離をRSとし、前記膨張タービンの中心軸から前記動翼の前記入口までの前記半径方向における距離をRRとしたとき、RS/RR≧1.4を満たす。
前記構成(4)によれば、可変ノズル出口から動翼入口までの距離が広がり、この部分の距離が広がることで、可変ノズル出口側で作動流体の流速低下が起り、静圧の低下を抑制できる。そのため、可変ノズルの圧力面と負圧面間の圧力差を低減できるので、クリアランスフローを抑制でき、タービン効率を向上できる。
特に、小開度域では、流れ損失全体に占めるクリアランスフローに起因した損失の割合が高いため、上記構成(4)による効果(クリアランスフローの抑制によるタービン効率向上効果)が大きい。
内燃機関からの排ガスによって駆動されるように構成された請求項1乃至6の何れか一項に記載の膨張タービンと、
前記膨張タービンによって駆動されて前記内燃機関への吸気を圧縮するように構成されたコンプレッサと、を備えたターボチャージャである。
前記構成(5)によれば、前記ターボチャージャにおいて、可変ノズルが小開度域のときのタービン効率の低下を抑制できると共に、可変ノズルが大開度域のときの作動流体の流量を確保することができる。また、所期の動翼性能が得られやすくなり、タービン効率を高く維持できる。
例えば、「ある方向に」、「ある方向に沿って」、「平行」、「直交」、「中心」、「同心」或いは「同軸」等の相対的或いは絶対的な配置を表す表現は、厳密にそのような配置を表すのみならず、公差、若しくは、同じ機能が得られる程度の角度や距離をもって相対的に変位している状態も表すものとする。
例えば、「同一」、「等しい」及び「均質」等の物事が等しい状態であることを表す表現は、厳密に等しい状態を表すのみならず、公差、若しくは、同じ機能が得られる程度の差が存在している状態も表すものとする。
例えば、四角形状や円筒形状等の形状を表す表現は、幾何学的に厳密な意味での四角形状や円筒形状等の形状を表すのみならず、同じ効果が得られる範囲で、凹凸部や面取り部等を含む形状も表すものとする。
一方、一つの構成要素を「備える」、「具える」、「具備する」、「含む」、又は「有する」という表現は、他の構成要素の存在を除外する排他的な表現ではない。
これらハウジングの内部に中心軸3がターボチャージャ1の軸方向に沿って設けられ、中心軸3は軸受(不図示)によって回転自在に支持されている。タービンハウジング2a側に位置する中心軸3の一端にタービンホイール4が固定され、コンプレッサハウジング2c側に位置する中心軸3の他端にコンプレッサホイール5が固定されている。
排気口6aから排出された排ガスeは排気管7を経て、作動流体としてタービンハウジング2aのスクロール部に接線方向に流入し、タービンホイール4を回転させた後、出口開口2eから流出する。
前記ハウジング内にターボチャージャ1の軸方向に沿って設けられた中心軸3のタービン側端部には、タービンホイール4が固定されている。タービンホイール4は、中心軸3に固定されたハブ26と、ハブ26の外表面(ハブ面26a)に周方向に放射状に固定された複数の動翼28とで構成されている。
ノズルプレート32とノズルマウント34との間に、空間sに連通する流路fが形成されている。流路fに複数の可変ノズル36が中心軸3の周方向(排気タービン1aの周方向)に配置され、これら複数の可変ノズル36は動翼28の周囲に間隔を空けて配置されている。
該アクチュエータを稼働させることで、複数の可変ノズル36を回動軸38を中心に同期して回動させることができる。複数の可変ノズル36を同期して回動させることで、空間sを通過した排ガスeが流路fを通過して動翼28に流入する際に、流路fの流路面積を変化させることができる。
流路fは中心軸3の軸線Cと直交する方向、即ち、排気タービン1aの半径方向に沿って形成されており、排気タービン1aはラジアルタービンを構成している。
排気管7からスクロール部30の空間sに流入した排ガスeは、流路fに接線方向に流入する。流路fに流入した排ガスeは動翼28に達してタービンホイール4及び中心軸3を回転し、その後、中心軸3の軸線C上に形成された出口開口42から流出する。
なお、図3に示す例示的な実施形態では、突出部44の先端の軸方向位置Xpが、動翼28の前縁28bにおけるチップ28aの軸方向位置をXtと一致している(即ち、Xp=Xtの条件を満たす)。一方、図4に示す例示的な実施形態では、突出部44の先端の軸方向位置Xpが、動翼28の前縁28bにおけるチップ28aの軸方向位置をXtよりもシュラウド側に後退している(即ち、Xp>Xtの条件を満たす)。
また、突出部44,54より上流側のシュラウド壁32aには、可変ノズル36の熱膨張による伸びを許容するため、最大開度時の可変ノズル36の出口端と突出部44,54(テーパ面44a,54a)との間に伸び代hが残るようになっている。
そのため、可変ノズル36の圧力面と負圧面間の圧力差を低減できるので、クリアランスフローを抑制でき、タービン効率を向上できる。特に、小開度域では、流れ損失全体に占めるクリアランスフローの抑制によるタービン効率向上効果が大きい。
また、突出部44,54によって作動流体wは第2壁面52側(ハブ側)へ寄せられ、第1壁面50側(シュラウド側)への偏流が抑制される。そのため、動翼28の出口で膨張タービン10(10A,10B)の径方向における流速分布(流速Vの径方向分布)の不均一性が緩和され、混合損失が低減する。従って、可変ノズル36が小開度域にある場合でも、タービン効率を高く維持できる。
これによって、スクロール部の形状に依存することなく、可変ノズル36が小開度域のときのタービン効率を向上できると共に、可変ノズル36が大開度域のときの動翼28へ流入する作動流体wの流量(最大流量)を確保できる。
従来の膨張タービン100は、可変ノズル36の出口側翼高さと動翼28の入口側翼高さとは同等であり、かつテーパ面44a(54a)及び突出部44(54)が形成されていない。そのため、図7に示すように、可変ノズル36の小開度領域において、動翼28に流入する作動流体wが持つ旋回成分に起因した遠心力により、作動流体wはシュラウド壁32aの壁面を含む第1壁面50側に押し付けられやすい。
従って、作動流体wが第1壁面50側に押し付けられると、動翼28の出口において、作動流体wの流れは第1壁面50側に偏り、第1壁面50側で流速Vが大きく、第2壁面52側で流速が小さくなる。その結果、動翼28の下流側で流速不均衡を解消するように作動流体wが広がり、混合損失が起こりやすい。
1a 排気タービン
1b 軸受台
1c コンプレッサ
2a、13 タービンハウジング
12 外殻部
2d 入口ケーシング
2e、42 出口開口
2b 軸受ハウジング
2c コンプレッサハウジング
2f 入口開口
2g 出口ケーシング
3 中心軸
4 タービンホイール
5 コンプレッサホイール
6 自動車用エンジン
6a 排気口
6b 給気口
7 排気管
8 給気管
9 インタークーラ
10A、10B、100 膨張タービン
16 結合具
20 軸受
22 潤滑油路
26 ハブ
26a ハブ面
28 動翼
28a チップ
28b 前縁
30 スクロール部
32 ノズルプレート
32a シュラウド壁
34 ノズルマウント
36 可変ノズル
38 回動軸
40 同期機構
42 出口開口
44、54 突出部
44a、54a テーパ面
50 第1壁面
52 第2壁面
C 軸線
a 空気
e 排ガス
f 流路
h 伸び代
r 潤滑油
s 空間
w 作動流体
Claims (5)
- 作動流体が持つエネルギーから動力を回収するための膨張タービンであって、
前記作動流体が導入されるスクロール部を含むタービンハウジングと、
前記タービンハウジング内において前記膨張タービンの周方向に間隔を空けて配置され、前記スクロール部を通過した前記作動流体の流路面積が変化するように回動軸周りに回動可能に構成された複数の可変ノズルと、
前記可変ノズルの下流側に位置する動翼を複数有し、前記タービンハウジング内に回転自在に設けられたタービンホイールと、を備え、
前記タービンハウジングは、前記動翼のチップに対向するシュラウド部を含む第1壁面と、前記作動流体の流路を挟んで前記第1壁面に対向する第2壁面とを有し、
前記可変ノズルの出口側の翼高さは前記動翼の入口側の翼高さより大きく、
前記シュラウド部は、前記可変ノズルの出口の下流側かつ前記動翼の入口の上流側において、前記作動流体の流路高さが下流側に向かって狭まるように、前記第2壁面に向かって突出する突出部を有し、
前記突出部の突出量は、前記突出部の先端が前記動翼の前記入口の前記チップを越えて前記第2壁面側に突出しないように設定されていることを特徴とする膨張タービン。 - 前記膨張タービンは、前記膨張タービンの半径方向に沿って前記作動流体が前記動翼の前記入口に流れ込むラジアルタービンであり、
前記動翼の前記入口における根本の軸方向位置を原点とし、前記動翼の前記入口における前記動翼の前記チップの軸方向位置をXtとしたとき、前記突出部の先端の軸方向位置Xpは0<Xt≦Xpの関係を満たしていることを特徴とする請求項1に記載の膨張タービン。 - 前記第1壁面は前記半径方向に対して傾斜したテーパ面を有し、該テーパ面によって前記突出部が形成されており、
前記テーパ面が前記膨張タービンの軸方向に対してなす角度が40度以下であることを特徴とする請求項1に記載の膨張タービン。 - 前記膨張タービンの中心軸から前記可変ノズルの前記回動軸までの前記半径方向における距離をRSとし、前記膨張タービンの中心軸から前記動翼の前記入口までの前記半径方向における距離をRRとしたとき、RS/RR≧1.4を満たすことを特徴とする請求項2又は3に記載の膨張タービン。
- 内燃機関からの排ガスによって駆動されるように構成された請求項1乃至4の何れか一項に記載の膨張タービンと、
前記膨張タービンによって駆動されて前記内燃機関への吸気を圧縮するように構成されたコンプレッサと、を備えていることを特徴とするターボチャージャ。
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JP6651599B2 (ja) * | 2017-11-30 | 2020-02-19 | 三菱重工業株式会社 | 可変ノズル機構及びこれを備えた回転機械 |
US11339680B2 (en) * | 2018-02-28 | 2022-05-24 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Radial inflow turbine and turbocharger |
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