WO2015002142A1 - Unité de tuyère variable et compresseur à suralimentation de type capacité variable - Google Patents

Unité de tuyère variable et compresseur à suralimentation de type capacité variable Download PDF

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Publication number
WO2015002142A1
WO2015002142A1 PCT/JP2014/067381 JP2014067381W WO2015002142A1 WO 2015002142 A1 WO2015002142 A1 WO 2015002142A1 JP 2014067381 W JP2014067381 W JP 2014067381W WO 2015002142 A1 WO2015002142 A1 WO 2015002142A1
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WO
WIPO (PCT)
Prior art keywords
variable nozzle
blade
variable
wall member
turbine
Prior art date
Application number
PCT/JP2014/067381
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English (en)
Japanese (ja)
Inventor
森田　功
奈都子 元田
Original Assignee
株式会社Ihi
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 株式会社Ihi filed Critical 株式会社Ihi
Priority to CN201480022430.1A priority Critical patent/CN105143635B/zh
Priority to DE112014003165.8T priority patent/DE112014003165B4/de
Publication of WO2015002142A1 publication Critical patent/WO2015002142A1/fr

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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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • 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 invention relates to a variable nozzle unit and a variable displacement supercharger capable of adjusting a flow path area (throat area) of a gas such as exhaust gas.
  • variable nozzle units used in variable capacity superchargers.
  • the configuration of a general variable nozzle unit is as follows (see Patent Document 1 and Patent Document 2).
  • An annular first wall member is provided on the radially outer side (inlet side) of the turbine impeller in the turbine housing of the variable capacity turbocharger.
  • An annular second wall member is provided at a position opposite to the first wall member in the axial direction of the turbine impeller.
  • the first wall member has a facing surface that faces the second wall member, and the second wall member has a facing surface that faces the first wall member.
  • a plurality of variable nozzle blades are arranged at intervals in the circumferential direction between the facing surface of the first wall member and the facing surface of the second wall member. Each variable nozzle blade is provided so as to be rotatable in an opening / closing direction (forward / reverse direction) around an axis parallel to the axis of the turbine impeller.
  • the plurality of variable nozzle blades are rotated in the opening direction (forward direction) in synchronization to increase the throat area.
  • the plurality of variable nozzle blades rotate in the closing direction (reverse direction) synchronously to reduce the throat area.
  • Patent Documents 3 and 4 disclose prior art related to the present invention.
  • the side clearance is between the side surface on the hub side of each variable nozzle blade and the opposed surface of the first wall member, and on the shroud side of each variable nozzle blade. It is formed between the side surface and the opposing surface of the second wall member. If the clearance flow (ie, the gas flow through the side clearance) increases during operation of the variable displacement turbocharger, the energy loss region on the inlet side of the turbine impeller increases due to the mixing of the clearance flow and the main flow. In addition, the turbine efficiency of the variable capacity supercharger is reduced. That is, there is a problem that it is not easy to increase the turbine efficiency of the variable capacity supercharger while ensuring the reliability of the rotation operation of each variable nozzle blade. In particular, since the angle (intersection angle) formed by the clearance flow and the mainstream flow is large in the operating region (operating point) on the small flow rate side, the above problem becomes more prominent.
  • variable nozzle unit is used for a variable displacement supercharger but also when used for another turbo rotating machine such as a gas turbine.
  • an object of the present invention is to provide a variable nozzle unit and a variable displacement supercharger that can solve the above-mentioned problems.
  • a variable nozzle unit capable of adjusting a flow passage area (throat area) of gas supplied to a turbine impeller of a turbo rotating machine.
  • a first wall member provided on the radially outer side (inlet side) of the turbine impeller in the turbine housing, and an axial direction of the turbine impeller with respect to the first wall member so as to face the first wall member
  • a second wall member spaced apart from the first wall member and a second wall member spaced apart in a circumferential direction between the first wall member and the second wall member, and an axis parallel to the axis of the turbine impeller
  • the shroud is pivotable in the opening / closing direction (forward / reverse direction) around the center, and the shroud side facing the second wall member protrudes (protrudes) radially inward from the hub side facing the first wall member.
  • Twist the trailing edge A plurality of variable nozzle vanes which twisted constructed mainly, by comprising the the gist.
  • the “turbo rotating machine” means a variable capacity supercharger and a gas turbine.
  • the “first wall member” and the “second wall member” may constitute a part of the turbine housing.
  • “provided” means that it is indirectly provided through another member in addition to being directly provided.
  • the term “arranged” is intended to include being disposed indirectly through another member in addition to being disposed directly.
  • the twist angle of each variable nozzle blade may be set to 2.0 to 5.0 degrees.
  • variable capacity supercharger that supercharges air supplied to the engine side using energy of exhaust gas from the engine.
  • the gist is that a variable nozzle unit is provided.
  • FIG. 1A is a view of a variable nozzle blade according to an embodiment of the present invention as viewed from the axial direction of a turbine impeller.
  • FIG. 1B (a) shows a meridional view of the periphery of the variable nozzle blade according to the embodiment of the present invention
  • FIG. 1B (b) shows the periphery of the variable nozzle blade according to the embodiment of the present invention viewed from the front edge side.
  • FIG. FIG. 2A is an enlarged cross-sectional view taken along line II-II in FIG. 3 and shows a state in which the opening degrees of a plurality of variable nozzle blades are opened.
  • FIG. 2B is an enlarged cross-sectional view taken along line II-II in FIG. FIG.
  • FIG. 3 is a front sectional view (a meridional view) of a radial turbine in the variable capacity turbocharger according to the embodiment of the present invention.
  • FIG. 4 is a front sectional view (a meridional view) of the variable capacity supercharger according to the embodiment of the present invention.
  • FIG. 5A is a view of a variable nozzle blade according to a first modification of the embodiment of the present invention as viewed from the axial direction of the turbine impeller.
  • FIG. 5B (a) is a meridional view around the variable nozzle blade according to the first modification of the embodiment of the present invention, and
  • FIG. 5B (b) is a first modification of the embodiment of the present invention viewed from the front edge side.
  • FIG. 6A is a view of a variable nozzle blade according to a second modification of the embodiment of the present invention as viewed from the axial direction of the turbine impeller.
  • 6B (a) is a meridional view around the variable nozzle blade according to the second modification of the embodiment of the present invention, and
  • FIG. 6B (b) is a second modification of the embodiment of the present invention viewed from the front edge side.
  • FIG. 7A (a) is a perspective view of a plurality of variable nozzle blades according to the invention example, and FIG.
  • FIG. 7A (b) is a view of the plurality of variable nozzle blades according to the invention example as viewed from the axial direction of the turbine impeller.
  • FIG. 7B (a) is a perspective view of a plurality of variable nozzle blades according to a comparative example
  • FIG. 7B (b) is a view of the plurality of variable nozzle blades according to the comparative example viewed from the axial direction of the turbine impeller.
  • 8 (a) and 8 (b) are diagrams showing a region where energy loss is large on the inlet side of the turbine impeller in the operating region on the small flow rate side
  • FIG. 8 (a) is a variable according to the invention example. The case where a nozzle blade is used is shown, and FIG.
  • FIG. 8B shows the case where a variable nozzle blade according to a comparative example is used.
  • FIG. 9 is a diagram showing the relationship between the twist angle of the variable nozzle blade and the improvement rate of the turbine efficiency in the operating region on the small flow rate side.
  • FIG. 10 is a diagram showing the results of an aerodynamic performance test simulating actual operating conditions.
  • the present invention is based on the following knowledge newly obtained by the inventors of the present application.
  • the first finding is that the variable nozzle blade is configured to be twisted with the trailing edge as a twist center so that the shroud side protrudes radially inward from the hub side (FIGS. 7A (a) and 7A (b)).
  • the comparative nozzle shown in FIGS. 7B (a) and 7B (b) is not used. Therefore, as shown in FIGS. 8A and 8B, as compared with the case of the variable nozzle blade 200 having the leading edge 200a and the trailing edge 200t, the inlet of the turbine impeller is operated during the operation of the turbo rotating machine.
  • the region L having a large energy loss on the side E can be reduced. This is because the variable nozzle blade 100 is configured to be twisted with the trailing edge 100t as a twisting center so that the shroud side 100s protrudes radially inward from the hub side 100h, thereby reducing the clearance flow through the side clearance. This is probably due to this.
  • FIG. 7A (a) is a perspective view of a plurality of variable nozzle blades 100 according to the invention example
  • FIG. 7A (b) is a view of the plurality of variable nozzle blades 100 according to the invention example from the axial direction of the turbine impeller
  • 7B is a perspective view of a plurality of variable nozzle blades 200 according to the comparative example
  • FIG. 7B is a diagram of the plurality of variable nozzle blades 200 according to the comparative example viewed from the axial direction of the turbine impeller.
  • FIGS. 8A and 8B are diagrams showing a region L where energy loss is large on the inlet side E of the turbine impeller in the operating region on the small flow rate side
  • FIG. 8A is an example of the invention.
  • FIG. 8B shows a case where the variable nozzle blade 200 according to the comparative example is used.
  • the inter-blade distance on the midspan side 100m (the center side of the shroud side 100s and the hub side 100h) of the plurality of variable nozzle blades 100 according to the invention example is the same as the inter-blade distance of the plurality of variable nozzle blades 200 according to the comparative example. They are set the same. 7A (b) and 7B (b), “ID” indicates the radially inner side, and “OD” indicates the radially outer side. Further, the region L where the energy loss is large in FIGS. 8A and 8B is obtained by a three-dimensional steady-state viscous CFD (Computational Fluid Dynamics) analysis. It was assumed that the side clearance was smaller than the side clearance on the hub side H.
  • CFD Computational Fluid Dynamics
  • the second finding is that when the twist angle of the variable nozzle blade is 2.0 to 5.0 degrees, as shown in FIG. 9, the improvement rate of the turbine efficiency of the turbo rotating machine can be sufficiently increased. That's it.
  • FIG. 9 is a diagram showing the relationship between the twist angle of the variable nozzle blade and the improvement rate of the turbine efficiency in the operating region on the small flow rate side.
  • the twist angle of the variable nozzle blade refers to the twist angle of the shroud side with respect to the hub side of the variable nozzle blade, and when the shroud side of the variable nozzle blade protrudes radially inward from the hub side, the variable nozzle blade The sign of the twist angle of the variable nozzle is positive, and the sign of the twist angle of the variable nozzle is negative when the hub side of the variable nozzle blade protrudes radially inward from the shroud side.
  • variable nozzle blade according to the invention example when used, the variable nozzle blade according to the comparative example is used.
  • the turbine efficiency was improved over the entire operating range, particularly in the operating range on the small flow rate side.
  • L is the left direction
  • R is the right direction
  • ID is the radially inner side
  • OD is the radially outer side
  • RD is the rotational direction of the turbine impeller (rotor shaft).
  • variable capacity supercharger an example of a supercharger 1 according to the present embodiment uses pressure energy of exhaust gas (an example of gas) from an engine (not shown), The air supplied to the engine is supercharged (compressed).
  • the variable capacity supercharger 1 includes a bearing housing 3.
  • a radial bearing 5 and a pair of thrust bearings 7 are provided in the bearing housing 3.
  • the plurality of bearings 5 and 7 are rotatably provided with a rotor shaft (turbine shaft) 9 extending in the left-right direction.
  • the rotor shaft 9 is rotatably provided in the bearing housing 3 via the plurality of bearings 5 and 7.
  • a compressor 11 that compresses air using centrifugal force is disposed.
  • a specific configuration of the compressor 11 is as follows.
  • Compressor housing 13 is provided on the right side of bearing housing 3.
  • a compressor impeller 15 is provided in the compressor housing 13 so as to be rotatable about its axis.
  • the compressor impeller 15 is integrally connected to the right end portion of the rotor shaft 9.
  • the compressor impeller 15 includes a compressor disk 17.
  • the hub surface 17h of the compressor disk 17 extends from the right side to the radially outer side (the radially outer side of the compressor impeller 15).
  • a plurality of compressor blades 19 are integrally formed on the hub surface 17 h of the compressor disk 17 at intervals in the circumferential direction.
  • An air inlet 21 for taking air into the compressor housing 13 is formed on the inlet side (upstream side when viewed from the air flow direction) of the compressor impeller 15 in the compressor housing 13.
  • the air intake 21 is connected to an air cleaner (not shown) that purifies air.
  • an annular diffuser passage 23 that pressurizes compressed air is formed on the outlet side of the compressor impeller 15 between the bearing housing 3 and the compressor housing 13 (downstream side when viewed from the air flow direction). Yes.
  • a spiral compressor scroll passage 25 is formed inside the compressor housing 13, and the compressor scroll passage 25 communicates with the diffuser passage 23.
  • An air discharge port 27 for discharging the compressed air to the outside of the compressor housing 13 is formed at an appropriate position of the compressor housing 13. The air discharge port 27 is connected to an intake manifold (not shown) of the engine.
  • An annular seal plate 29 is provided on the right side of the bearing housing 3 to prevent leakage of compressed air to the thrust bearing 7 side.
  • a radial turbine 31 is disposed on the left side of the bearing housing 3 to generate a rotational force (rotational torque) using the pressure energy of the exhaust gas.
  • a specific configuration of the radial turbine 31 is as follows.
  • a turbine housing 33 is provided on the left side of the bearing housing 3.
  • a turbine impeller 35 is provided in the turbine housing 33 so as to be rotatable about its axis.
  • the turbine impeller 35 is integrally connected to the left end portion of the rotor shaft 9.
  • the turbine impeller 35 includes a turbine disk 37.
  • the hub surface 37h of the turbine disk 37 extends from the left side (one axial direction side of the turbine impeller 35) to the radially outer side (the radial direction outer side of the turbine impeller 35).
  • a plurality of turbine blades 39 are integrally formed on the hub surface 37 h of the turbine disk 37 at equal intervals in the circumferential direction.
  • a gas inlet 41 for taking exhaust gas into the turbine housing 33 is formed at an appropriate position of the turbine housing 33.
  • the gas inlet 41 is connected to an exhaust manifold (not shown) of the engine.
  • a spiral turbine scroll passage 43 is formed on the inlet side of the turbine impeller 35 inside the turbine housing 33 (upstream side when viewed from the flow direction of the exhaust gas).
  • the turbine scroll passage 43 communicates with the gas intake 41.
  • a gas discharge port 45 for discharging the exhaust gas is formed on the outlet side of the turbine impeller 35 in the turbine housing 33 (downstream side when viewed from the flow direction of the exhaust gas).
  • the gas discharge port 45 is connected to a catalyst (not shown) via a connecting pipe (not shown).
  • an annular step 47 is formed on the inlet side of the gas discharge port 45 in the turbine housing 33.
  • An annular heat shield plate 49 that shields heat from the turbine impeller 35 side is provided on the left side surface of the bearing housing 3.
  • a wave washer 51 is provided between the left side surface of the bearing housing 3 and the outer edge portion of the heat shield plate 49.
  • variable nozzle unit 53 for adjusting (variable) the flow area (throat area) of exhaust gas supplied to the turbine impeller 35 side is disposed.
  • the specific configuration of the variable nozzle unit 53 is as follows.
  • a nozzle ring 55 as a first wall member is disposed concentrically with the turbine impeller 35 via a support ring 57 on the radially outer side (inlet side) of the turbine impeller 35 in the turbine housing 33. It is installed.
  • the nozzle ring 55 is formed in an annular shape, for example.
  • the inner peripheral edge of the nozzle ring 55 is fitted to the outer peripheral edge of the heat shield plate 49.
  • the nozzle ring 55 is formed with a plurality (only one shown) of first support holes 59 penetrating at equal intervals in the circumferential direction.
  • the outer peripheral edge of the support ring 57 is sandwiched between the bearing housing 3 and the turbine housing 33.
  • a shroud ring 61 as a second wall member is provided integrally and concentrically with the nozzle ring 55 via a plurality of connecting pins 63 at a position facing the nozzle ring 55 in the lateral direction.
  • the shroud ring 61 is provided to be separated from the nozzle ring 55 in the axial direction of the turbine impeller 35 so as to face the nozzle ring 55.
  • the nozzle ring 55 is formed in an annular shape, for example.
  • a plurality (only one is shown) of second support holes 65 are formed in the shroud ring 61 so as to penetrate the shroud ring 61 at equal intervals in the circumferential direction so as to align with the plurality of first support holes 59 of the nozzle ring 55.
  • the plurality of connecting pins 63 have a function of setting an interval between the facing surface of the nozzle ring 55 and the facing surface of the shroud ring 61.
  • the shroud ring 61 has a cylindrical shroud portion 67 that covers the outer edges of the plurality of turbine blades 39 on the inner peripheral edge side.
  • the shroud portion 67 protrudes leftward (one axial direction side of the turbine impeller 35) and is located inside the stepped portion 47 of the turbine housing 33.
  • a ring groove 69 is formed on the outer peripheral surface of the shroud portion 67 of the shroud ring 61.
  • a plurality of seal rings 71 that suppress leakage of exhaust gas from the turbine scroll flow path 43 side are provided on the inner peripheral surface of the stepped portion 47 of the turbine housing 33 with its own elastic force (elastic force of the plurality of seal rings 71). Is provided in pressure contact.
  • the inner peripheral edge of each seal ring 71 is fitted in the ring groove 69 of the shroud ring 61.
  • variable nozzle blades between the nozzle ring 55 and the shroud ring 61 (in other words, between the facing surface of the nozzle ring 55 and the facing surface of the shroud ring 61).
  • 73 are arranged at equal intervals in the circumferential direction.
  • Each variable nozzle blade 73 is rotatable in the opening / closing direction (forward / reverse direction) around an axis parallel to the axis C of the turbine impeller 35.
  • a first blade shaft 75 is integrally formed on the right side surface (side surface of the hub side 73 h) of each variable nozzle blade 73.
  • the first blade shaft 75 is rotatably supported in the corresponding first support hole 59 of the nozzle ring 55.
  • a second blade shaft 77 is integrally formed with the first blade shaft 75 on the left side surface (side surface of the shroud side 73 s) of each variable nozzle blade 73.
  • the second blade shaft 77 is rotatably supported in the corresponding second support hole 65 of the shroud ring 61.
  • Each variable nozzle blade 73 has a first flange (not shown) that can contact the opposing surface of the nozzle ring 55 on the base end side of the first blade shaft 75. Further, each variable nozzle blade 73 has a second flange portion (not shown) that can contact the facing surface of the shroud ring 61 on the proximal end side of the second blade shaft 77.
  • Each variable nozzle blade 73 is a double-supported type having a first blade shaft 75 and a second blade shaft 77, but may be a cantilever type in which the second blade shaft 77 is omitted.
  • variable nozzle blades 73 are set to have the same cord length from the shroud side 73s to the hub side 73h.
  • Each variable nozzle blade 73 has the same blade shape (blade cross-sectional shape).
  • the cord length or blade shape of each variable nozzle blade 73 may not be the same from the shroud side 73s to the hub side 73h.
  • each variable nozzle blade 73 protrudes (projects) the shroud side 73s radially inward from the hub side 73h and the midspan side (center side of the shroud side 73s and the hub side 73h) 73m.
  • the rear edge 73t is twisted as described above.
  • each variable nozzle blade 73 projects the shroud side 73s radially inward from the hub side 73h and the midspan side 73m in a state where the trailing edge 73t is held parallel to the axis C of the turbine impeller 35. It is configured to be twisted.
  • each variable nozzle blade 73 protrudes radially inward from the shroud side 73s.
  • the twist angle (torsion angle of the shroud side 73s with respect to the hub side 73h) ⁇ of each variable nozzle blade 73 is set to 2.0 to 5.0 degrees. Furthermore, as shown in FIGS.
  • each variable nozzle blade 73 is twisted as described above, so that the leading edge 73a of each variable nozzle blade 73 on the meridian plane is
  • the shroud side end 73as is inclined with respect to a direction PD parallel to the axis C of the turbine impeller 35 such that the shroud side end 73as is positioned radially inward from the hub side end 73ah.
  • a link mechanism 81 for rotating a plurality of variable nozzle blades 73 synchronously is disposed in an annular link chamber 79 formed on the opposite side of the opposed surface of the nozzle ring 55.
  • the link mechanism 81 has a known configuration as disclosed in JP2009-243431A, JP2009-243300A, and the like.
  • the link mechanism 81 is connected via a power transmission mechanism 83 to a rotation actuator (not shown) such as a motor or a cylinder that rotates the plurality of variable nozzle blades 73 in the opening / closing direction.
  • Exhaust gas taken in from the gas inlet 41 flows from the inlet side to the outlet side of the turbine impeller 35 via the turbine scroll flow path 43, thereby generating a rotational force (rotational torque) using the pressure energy of the exhaust gas.
  • the rotor shaft 9 and the compressor impeller 15 can be rotated integrally with the turbine impeller 35.
  • the air taken in from the air intake 21 can be compressed and discharged from the air outlet 27 via the diffuser passage 23 and the compressor scroll passage 25, and the air supplied to the engine is supercharged. (Compressed).
  • variable displacement supercharger 1 When the engine speed is high and the exhaust gas flow rate is high, the link mechanism 81 is operated by a rotating actuator and the variable nozzle blades 73 are moved in the forward direction (opened). The gas passage area (throat area) of the exhaust gas supplied to the turbine impeller 35 side is increased, and a lot of exhaust gas is supplied. On the other hand, when the engine speed is low and the flow rate of the exhaust gas is small, the plurality of variable nozzle blades 73 are rotated synchronously in the reverse direction (closed direction) while the link mechanism 81 is operated by the rotation actuator. As a result, the throat area is reduced, the flow rate of the exhaust gas is increased, and the work amount of the turbine impeller 35 is sufficiently ensured. Thus, the rotational force can be sufficiently and stably generated by the turbine impeller 35 regardless of the flow rate of the exhaust gas (normal operation of the variable displacement supercharger 1).
  • Each of the variable nozzle blades 73 is configured to be twisted with the trailing edge 73t as a twist center so that the shroud side 73s protrudes radially inward from the hub side 73h and the midspan side 73m.
  • the side between the side surface on the hub side 73 h of each variable nozzle blade 73 and the facing surface of the nozzle ring 55, and the side surface between the side surface on the shroud side 73 s of each variable nozzle blade 73 and the facing surface of the shroud ring 61 Even if the clearance is formed, a region where the energy loss is large on the inlet side of the turbine impeller 35 can be reduced.
  • each variable nozzle blade 73 is set to 2.0 to 5.0 degrees, the turbine efficiency of the variable displacement turbocharger 1 (when the second novel knowledge described above is applied) The improvement rate of the turbine efficiency of the radial turbine 31 can be sufficiently increased (the characteristic action of the variable capacity supercharger 1).
  • the turbine efficiency of the variable capacity supercharger 1 can be increased while ensuring the reliability of the rotating operation of each variable nozzle blade 73.
  • the improvement rate of the turbine efficiency of the variable capacity supercharger 1 can be sufficiently increased, the above-described effects can be further enhanced.
  • the variable nozzle blade 85 is variable instead of the variable nozzle blade 73 (see FIG. 1A). It is used for the nozzle unit 53 (see FIG. 3).
  • the variable nozzle blade 85 has the same configuration as the variable nozzle blade 73, and only the characteristic part of the configuration of the variable nozzle blade 85 will be described.
  • those corresponding to the components in the variable nozzle blade 73 are denoted by the same reference numerals in the drawing.
  • Each of the variable nozzle blades 85 is twisted with the trailing edge 85t as the center of twist so that the shroud side 85s protrudes radially inward from the hub side 85h and the midspan side (the center side of the shroud side 85s and the hub side 85h) 85m. It is configured. Further, since each variable nozzle blade 85 is configured to be twisted as described above, the front edge 85a of each variable nozzle blade 85 has a shroud-side end 85as more than a hub-side end 85ah on the meridian surface. It inclines with respect to direction PD parallel to the axial center (refer FIG. 3) of the turbine impeller 35 so that it may be located inside radial direction.
  • Each variable nozzle blade 85 has a blade surface 85o on the radially outer side.
  • the blade surface 85o includes a concave curved surface portion (concave portion) 87 formed from the shroud side 85s to the midspan side 85m.
  • the concave curved surface portion 87 is located at a portion near the leading edge 85a on the blade surface 85o.
  • the concave curved surface portion 87 is formed on the blade surface 85o so as to be the lowest at any portion between the center and the leading edge 85a in the code line (or camber line) of the variable nozzle blade 85. Yes.
  • the concave curved surface portion 87 is formed to have a gentle curved surface.
  • Each variable nozzle blade 85 has a blade surface 85i on the radially inner side.
  • the blade surface 85i includes a convex curved surface portion (convex portion) 89 formed from the shroud side 85s to the midspan side 85m.
  • the convex curved surface part 89 is located in the site
  • the convex curved surface portion 89 is formed on the blade surface 85i so as to be the highest in any part between the center of the code line (or camber line) of the variable nozzle blade 85 and the leading edge 85a. Yes.
  • the convex curved surface portion 89 is formed to have a gentle curved surface.
  • variable nozzle blade 85 is twisted with the trailing edge 85t as the center of twist so that the shroud side 85s protrudes radially inward from the hub side 85h and the midspan side 85m. Configured. Therefore, there exists an effect
  • a gentle concave curved surface portion 87 is formed from the shroud side 85s to the midspan side 85m at a portion near the front edge 85a on the radially outer blade surface 85o of each variable nozzle blade 85. Therefore, it is possible to generate a low pressure region A due to separation around the portion near the front edge 85a on the radially outer blade surface 85o of each variable nozzle blade 85. As a result, although there is a tendency that a higher pressure is applied to the radially outer blade surface 85o of each variable nozzle blade 85 than the radially inner blade surface 85i, the thrust toward the opposed surface side of the shroud ring 61 is applied to each variable nozzle blade 85. A force F can be generated.
  • each variable nozzle blade 85 is brought close to the facing surface side of the shroud ring 61 so that the side clearance on the shroud ring side is made smaller than the side clearance on the hub side, so that the variable displacement supercharger 1 (see FIG. 4). Turbine efficiency can be further increased. As shown in paragraphs [0038] and [0039] of Japanese Patent Application Laid-Open No. 2009-144545, the turbine efficiency of the variable displacement turbocharger 1 is smaller when the side clearance on the shroud ring side is smaller than the side clearance on the hub side. Research has shown that it can contribute to the improvement of
  • the variable nozzle blade 91 is variable instead of the variable nozzle blade 73 (see FIG. 1A). It is used for the nozzle unit 53 (see FIG. 3).
  • the variable nozzle blade 91 has the same configuration as the variable nozzle blade 73, and only the characteristic part of the configuration of the variable nozzle blade 91 will be described. Note that among the plurality of constituent elements in the variable nozzle blade 91, those corresponding to the constituent elements in the variable nozzle blade 73 are denoted by the same reference numerals in the drawing.
  • Each of the variable nozzle blades 91 is twisted with the trailing edge 91t as a twist center so that the shroud side 91s protrudes radially inward from the hub side 91h and the midspan side (the center side of the shroud side 91s and the hub side 91h) 91m. It is configured.
  • the front edge 91a of each variable nozzle blade 91 has a shroud side end 91as more than a hub side end 91ah on the meridian surface. It inclines with respect to direction PD parallel to the axial center (refer FIG. 3) of the turbine impeller 35 so that it may be located inside radial direction.
  • Each variable nozzle blade 91 is configured to project the midspan side 91m outward in the radial direction from the hub side 91h.
  • variable nozzle blade 91 is twisted with the trailing edge 91t as the twist center so that the shroud side 91s protrudes radially inward from the hub side 91h and the midspan side 91m. Therefore, the same operations and effects as those of the above-described embodiment of the present invention are achieved.
  • each variable nozzle blade 91 is configured to project the midspan side 91m radially outward from the hub side 91h. Therefore, the thrust force due to the pressure acting on the radially outer blade surface 91o of each variable nozzle blade 91 can be reduced. Thereby, the thrust force F to the opposing surface side of the shroud ring 61 can be generated in each variable nozzle blade 91 by the pressure acting on the radially inner side surface 91 i of each variable nozzle blade 91. Therefore, each variable nozzle blade 91 is brought close to the facing surface side of the shroud ring 61 so that the side clearance on the shroud ring side is made smaller than the side clearance on the hub side, so that the variable displacement supercharger 1 (see FIG. 4). Turbine efficiency can be further increased.
  • variable capacity supercharger 1 is applied to a turbo rotating machine other than the variable capacity supercharger 1 such as a gas turbine. It can be implemented in various other modes such as application. Further, the scope of rights encompassed by the present invention is not limited to these embodiments.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)

Abstract

La présente invention concerne une unité de tuyère variable ayant une pluralité d'aubes (73) de distributeur variables disposées à intervalles réguliers dans la direction circonférentielle, entre un distributeur annulaire (55) et un anneau d'étanchéité (61). Chaque aube (73) de distributeur variable peut tourner dans la direction d'ouverture/de fermeture autour d'un centre axial parallèle au centre axial (C) d'une pale (35) de turbine. Chaque aube (73) de distributeur variable est conçue de façon à pouvoir se visser, ayant un bord arrière (73t) comme centre de vissage associé, de sorte qu'un côté carénage (73s) sorte davantage vers l'intérieur dans la direction radiale qu'un côté moyeu (73h) et qu'un côté mi-portée (73m).
PCT/JP2014/067381 2013-07-05 2014-06-30 Unité de tuyère variable et compresseur à suralimentation de type capacité variable WO2015002142A1 (fr)

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CN201480022430.1A CN105143635B (zh) 2013-07-05 2014-06-30 可变喷嘴单元以及可变容量型增压器
DE112014003165.8T DE112014003165B4 (de) 2013-07-05 2014-06-30 Variable Düseneinheit und Turbolader mit variablem Geometriesystem

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JP2018532932A (ja) * 2015-09-16 2018-11-08 ボーグワーナー インコーポレーテッド パルス分離型可変タービン構造ターボチャージャのためのカートリッジ

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WO2018084154A1 (fr) * 2016-11-01 2018-05-11 株式会社Ihi Unité tuyère variable et compresseur de suralimentation
US11047256B2 (en) 2016-11-10 2021-06-29 Ihi Corporation Variable nozzle unit and turbocharger
DE102017118794A1 (de) * 2017-08-17 2019-02-21 Ihi Charging Systems International Gmbh Verstellbarer Leitapparat für eine Turbine, Turbine für einen Abgasturbolader und Abgasturbolader
DE102018211673A1 (de) 2018-07-12 2020-01-16 Continental Automotive Gmbh Leitschaufel und mit einer solchen versehene Turbinenanordnung
CN112867852A (zh) * 2018-12-04 2021-05-28 株式会社Ihi 可变容量型增压器
DE102018221161B4 (de) * 2018-12-06 2021-08-26 Vitesco Technologies GmbH Abgasturbine eines Abgasturboladers sowie Abgasturbolader mit einem strömungstechnischen Störelement im Turbinengehäuse
JP7165804B2 (ja) * 2019-02-25 2022-11-04 三菱重工エンジン＆ターボチャージャ株式会社 ノズルベーン
JP7248113B2 (ja) * 2019-06-14 2023-03-29 株式会社Ihi 過給機
JP7288982B2 (ja) 2020-01-07 2023-06-08 三菱重工エンジン＆ターボチャージャ株式会社 タービン及びターボチャージャ

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DE112014003165T5 (de) 2016-03-24
JP2015014252A (ja) 2015-01-22

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