CN102297016B - Turbocharger for double-vane nozzle systems - Google Patents

Turbocharger for double-vane nozzle systems Download PDF

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Publication number
CN102297016B
CN102297016B CN2011102331062A CN201110233106A CN102297016B CN 102297016 B CN102297016 B CN 102297016B CN 2011102331062 A CN2011102331062 A CN 2011102331062A CN 201110233106 A CN201110233106 A CN 201110233106A CN 102297016 B CN102297016 B CN 102297016B
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CN
China
Prior art keywords
nozzle
blade
fixed
leaf
double
Prior art date
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Application number
CN2011102331062A
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Chinese (zh)
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CN102297016A (en
Inventor
施永强
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Jiangsu Katie Navigation Control System Ltd By Share Ltd
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WUXI KAIDI BOOSTER DELER CO Ltd
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Application filed by WUXI KAIDI BOOSTER DELER CO Ltd filed Critical WUXI KAIDI BOOSTER DELER CO Ltd
Priority to CN2011102331062A priority Critical patent/CN102297016B/en
Publication of CN102297016A publication Critical patent/CN102297016A/en
Priority to JP2014525285A priority patent/JP6116564B2/en
Priority to CA2833790A priority patent/CA2833790C/en
Priority to DE112012001868.0T priority patent/DE112012001868B4/en
Priority to PCT/CN2012/001087 priority patent/WO2013023441A1/en
Priority to US14/009,070 priority patent/US20140086725A1/en
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Publication of CN102297016B publication Critical patent/CN102297016B/en
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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
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • 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
    • 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
    • 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

Abstract

The invention provides a turbocharger for double-vane nozzle systems, which comprises a turbine casing, a fixed nozzle ring, a linearly moving nozzle disk, a middle shell, a rack, rocking levers and gears, wing-shaped fixed vanes are arranged on the front end surface of the fixed nozzle ring, vane-shaped holes are arranged between the fixed vanes, the fixed nozzle ring is mounted on the outer circle of the middle shell, and is fixed on the middle shell by bolts, the linearly moving nozzle disk is mounted on the rear end of the fixed nozzle ring, a group of movable vanes are arranged on the front end surface of the linearly moving nozzle disk, and are movably inserted into the vane-shaped holes, the rear end surface of the linearly moving nozzle disk is firmly connected with the two rocking levers, and the rocking levers are inserted into the middle shell, and are engaged with the rack through the gears. Since the new vanes of the turbocharger for double-vane nozzle systems are arranged along a nozzle flow passage, not only can the sectional area of the passage be reduced, but also the original nozzle is divided into two air passages, so that the transverse flow loss of air flow can be reduced. Meanwhile, the air still flows according to the optimal air flow angle of the original design, so the operation of the turbine can be kept in the high-efficiency area.

Description

The turbosupercharger of double-leaf nozzle system
Technical field
The present invention relates to the turbosupercharger of double-leaf nozzle system, belong to the automotive fittings field.
Background technique
Waste gas by motor is discharged is the turbine work done in the pressurized machine, can only be in work in the narrow and small efficient district.Even be placed on the vehicle supercharger design point in the 50-70% scope, then motor must cause the pressurized machine hypervelocity at full capacity the time.People are added in exhaust by-pass valve mechanism on the pressurized machine for this reason, to improve its reliability, have also wasted the energy of the available combustion gas of part simultaneously.
Adopting the adjustable nozzle structure is to improve the effective ways of turbine pneumatic performance, also is the enforcement that each pressurized machine manufacturer of the world generally acknowledges and pays, and three kinds of different schemes are arranged at present:
By U.S. Honeywell Int Inc patent applied for number 200710152744.5 " blade assembly of variable nozzle turbocharger and the assembling methods of blade assembly " is exactly the variable-nozzle method that adopts the rotor blade angle.To be the cross-section area of nozzle reduce with the minimizing of blade rotating angle its advantage, and the nozzle area slip can reach more than 50%; Shortcoming is nozzle angle α excessive (a starting state), air-flow C, and " r clashes into turbine leaf convex surface; Spray angle α too small (completely negative state), air-flow C ' r clashes into leaf concave surface (seeing Figure 11), and pressurized machine thermal efficiency when low high operating mode is worked is descended.
Variable cross section by the French Honeywell Garrett Co., Ltd number of applying for a patent 00819834.9 " the form-varied turbosupercharger that has sliding piston " is simple in structure, and nozzle is half the by stator blade, and second half is made up of no leaf air flue.Adjustable area only has or not the leaf air flue, and this is half the, and certain adjustable area 50% has been enough, but its aeroperformance is bad.When no leaf passage is opened, air-flow will flow through from blade path and no leaf passage simultaneously, because the flow angle of two passages is inequality, the air turbulence with causing behind the nozzle increases the air current flow loss, reduction turbine heat efficient.
By the variable-nozzle structure that the special energetics of Britain's Hall plug Co., Ltd puts forward, on the fixed nozzle blade, to adorn a screen and close circle, mobile screen closes circle can cover the portion nozzle runner, reaches the purpose in adjustable nozzle cross section.Its shortcoming covers the portion nozzle runner and must cause from the air turbulence of volute to nozzle inlet as alternative plan, can reduce turbine heat efficient equally.
Summary of the invention
The technical problem that the present invention will solve is to overcome existing defective, and the turbosupercharger of double-leaf nozzle system is provided.Along new blade is set in the nozzle flow channel, can reduce channel cross-sectional area, be separated into two air flues to former nozzle again, to reduce the loss of air-flow lateral flow.Air-flow is still moving by intrinsic best air-flow angular flux simultaneously, can keep turbine in efficient district's work.
In order to solve the problems of the technologies described above, the invention provides following technological scheme:
The turbosupercharger of double-leaf nozzle system comprises turbine casing, fixed nozzle ring, straight line moving nozzle dish, mesochite, tooth bar, rocking lever, gear; Said fixed nozzle ring front-end face has one group of stator blade, and it is shaped as airfoil, has the leaf type hole between the stator blade; In the middle of the fixed nozzle ring center hole is arranged, be sleeved on the mesochite outer ring, and pass through screw on mesochite; Fixed nozzle ring rear end is equipped with straight line moving nozzle dish, and straight line moving nozzle dish front-end face has one group of moving blade, and the shape of moving blade is consistent with the shape in leaf type hole; Moving blade is inserted in the leaf type hole versatilely, in the middle of the straight line moving nozzle dish center hole is arranged, and is sleeved on the mesochite outer ring; Straight line moving nozzle back-end disk face is fixedly connected with two rocking levers, and rocking lever inserts in the mesochite, and the rocking lever end has tooth; Be meshed with a tooth bar through gear, tooth bar is connected with drive unit.
Further, the flow inlet angle scope of said blade is 18-24 °.
Further, stator blade quantity is 4-11, and moving blade quantity is 4-11.
Further, the drive unit of connection tooth bar is pneumatic actuator or solenoid valve.
The turbosupercharger of double-leaf nozzle system of the present invention can reduce channel cross-sectional area along new blade is set in the nozzle flow channel, is separated into two air flues to former nozzle again, to reduce the loss of air-flow lateral flow.Air-flow is still moving by intrinsic best air-flow angular flux simultaneously, can keep turbine in efficient district's work.Moving blade and stator blade are equidirectional along air-flow, can avoid as alternative plan and third party's case, causing air turbulence, reduce flow resistance loss.Through the increase or the minimizing of adjustment blade quantity, reach the purpose of regulation and control exit area of nozzle.When moving blade all gets in the stator blade, the long-pending slip of its cross section of fluid channel can be adjusted with wing thickness, can satisfy the needs of motor variable working condition.Its vane thickness of different turbosupercharger is different, to adapt to actual demand.
Description of drawings
Accompanying drawing is used to provide further understanding of the present invention, and constitutes the part of specification, is used to explain the present invention with embodiments of the invention, is not construed as limiting the invention.In the accompanying drawings:
Fig. 1 is the structural representation of the turbosupercharger of double-leaf nozzle system of the present invention;
Fig. 2 is a straight line moving nozzle dish structural representation of the present invention,
Fig. 3 is the structural representation of fixed nozzle ring of the present invention;
Fig. 4 is the schematic side view of fixed nozzle ring of the present invention;
Fig. 5 is the assembling schematic representation of straight line moving nozzle dish of the present invention and rocking lever;
Fig. 6 is the structural representation of rocking lever of the present invention;
Fig. 7 is the structural representation of tooth bar of the present invention;
Fig. 8 is the side-looking structural representation of gear of the present invention;
Fig. 9 is the main TV structure schematic representation of gear of the present invention;
Figure 10 is the assembling schematic representation of straight line moving nozzle dish of the present invention, fixed nozzle ring and rocking lever,
Figure 11 is the technical Analysis schematic representation of first scheme in the background technique.
Embodiment
Below in conjunction with accompanying drawing the preferred embodiments of the present invention are described, should be appreciated that preferred embodiment described herein only is used for explanation and explains the present invention, and be not used in qualification the present invention.
Embodiment one
The quantity of getting stator blade 8 is 8, and the quantity of moving blade 7 is 8, and the blade flow inlet angle is that established angle is 21 °.
Like Fig. 1,4, shown in 10; Fixed nozzle ring 1 front-end face has one group of stator blade 8, and it is shaped as airfoil, has leaf type hole 9 between the stator blade 8; Center hole is arranged in the middle of the fixed nozzle ring 1; Be sleeved on mesochite 5 outer rings, and pass through screw on mesochite 5, fixed nozzle ring 1 rear end is equipped with straight line moving nozzle dish 2.
Like Fig. 2, shown in 10, straight line moving nozzle dish 2 front-end faces have one group of moving blade 7, and the shape of moving blade 7 is consistent with the shape in leaf type hole 9, and moving blade 7 is inserted in the leaf type hole 9 versatilely.
Like Fig. 1,5,6, shown in 10; Two rocking levers 3 are passed through screw at straight line moving nozzle dish 2 ear end faces; The moving blade 7 of straight line moving nozzle dish 2 front-end faces is penetrated in the leaf type hole 9 of fixed nozzle ring 1, fixed nozzle ring 1 and straight line moving nozzle dish 2 are sleeved on mesochite 5 outer rings, and two rocking levers 3 are inserted in the hole of mesochite 5; The horizontal position at mesochite 5 oil back chamber edges is opened in the hole of mesochite 5, does not have interference with the oil return in the mesochite 5.Rocking lever 3 is terminal has a tooth, with tooth bar 4 through gear 6 engagements.
Like Fig. 1, shown in 3, four circular holes at fixed nozzle ring 1 middle part are aimed at the screw on the mesochite 5, and are fixedly connected with mesochite 5 with screw-driving.Through debugging, require moving blade 7 in the leaf type hole 9 of fixed nozzle ring 1, easily to slide.
The movable spacing scope of moving blade 7, the longest position: flush with stator blade 8 front ends; The shortest position: flush with the ear end face of fixed nozzle ring 1.
Like Fig. 6,7,8, shown in 9, there is tooth at tooth bar 4 two ends, and the end of rocking lever 3 has tooth; Pneumatic actuator promotes tooth bar 4 and moves up and down; Because tooth bar 4 and gear 6 engagements, thereby driven gear 6 rotates, and meshes because of gear 6 and rocking lever 3 terminal teeth again; Thereby drive rocking lever 3 side-to-side movements; rocking lever 3 and straight line moving nozzle dish 2 are connected through screw, and then drive straight line moving nozzle dish 2 move left and right, the interior or action withdrawed from the leaf type hole 9 in realization moving blade 7 insertion leaf type holes 9.
According to engine operating condition variation needs, move straight line moving nozzle dish 2, make moving blade 7 progress in the fixed nozzle ring 1, until whole entering, then nozzle vane quantity increases; Perhaps make moving blade 7 withdraw from fixed nozzle ring 1 gradually, move to the ear end face of fixed nozzle ring 1 until the front-end face of moving blade 7, then nozzle vane quantity reduces.Through the increase or the minimizing of adjustment blade quantity, reach the purpose of regulation and control exit area of nozzle.
The turbosupercharger of double-leaf nozzle system of the present invention can reduce channel cross-sectional area along new blade is set in the nozzle flow channel, is separated into two air flues to former nozzle again, to reduce the loss of air-flow lateral flow.Air-flow is still moving by intrinsic best air-flow angular flux simultaneously, can keep turbine in efficient district's work.Moving blade and stator blade are equidirectional along air-flow, can avoid as alternative plan and third party's case, causing air turbulence, reduce flow resistance loss.Through the increase or the minimizing of adjustment blade quantity, reach the purpose of regulation and control exit area of nozzle.When moving blade all gets in the stator blade, the long-pending slip of its cross section of fluid channel can be adjusted with wing thickness, can satisfy the needs of motor variable working condition.Its vane thickness of different turbosupercharger is different, to adapt to actual demand.
Embodiment two
Present embodiment and embodiment's one difference is: the drive unit that the promotion tooth bar moves up and down is a solenoid valve.
What should explain at last is: the above is merely the preferred embodiments of the present invention; Be not limited to the present invention; Although the present invention has been carried out detailed explanation with reference to previous embodiment; For a person skilled in the art, it still can be made amendment to the technological scheme that aforementioned each embodiment put down in writing, and perhaps part technical characteristics wherein is equal to replacement.All within spirit of the present invention and principle, any modification of being done, be equal to replacement, improvement etc., all should be included within protection scope of the present invention.

Claims (4)

1. the turbosupercharger of double-leaf nozzle system comprises turbine casing, it is characterized in that: comprise fixed nozzle ring, straight line moving nozzle dish, mesochite, tooth bar, rocking lever, gear,
Said fixed nozzle ring front-end face has one group of stator blade, and it is shaped as airfoil, has the leaf type hole between the stator blade, in the middle of the fixed nozzle ring center hole is arranged, and is sleeved on the mesochite outer ring, and passes through screw on mesochite,
Fixed nozzle ring rear end is equipped with straight line moving nozzle dish, and straight line moving nozzle dish front-end face has one group of moving blade, and the shape of moving blade is consistent with the shape in leaf type hole; Moving blade is inserted in the leaf type hole versatilely, in the middle of the straight line moving nozzle dish center hole is arranged, and is sleeved on the mesochite outer ring; Straight line moving nozzle back-end disk face is fixedly connected with two rocking levers, and rocking lever inserts in the mesochite, and the rocking lever end has tooth; Be meshed with a tooth bar through gear, tooth bar is connected with drive unit.
2. the turbosupercharger of double-leaf nozzle system according to claim 1 is characterized in that: the flow inlet angle scope of said blade is 18-24 °.
3. the turbosupercharger of double-leaf nozzle system according to claim 1 is characterized in that: stator blade quantity is 4-11, and moving blade quantity is 4-11.
4. the turbosupercharger of double-leaf nozzle system according to claim 1 is characterized in that: the drive unit that connects tooth bar is a solenoid valve.
CN2011102331062A 2011-08-15 2011-08-15 Turbocharger for double-vane nozzle systems Active CN102297016B (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
CN2011102331062A CN102297016B (en) 2011-08-15 2011-08-15 Turbocharger for double-vane nozzle systems
JP2014525285A JP6116564B2 (en) 2011-08-15 2012-08-15 Turbocharger with dual vane nozzle system
CA2833790A CA2833790C (en) 2011-08-15 2012-08-15 Turbocharger with dual-blade nozzle system
DE112012001868.0T DE112012001868B4 (en) 2011-08-15 2012-08-15 Turbocharger with double vane nozzle system
PCT/CN2012/001087 WO2013023441A1 (en) 2011-08-15 2012-08-15 Turbocharger with dual-blade nozzle system
US14/009,070 US20140086725A1 (en) 2011-08-15 2012-08-15 Turbocharger with a double-vane nozzle system

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Application Number Priority Date Filing Date Title
CN2011102331062A CN102297016B (en) 2011-08-15 2011-08-15 Turbocharger for double-vane nozzle systems

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CN102297016A CN102297016A (en) 2011-12-28
CN102297016B true CN102297016B (en) 2012-12-12

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US (1) US20140086725A1 (en)
JP (1) JP6116564B2 (en)
CN (1) CN102297016B (en)
CA (1) CA2833790C (en)
DE (1) DE112012001868B4 (en)
WO (1) WO2013023441A1 (en)

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CN101949305A (en) * 2010-09-07 2011-01-19 康跃科技股份有限公司 Turbocharger composite nozzle device
CN202181948U (en) * 2011-08-15 2012-04-04 无锡凯迪增压器配件有限公司 Turbine supercharger for double-blade spray nozzle system

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US20140086725A1 (en) 2014-03-27
CA2833790A1 (en) 2013-02-21
JP6116564B2 (en) 2017-04-19
CN102297016A (en) 2011-12-28
DE112012001868T5 (en) 2014-02-06
JP2014521881A (en) 2014-08-28
WO2013023441A1 (en) 2013-02-21
CA2833790C (en) 2016-09-20
DE112012001868B4 (en) 2023-07-06

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Denomination of invention: Turbocharger for double-vane nozzle systems

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