WO2015118562A2 - Aube perfectionnée pour turbocompresseurs à géométrie de turbine variable - Google Patents

Aube perfectionnée pour turbocompresseurs à géométrie de turbine variable Download PDF

Info

Publication number
WO2015118562A2
WO2015118562A2 PCT/IN2015/000074 IN2015000074W WO2015118562A2 WO 2015118562 A2 WO2015118562 A2 WO 2015118562A2 IN 2015000074 W IN2015000074 W IN 2015000074W WO 2015118562 A2 WO2015118562 A2 WO 2015118562A2
Authority
WO
WIPO (PCT)
Prior art keywords
vane
deflection
trailing edge
leading edge
line
Prior art date
Application number
PCT/IN2015/000074
Other languages
English (en)
Other versions
WO2015118562A3 (fr
Inventor
Yadagiri Rapolu Ganesh
Swaminathan B Siddharth
Subramani D.A.
Gopalakrishnan A
Original Assignee
Turbo Energy Limited
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 Turbo Energy Limited filed Critical Turbo Energy Limited
Publication of WO2015118562A2 publication Critical patent/WO2015118562A2/fr
Publication of WO2015118562A3 publication Critical patent/WO2015118562A3/fr

Links

Classifications

    • 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
    • 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
    • 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
    • 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
    • F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades

Definitions

  • This invention relates to a vane for variable turbine geometry turbochargers. More particularly, the present invention relates to an improved vane design that is applicable to aerodynamic vanes that are disposed within a variable geometry.
  • Turbochargers are widely used in internal combustion engines. They are a type of forced induction system. They deliver compressed air to the engine intake, allowing more fuel to be combusted, thus boosting the engine's horsepower without significantly increasing engine weight. Turbochargers use the exhaust flow from the engine to drive a turbine, which is mechanically connected to a compressor. Turbochargers, which utilize some form of turbine flow and pressure control are called by several names and offer control though various means. Some have rotating vanes, some have sliding sections or rings. Some titles for these devices are: Variable turbine geometry(VTG), Variable geometry turbine (VGT) variable nozzle turbine (VNT), or simply variable geometry (VG).
  • VVTG Variable turbine geometry
  • VNT Variable geometry turbine
  • VNT variable nozzle turbine
  • VG simply variable geometry
  • VTG turbochargers utilize adjustable guide vanes that are rotatably connected to a pair of vane rings and/or the nozzle wall. These vanes are adjusted to control the exhaust gas backpressure and the turbocharger speed by modulating the exhaust gas flow to the turbine wheel.
  • the efficiency of turbine in VTG turbocharger depends on various factors such as flow incidence angle at the turbine inlet, pressure drop across the guide vanes and uniformity of gas distribution entering the turbine.
  • the vane disclosed in PCT/US2003/027529 is designed in an asymmetric shape in a way that the vane has been characterized as concave or convex relative to the interior to the vane and is defined by a continuous curve to increase the aerodynamic efficiency of gas flow.
  • This vane consists of a gradual curve that starts at a point between about 5 to 40 percent of the initial vane length and gradually increases to a maximum point between about 40 to 80 percent of the initial vane length then gradually decreases back to zero at or before the end of the vane length.
  • the flat portions near start of the vane length and end of the vane length are introduced to achieve positive torque due to increase in drag.
  • Such a configuration requires flow over the vane to turn 2 to 3 times according to the vane profile.
  • the vane disclosed in US patent application number 12/812499 is designed such that the line of curvature of the guide vane has at least one or more than one sector having a discontinuous course to increase the aerodynamic efficiency of gas flow.
  • the vane disclosed has at least one discontinuous section, this may leads to local flow recirculation near the discontinuity which will case local pressure drop, thereby affecting the overall efficiency of the turbine There is therefore a need in the art for an improved turbocharger vane to overcome the above mentioned problems.
  • the present invention as embodied by an improved vane for variable turbine geometry turbocharger, succinctly fulfils the above-mentioned need(s) in the art.
  • the present invention has objective(s) arising as a result of the above-mentioned need(s), said objective(s) being enumerated below.
  • the objective(s) of the present invention are enumerated, it will be obvious to a person skilled in the art that, the enumerated objective(s) are not exhaustive of the present invention in its entirety, and are enclosed solely for the purpose of illustration.
  • the present invention encloses within its scope and purview, any structural alternative(s) and/or any functional equivalent(s) even though, such structural alternative(s) and/or any functional equivalent(s) are not mentioned explicitly herein or elsewhere, in the present disclosure.
  • the present invention therefore also encompasses, any improvisation(s)/modification(s) applied to the structural alternative(s)/functional alternative(s) within its scope and purview.
  • the present invention may be embodied in other specific form(s) without departing from the spirit or essential attributes thereof.
  • Yet another objective of the present invention is to provide an improved vane for variable turbine geometry turbocharger in which the efficiency of the turbine is increased by eliminating conventional local flow recirculation.
  • the present invention as embodied by an improved vane for variable turbine geometry turbocharger, succinctly fulfils the objective(s) of the present invention as broadly enumerated in the present disclosure.
  • the objectives are only indicative of the scope and general coverage of the present invention.
  • a vane comprises two different edges-a leading edge and a trailing edge, two different lines- a first line that splits the vane into two parts and a second line that is a straight line that connects the leading edge with the trailing edge, two different airfoils- an outer airfoil associated with both the leading edge and the trailing edge and an inner airfoil associated with both the leading edge and the trailing edge, and has a certain radial thickness.
  • the vane is rotated to open or close at different operating conditions about a pivot point.
  • the first line and the second line of the vane may or may not intersect with each other.
  • An improved vane is characterized by one or more points of deflection and corresponding angles of deflection that split the vane into a plurality of sections, wherein the plurality of sections are continuous in nature.
  • the one or more points of deflection can lie anywhere within the conventional vane.
  • the improved vane is formed by bending or rotating the trailing edge of the conventional vane towards the turbine wheel about every single point of deflection by a corresponding angle of deflection, wherein the angle of deflection is greater than 4° and less than 60°. This results in two portions being formed-a trailing edge portion and leading edge portion. After the trailing edge is rotated, the part of the trailing edge portion and the part of the leading edge portion falling near the bend are discarded and one or more arcs are constructed to join the leading edge portion and the trailing edge portion and complete the inner airfoil and the outer airfoil surfaces for the improved vane.
  • the one or more arcs constructed on the inner airfoil and the outer airfoil are maintained tangential between the leading edge portion and the trailing edge portion for smooth flow of gas.
  • the ratio of the length of leading edge portion and the length of second line, with respect to every single point of deflection is maintained between 0.1 and 0.9.
  • FIG. 2 illustrates one embodiment of an improved vane for turbocharger in accordance with the present invention.
  • Figure 3 illustrates the region of deflection, point of deflection and angle of deflection to form the improved vane for turbocharger.
  • Figures 4(a), 4(b) and 4(c) illustrates some other embodiments of the improved vane for turbocharger in accordance with the present invention with respect to different points of deflections and different angles of deflections.
  • the primary vane (100) comprises two different edges-a leading edge (101) and a trailing edge (102), two different lines- a first line (105) that splits the vane into two parts and a second line (203) that is a straight line that connects the leading edge (101) with the trailing edge (102), two different airfoils- an outer airfoil (103) associated with both the leading edge (101) and the trailing edge (102) and an inner airfoil (104) associated with both the leading edge (101) and the trailing edge (102), and has a certain radial thickness (106).
  • the primary vane (100) is rotated to open or close at different operating conditions about a pivot point (107).
  • the first line (105) and the second line (203) of the primary vane (100) may or may not intersect with each other.
  • An improved vane is (200) depicted in Figures 2 and 3.
  • the improved vane (200) is characterized by one or more points of deflection (201) and corresponding angles of deflection (202) that split the vane into a plurality of sections, wherein the plurality of sections are continuous in nature.
  • the improved vane (200) can have a maximum of 3 points of deflections (201).
  • the one or more points of deflection (201) can lie anywhere with the primary vane (100) or outside the primary vane (100).
  • the improved vane (200) is formed by bending or rotating the trailing edge (102) of the primary vane (100) towards the turbine wheel about every single point of deflection (201) by a corresponding angle of deflection (202), wherein the angle of deflection is greater than 4° and less than 60°, as illustrated in Figure 3.
  • the part of the trailing edge portion (206) and the part of the leading edge portion (205) falling near the bend are discarded and one or more arcs are constructed to join the leading edge portion (205) and the trailing edge portion (206) and complete the inner airfoil (104) and the outer airfoil (105) surfaces for the improved vane (200).
  • the one or more arcs constructed on the inner airfoil (104) and the outer airfoil (105) are maintained tangential between the leading edge portion (205) and the trailing edge portion (206) for smooth flow of gas.
  • the region where the bend or rotation takes place in the improved vane (200) is illustrated as a region of deflection (204) in Figure 3.
  • the improved vane (200) in different embodiments with different points of deflection (201) and different angles of deflection (202) are illustrated in Figures 4(a), 4(b) and 4(c).
  • the length from the point of deflection (201) to the leading edge (101) is illustrated as (207) and the length from point of deflection (201) to the trailing edge (202) is (208).
  • the ratio of the length from point of deflection (201) to the leading edge (101), and the length of the second line (203), with respect to every single point of deflection (201 ) is maintained between 0.1 and 0.9.
  • the length from the point of deflection (201) to the leading edge (101), and the length from point of deflection (201) to the trailing edge (102) should be greater than or equal to 2mm.
  • the first line and the second line do not intersect at all.
  • the first line of the improved vane is not a continuous curve; it can be any combination of continuous sections such as "straight line - arc - straight line” or "arc-arc-straight line”.
  • the vane (200) described and illustrated in Figures 2 and 3 is derived from a symmetric vane. But, the concept explained herein can also be applied to asymmetric vanes as well. Moreover, the leading edge portion (205) and trailing edge portion (206) required to create the improved vane airfoil can be borrowed even from different primary vanes.
  • the improved vane has a lower turbine inlet flow angle and lower pressure drop when compared with the primary vane and thus has a higher efficiency. Greater controllability can be achieved by adjusting the one or more points of deflection and corresponding angles of deflection.
  • the improved vane has no local flow recirculation problem and thus the efficiency of the turbine is high.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Architecture (AREA)
  • Supercharger (AREA)

Abstract

Aubes utilisées dans le turbocompresseur comprenant un bord d'attaque, un bord de fuite, un profil aérodynamique interne et un profil aérodynamique externe. Les profils aérodynamiques interne et externe sont tous les deux associés au bord d'attaque et au bord de fuite. Une aube perfectionnée de la présente invention est formée par la rotation du bord de fuite de l'aube vers la roue de turbine autour d'un point de déviation d'un angle de déviation. Une fois que le bord de fuite a tourné, la partie de la partie bord de fuite et la partie de la partie bord d'attaque tombant près du coude sont écartées et un ou plusieurs arcs sont construits de façon à relier les parties et à achever les surfaces de profil aérodynamique interne et de profil aérodynamique externe pour l'aube perfectionnée. Le ou les arcs construits sur le profil aérodynamique interne et le profil aérodynamique externe sont maintenus de manière tangentielle entre la partie bord d'attaque et la partie bord de fuite pour un écoulement de gaz régulier.
PCT/IN2015/000074 2014-02-07 2015-02-06 Aube perfectionnée pour turbocompresseurs à géométrie de turbine variable WO2015118562A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IN565/CHE/2014 2014-02-07
IN565CH2014 2014-02-07

Publications (2)

Publication Number Publication Date
WO2015118562A2 true WO2015118562A2 (fr) 2015-08-13
WO2015118562A3 WO2015118562A3 (fr) 2015-12-10

Family

ID=53778574

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IN2015/000074 WO2015118562A2 (fr) 2014-02-07 2015-02-06 Aube perfectionnée pour turbocompresseurs à géométrie de turbine variable

Country Status (1)

Country Link
WO (1) WO2015118562A2 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3783209A4 (fr) * 2018-11-13 2021-03-03 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Aube de distributeur
CN115717604A (zh) * 2022-09-28 2023-02-28 广东顺威精密塑料股份有限公司 一种带襟叶的后向离心风轮及其叶片叶型设计方法

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19936507A1 (de) * 1999-08-05 2001-02-15 3K Warner Turbosystems Gmbh Turbinenleitschaufel für einen Abgas-Turbolader
US6419464B1 (en) * 2001-01-16 2002-07-16 Honeywell International Inc. Vane for variable nozzle turbocharger

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3783209A4 (fr) * 2018-11-13 2021-03-03 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Aube de distributeur
CN115717604A (zh) * 2022-09-28 2023-02-28 广东顺威精密塑料股份有限公司 一种带襟叶的后向离心风轮及其叶片叶型设计方法

Also Published As

Publication number Publication date
WO2015118562A3 (fr) 2015-12-10

Similar Documents

Publication Publication Date Title
US6709232B1 (en) Cambered vane for use in turbochargers
US7255530B2 (en) Vane and throat shaping
US8360730B2 (en) Turbine wheel with backswept inducer
US20150016968A1 (en) Mixed-flow turbocharger with variable turbine geometry
US10808569B2 (en) Turbocharger
EP3231996B1 (fr) Aube pour une machine à flux axial
US20100296924A1 (en) Guide Vane for a Variable Turbine Geometry
JP5850968B2 (ja) 不均一に分布させられた翼と均一なスロート面積とを備えたノズルリング
US20120076646A1 (en) Steam Turbine Stator Vane and Steam Turbine Using the Same
CN101103178A (zh) 可变喷嘴涡轮增压器
US8197195B2 (en) Turbocharger with stepped two-stage vane nozzle
EP2105583B1 (fr) Turbocompresseur à piston coulissant et des aubes directrices avec des barrières anti-fuite
US9995166B2 (en) Turbomachine including a vane and method of assembling such turbomachine
US11125085B2 (en) Blade of fan or compressor
CN109844263B (zh) 涡轮机叶轮、涡轮机及涡轮增压器
US20210372288A1 (en) Compressor stator with leading edge fillet
WO2015118562A2 (fr) Aube perfectionnée pour turbocompresseurs à géométrie de turbine variable
JP5201333B2 (ja) 可変ノズルのベーン形状及び可変容量過給機
US10208619B2 (en) Variable low turbine vane with aft rotation axis
US11208894B2 (en) Turbine wheel
KR20180038615A (ko) 터보차처의 노즐 베인

Legal Events

Date Code Title Description
NENP Non-entry into the national phase in:

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 15746874

Country of ref document: EP

Kind code of ref document: A2