US20020094284A1 - Vane for variable nozzle turbocharger - Google Patents
Vane for variable nozzle turbocharger Download PDFInfo
- Publication number
- US20020094284A1 US20020094284A1 US09/761,277 US76127701A US2002094284A1 US 20020094284 A1 US20020094284 A1 US 20020094284A1 US 76127701 A US76127701 A US 76127701A US 2002094284 A1 US2002094284 A1 US 2002094284A1
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- Prior art keywords
- vane
- post
- vanes
- turbine
- unison ring
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- 230000007246 mechanism Effects 0.000 description 8
- 230000006735 deficit Effects 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000005266 casting Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000002195 synergetic effect Effects 0.000 description 1
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Classifications
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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
- F02B37/12—Control of the pumps
- F02B37/22—Control of the pumps by varying cross-section of exhaust passages or air passages, e.g. by throttling turbine inlets or outlets or by varying effective number of guide conduits
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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
- 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
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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
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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
- 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
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
- F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
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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
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
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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
- F05D2250/00—Geometry
- F05D2250/40—Movement of components
- F05D2250/41—Movement of components with one degree of freedom
- F05D2250/411—Movement of components with one degree of freedom in rotation
Definitions
- This invention relates generally to the field of variable geometry turbochargers and, more particularly, to an improved vane design for a plurality of pivoting aerodynamic vanes disposed within a turbine housing of a variable nozzle turbocharger to provide improved vane operation and extended vane/turbocharger service life.
- Turbochargers for gasoline and diesel internal combustion engines are devices known in the art that are used for pressurizing or boosting the intake air stream, routed to a combustion chamber of the engine, by using the heat and volumetric flow of exhaust gas exiting the engine.
- the exhaust gas exiting the engine is routed into a turbine housing of a turbocharger in a manner that causes an exhaust gas-driven turbine to spin within the housing.
- the exhaust gas-driven turbine is mounted onto one end of a shaft that is common to a radial air compressor mounted onto an opposite end of the shaft and housed in a compressor housing.
- rotary action of the turbine also causes the air compressor to spin within a compressor housing of the turbocharger that is separate from the turbine housing.
- the spinning action of the air compressor causes intake air to enter the compressor housing and be pressurized or boosted a desired amount before it is mixed with fuel and combusted within the engine combustion chamber.
- variable geometry turbochargers have been configured to address this need.
- a type of such variable geometry turbocharger is one having a variable exhaust nozzle, referred to as a variable nozzle turbocharger.
- Different configurations of variable nozzles have been employed in variable nozzle turbochargers to control the exhaust gas flow.
- One approach taken to achieve exhaust gas flow control in such variable nozzle turbochargers involves the use of multiple pivoting vanes that are positioned annularly around the turbine inlet. The pivoting vanes are commonly controlled to alter the throat area of the passages between the vanes, thereby functioning to control the exhaust gas flow into the turbine.
- Known multiple vane variable nozzle turbochargers include vanes that are each configured having a shaft projecting outwardly therefrom, each such shafted being positioned within a respective shaft opening in a turbine housing or nozzle wall. While the vanes are commonly actuated to pivot vis-a-vis their shafts within the respective openings, it has been discovered that such conventional vane attachment and pivoting mechanism is not without its problems.
- a vane pivoting mechanism be constructed, for use with a variable nozzle turbocharger, in a manner that provides improved vane operational reliability when compared to conventional vane pivoting mechanisms.
- a variable geometry turbocharger incorporating the present invention includes a turbine housing having an inlet for exhaust gas and an outlet, a volute connected to the inlet, and an integral outer nozzle wall adjacent the volute.
- a turbine wheel is carried within the turbine housing and attached to a shaft.
- a plurality of vanes are disposed within the turbine housing, each vane having a hole extending into the vane through an axial vane surface substantially parallel to the outer nozzle wall, each vane hole receiving a respective post projecting outwardly from the outer nozzle wall, the vanes further having actuation tabs extending from an axial vane surface opposite from the holes.
- An annular unison ring is positioned axially adjacent the vanes, the unison ring having a plurality of slots that each accommodate a respective tab therein. Te unison ring is rotated to effect movement of the tabs within respective slots by pivoting movement of the vanes on the posts, wherein such movement of the tabs within the slots causes the vanes to move radially relative to the turbine wheel shaft.
- FIG. 1 is an exploded isometric view of a turbine housing for a variable geometry turbocharger employing conventional vanes
- FIG. 2 is a top view of the unison ring and slots showing the engagement with the tabs on the vanes;
- FIG. 3 is a detailed view of a vane and post incorporating the present invention
- FIG. 4 is a detailed view of a vane and tab incorporating the present invention.
- FIG. 5 is a detailed view of a vane incorporating the present invention showing the internal elements of the vane.
- a variable geometry or variable nozzle turbocharger generally comprises a center housing having a turbine housing attached at one end, and a compressor housing attached at an opposite end.
- a shaft is rotatably disposed within a bearing assembly contained within the center housing.
- a turbine or turbine wheel is attached to one shaft end and is carried within the turbine housing, and a compressor impeller is attached to an opposite shaft end and is carried within the compressor housing.
- the turbine and compressor housings are attached to the center housing by bolts that extend between the adjacent housings.
- FIG. 1 illustrates a portion of a known variable nozzle turbocharger 10 comprising a turbine housing 12 having a standard inlet 14 for receiving an exhaust gas stream, and an outlet 16 for directing exhaust gas to the exhaust system of the engine.
- a volute is connected to the exhaust inlet and an integral outer nozzle wall is incorporated in the turbine housing casting adjacent the volute.
- a turbine wheel and shaft assembly 18 is carried within the turbine housing. Exhaust gas, or other high energy gas supplying the turbocharger, enters the turbine through the inlet and is distributed through the volute in the turbine housing for substantially radial entry into the turbine wheel through a circumferential nozzle entry 20 .
- vanes 22 are mounted to a nozzle wall 24 machined into the turbine housing using shafts 26 that project perpendicularly outwardly from the vanes.
- the shafts 26 are rotationally engaged within respective openings 28 in the nozzle wall.
- the vanes each include actuation tabs 30 that project from a side opposite the shafts and that are engaged by respective slots 32 in a unison ring 34 , which acts as a second nozzle wall.
- An actuator assembly is connected with the unison ring and is configured to rotate the ring in one directed or the other as necessary to move the vanes radially, with respect to an axis of rotation of the turbine wheel, outwardly or inwardly to respectively increase or decrease the flow of exhaust gas to the turbine.
- the vane tabs 30 are caused to move within their respective slot 32 from one slot end to an opposite slot end. Since the slots are oriented with a radial directional component along the unison ring, the movement of the vane tabs within the respective slots causes the vanes to pivot via rotation of the vane shafts within their respective openings and open or close the nozzle area depending on the unison ring rotational direction.
- variable nozzle turbochargers comprising such elements is disclosed in U.S. patent application Ser. No. 09/408,694 filed Sep. 30, 1999 entitled VARIABLE GEOMETRY TURBOCHARGER, having a common assignee with the present application, which is incorporated herein by reference.
- FIG. 2 illustrates the general movement pattern of vanes 36 when actuated by the unison ring.
- This movement pattern is generally the same for both known vane configurations and vane configurations prepared according to principles of this invention as used with variable nozzle turbochargers.
- Each vane tab 42 is disposed within a respective elongated slot 38 of a unison ring 40 .
- a closed position “A” the vane tab 42 is positioned adjacent a first end 44 of the slot 38 .
- This position is referred to as a closed position because the vane is not flared radially outward, thereby serving to limit the flow of exhaust gas to the turbine.
- the unison ring 40 has been rotated a sufficient amount such that the vane tab 42 is moved within the slot 38 away from the first slot end 44 towards a middle position of the slot.
- the vane tab movement is provided by the pivoting action of the vane relative to the nozzle wall, allowing the vane to be rotated a given extent.
- variable nozzle turbochargers comprising the multiple vanes as described above and illustrated in FIG. 1, requires that the vanes be permitted to pivot freely vis-a-vis the nozzle wall when actuated by the unison ring.
- Such free pivoting movement requires that the vane shafts not bind or otherwise be restricted in their rotational movement within their respective nozzle holes.
- the known vane design can produce impairments to free pivoting vane movement if the shafts projecting from the vanes are not perfectly perpendicular. Additionally, the known vane designs can produce an impairment to free pivoting vane movement by the relatively high cantilever load stress imposed on the vane by virtue of the vane shaft and hole attachment mechanism.
- FIGS. 3 to 5 illustrate a vane 50 for use with a variable nozzle turbocharger, constructed according to principles of this invention, comprising an upper or low pressure airfoil surface 52 , an opposite high pressure airfoil surface 54 , and axial surfaces 56 and 58 . These vane surfaces are defined relative to the vane placement within the turbine housing.
- the vane 50 includes a leading edge 60 and a trailing edge 62 at opposite common ends of the high and low pressure airfoil surfaces 52 and 54 .
- the vane includes a tab 64 projecting outwardly away from the axial surface 58 and positioned adjacent the leading edge 60 . The tab is configured to cooperate with a unison ring slot in the manner described above to facilitate vane actuation.
- vanes 50 constructed according to the practice of this invention do not include a shaft. Rather, the vanes of this invention are designed having a hole 64 extending through the axial surface 56 that is sized and configured to accommodate placement of a respective post 68 therein (see FIG, 3 ), wherein the post projects perpendicularly outwardly away from the turbine housing nozzle wall. Configured in this manner, vane pivoting movement vis-a-vis the nozzle wall is provided by the relative rotational motion between the fixed post and the hole in the vane.
- the pivoting mechanism provided by the fixed wall post disposed in the rotatable vane hole reduces the amount of cantilever load stress on the vane, when compared to known vane designs and attachment mechanisms, thereby serving to reduce and/or eliminate potential impairments to efficient vane movement and operation.
- Each post 68 is configured to be attached to the nozzle wall by press fit or other conventional attachment method, and is positioned within the nozzle wall in a substantially circular pattern the coincides with the desired spaced apart vane arrangement.
- the post 68 is configured having a stepped design with two different diameters, wherein a first enlarged diameter section 70 is sized and configured to provide a secure press fit attachment within the nozzle wall, and wherein a second reduced diameter section 72 is sized and configured to project outwardly from the nozzle wall and fit within the vane hole 66 to provide rotational movement thereupon.
- the vane 50 is configured having a thickness, as measured between the high and low pressure airfoil surfaces 52 and 54 , that is greater than known vane designs, to accommodate a sufficiently strong post without compromising the structural integrity of the vane.
- An unexpected and synergistic effect of increasing the vane thickness to accommodate the nozzle wall post is the realization of a wider area turndown ratio for a fixed rotation of the vane, when compared to turbochargers comprising the conventional prior art vanes. Therefore, vanes of this invention can provide a greater aerodynamic flow range for a fixed efficiency level than that of turbochargers comprising known vane designs.
- the vane can be formed from the same types of materials, and in the same manner, as that used to form conventional prior art vanes.
- the vanes have a substantially solid design or are alternatively configured having a cored out design.
- the vane axial surfaces 56 and 58 are configured having a cored out design.
- the cored out design is preferred as it has been found to provide better formability, a higher stiffness to weight ratio, be more cost effective to produce, and have a reduced mass when compared to conventional prior art vanes.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Supercharger (AREA)
- Control Of Turbines (AREA)
Abstract
Description
- This invention relates generally to the field of variable geometry turbochargers and, more particularly, to an improved vane design for a plurality of pivoting aerodynamic vanes disposed within a turbine housing of a variable nozzle turbocharger to provide improved vane operation and extended vane/turbocharger service life.
- Turbochargers for gasoline and diesel internal combustion engines are devices known in the art that are used for pressurizing or boosting the intake air stream, routed to a combustion chamber of the engine, by using the heat and volumetric flow of exhaust gas exiting the engine. Specifically, the exhaust gas exiting the engine is routed into a turbine housing of a turbocharger in a manner that causes an exhaust gas-driven turbine to spin within the housing. The exhaust gas-driven turbine is mounted onto one end of a shaft that is common to a radial air compressor mounted onto an opposite end of the shaft and housed in a compressor housing. Thus, rotary action of the turbine also causes the air compressor to spin within a compressor housing of the turbocharger that is separate from the turbine housing. The spinning action of the air compressor causes intake air to enter the compressor housing and be pressurized or boosted a desired amount before it is mixed with fuel and combusted within the engine combustion chamber.
- In a turbocharger it is often desirable to control the flow of exhaust gas to the turbine to improve the efficiency or operational range of the turbocharger. Variable geometry turbochargers have been configured to address this need. A type of such variable geometry turbocharger is one having a variable exhaust nozzle, referred to as a variable nozzle turbocharger. Different configurations of variable nozzles have been employed in variable nozzle turbochargers to control the exhaust gas flow. One approach taken to achieve exhaust gas flow control in such variable nozzle turbochargers involves the use of multiple pivoting vanes that are positioned annularly around the turbine inlet. The pivoting vanes are commonly controlled to alter the throat area of the passages between the vanes, thereby functioning to control the exhaust gas flow into the turbine.
- In order to ensure the proper and reliable operation of such variable nozzle turbochargers, it is important that the individual vanes be configured and assembled within the turbine housing to move or pivot freely in response to a desired exhaust gas flow control actuation. Because these pivoting vanes are subjected to millions of high temperature cycles during turbocharger operation it is necessary that any such pivoting mechanism be one that is capable of repeatably functioning under such cycled temperature conditions without enduring any cycled temperature related material or mechanical problem or failure.
- Known multiple vane variable nozzle turbochargers include vanes that are each configured having a shaft projecting outwardly therefrom, each such shafted being positioned within a respective shaft opening in a turbine housing or nozzle wall. While the vanes are commonly actuated to pivot vis-a-vis their shafts within the respective openings, it has been discovered that such conventional vane attachment and pivoting mechanism is not without its problems.
- For example, in order to ensure freely pivoting movement of the vane shaft with the opening it is essential that the shaft project perfectly perpendicularly from the vane, to thereby avoid undesired binding or otherwise impairment of the vane pivoting movement. Secondary straightening or machining operations are sometimes necessary to ensure the perpendicularity of the vane shafts., which secondary operations can be both time consuming and costly. Additionally, this type of vane attachment and pivoting mechanism can produce a high cantilevered load on the vane shaft when actuated that can also impair free vane pivoting movement, and that can ultimately result in a vane material or mechanical failure.
- It is, therefore, desirable that a vane pivoting mechanism be constructed, for use with a variable nozzle turbocharger, in a manner that provides improved vane operational reliability when compared to conventional vane pivoting mechanisms.
- A variable geometry turbocharger incorporating the present invention includes a turbine housing having an inlet for exhaust gas and an outlet, a volute connected to the inlet, and an integral outer nozzle wall adjacent the volute. A turbine wheel is carried within the turbine housing and attached to a shaft. A plurality of vanes are disposed within the turbine housing, each vane having a hole extending into the vane through an axial vane surface substantially parallel to the outer nozzle wall, each vane hole receiving a respective post projecting outwardly from the outer nozzle wall, the vanes further having actuation tabs extending from an axial vane surface opposite from the holes. An annular unison ring is positioned axially adjacent the vanes, the unison ring having a plurality of slots that each accommodate a respective tab therein. Te unison ring is rotated to effect movement of the tabs within respective slots by pivoting movement of the vanes on the posts, wherein such movement of the tabs within the slots causes the vanes to move radially relative to the turbine wheel shaft.
- The invention will be more clearly understood with reference to the following drawings wherein:
- FIG. 1 is an exploded isometric view of a turbine housing for a variable geometry turbocharger employing conventional vanes;
- FIG. 2 is a top view of the unison ring and slots showing the engagement with the tabs on the vanes;
- FIG. 3 is a detailed view of a vane and post incorporating the present invention;
- FIG. 4 is a detailed view of a vane and tab incorporating the present invention;
- FIG. 5 is a detailed view of a vane incorporating the present invention showing the internal elements of the vane.
- A variable geometry or variable nozzle turbocharger generally comprises a center housing having a turbine housing attached at one end, and a compressor housing attached at an opposite end. A shaft is rotatably disposed within a bearing assembly contained within the center housing. A turbine or turbine wheel is attached to one shaft end and is carried within the turbine housing, and a compressor impeller is attached to an opposite shaft end and is carried within the compressor housing. The turbine and compressor housings are attached to the center housing by bolts that extend between the adjacent housings.
- FIG. 1 illustrates a portion of a known
variable nozzle turbocharger 10 comprising aturbine housing 12 having astandard inlet 14 for receiving an exhaust gas stream, and anoutlet 16 for directing exhaust gas to the exhaust system of the engine. A volute is connected to the exhaust inlet and an integral outer nozzle wall is incorporated in the turbine housing casting adjacent the volute. A turbine wheel andshaft assembly 18 is carried within the turbine housing. Exhaust gas, or other high energy gas supplying the turbocharger, enters the turbine through the inlet and is distributed through the volute in the turbine housing for substantially radial entry into the turbine wheel through acircumferential nozzle entry 20. -
Multiple vanes 22 are mounted to anozzle wall 24 machined into the turbinehousing using shafts 26 that project perpendicularly outwardly from the vanes. Theshafts 26 are rotationally engaged withinrespective openings 28 in the nozzle wall. The vanes each includeactuation tabs 30 that project from a side opposite the shafts and that are engaged byrespective slots 32 in aunison ring 34, which acts as a second nozzle wall. - An actuator assembly is connected with the unison ring and is configured to rotate the ring in one directed or the other as necessary to move the vanes radially, with respect to an axis of rotation of the turbine wheel, outwardly or inwardly to respectively increase or decrease the flow of exhaust gas to the turbine. As the unison ring is rotated, the
vane tabs 30 are caused to move within theirrespective slot 32 from one slot end to an opposite slot end. Since the slots are oriented with a radial directional component along the unison ring, the movement of the vane tabs within the respective slots causes the vanes to pivot via rotation of the vane shafts within their respective openings and open or close the nozzle area depending on the unison ring rotational direction. An example of a known variable nozzle turbochargers comprising such elements is disclosed in U.S. patent application Ser. No. 09/408,694 filed Sep. 30, 1999 entitled VARIABLE GEOMETRY TURBOCHARGER, having a common assignee with the present application, which is incorporated herein by reference. - FIG. 2 illustrates the general movement pattern of
vanes 36 when actuated by the unison ring. This movement pattern is generally the same for both known vane configurations and vane configurations prepared according to principles of this invention as used with variable nozzle turbochargers. Eachvane tab 42 is disposed within a respectiveelongated slot 38 of aunison ring 40. In a closed position “A”, thevane tab 42 is positioned adjacent afirst end 44 of theslot 38. This position is referred to as a closed position because the vane is not flared radially outward, thereby serving to limit the flow of exhaust gas to the turbine. At an intermediate position “B” theunison ring 40 has been rotated a sufficient amount such that thevane tab 42 is moved within theslot 38 away from thefirst slot end 44 towards a middle position of the slot. The vane tab movement is provided by the pivoting action of the vane relative to the nozzle wall, allowing the vane to be rotated a given extent. - At position “B” the intermediate radial projection of the vane serves to increase the flow of exhaust gas to the turbine when compared to closed position “A”. At position “C” the unison ring has now been rotated to a maximum position, causing the
vane tab 42 to be moved within theslot 38 to asecond end 46. Again, such further vane movement is facilitated by the pivoting arrangement between the vane and the nozzle wall, allowing the vane to be rotated to a maximum open position. At position “C” the maximum radial projection of the vane serves to increase the flow of exhaust gas to the turbine when compared to the intermediate position “A”. - As mentioned above in the background, proper operation of known variable nozzle turbochargers, comprising the multiple vanes as described above and illustrated in FIG. 1, requires that the vanes be permitted to pivot freely vis-a-vis the nozzle wall when actuated by the unison ring. Such free pivoting movement requires that the vane shafts not bind or otherwise be restricted in their rotational movement within their respective nozzle holes. The known vane design can produce impairments to free pivoting vane movement if the shafts projecting from the vanes are not perfectly perpendicular. Additionally, the known vane designs can produce an impairment to free pivoting vane movement by the relatively high cantilever load stress imposed on the vane by virtue of the vane shaft and hole attachment mechanism.
- FIGS.3 to 5 illustrate a vane 50 for use with a variable nozzle turbocharger, constructed according to principles of this invention, comprising an upper or low
pressure airfoil surface 52, an opposite highpressure airfoil surface 54, andaxial surfaces leading edge 60 and a trailingedge 62 at opposite common ends of the high and low pressure airfoil surfaces 52 and 54. The vane includes atab 64 projecting outwardly away from theaxial surface 58 and positioned adjacent the leadingedge 60. The tab is configured to cooperate with a unison ring slot in the manner described above to facilitate vane actuation. - Referring particularly to FIGS. 3 and 5, unlike the known vane design, vanes50 constructed according to the practice of this invention do not include a shaft. Rather, the vanes of this invention are designed having a
hole 64 extending through theaxial surface 56 that is sized and configured to accommodate placement of arespective post 68 therein (see FIG, 3), wherein the post projects perpendicularly outwardly away from the turbine housing nozzle wall. Configured in this manner, vane pivoting movement vis-a-vis the nozzle wall is provided by the relative rotational motion between the fixed post and the hole in the vane. The pivoting mechanism provided by the fixed wall post disposed in the rotatable vane hole reduces the amount of cantilever load stress on the vane, when compared to known vane designs and attachment mechanisms, thereby serving to reduce and/or eliminate potential impairments to efficient vane movement and operation. - Each
post 68 is configured to be attached to the nozzle wall by press fit or other conventional attachment method, and is positioned within the nozzle wall in a substantially circular pattern the coincides with the desired spaced apart vane arrangement. In an example embodiment, thepost 68 is configured having a stepped design with two different diameters, wherein a firstenlarged diameter section 70 is sized and configured to provide a secure press fit attachment within the nozzle wall, and wherein a second reduced diameter section 72 is sized and configured to project outwardly from the nozzle wall and fit within the vane hole 66 to provide rotational movement thereupon. - The vane50 is configured having a thickness, as measured between the high and low pressure airfoil surfaces 52 and 54, that is greater than known vane designs, to accommodate a sufficiently strong post without compromising the structural integrity of the vane. An unexpected and synergistic effect of increasing the vane thickness to accommodate the nozzle wall post is the realization of a wider area turndown ratio for a fixed rotation of the vane, when compared to turbochargers comprising the conventional prior art vanes. Therefore, vanes of this invention can provide a greater aerodynamic flow range for a fixed efficiency level than that of turbochargers comprising known vane designs.
- The vane can be formed from the same types of materials, and in the same manner, as that used to form conventional prior art vanes. The vanes have a substantially solid design or are alternatively configured having a cored out design. In an example embodiment, the vane
axial surfaces - Having now described the invention in detail as required by the patent statutes, those skilled in the art will recognize modifications and substitutions to the specific embodiments disclosed herein. Such modifications are within the scope and intent of the present invention.
Claims (3)
Priority Applications (12)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/761,277 US6419464B1 (en) | 2001-01-16 | 2001-01-16 | Vane for variable nozzle turbocharger |
PCT/US2002/001397 WO2002057599A1 (en) | 2001-01-16 | 2002-01-16 | Improved vane for variable nozzle turbocharger |
CNB02800079XA CN100422510C (en) | 2001-01-16 | 2002-01-16 | Improved vane for variable nozzle turbocharger |
MXPA02007528A MXPA02007528A (en) | 2001-01-16 | 2002-01-16 | Improved vane for variable nozzle turbocharger. |
JP2002557646A JP2004518062A (en) | 2001-01-16 | 2002-01-16 | Improved blades for variable nozzle turbochargers |
PL02357217A PL357217A1 (en) | 2001-01-16 | 2002-01-16 | Improved vane for variable nozzle turbocharger |
HU0300055A HUP0300055A2 (en) | 2001-01-16 | 2002-01-16 | Improved vane for variable nozzle turbocharger |
KR1020027010145A KR20020084114A (en) | 2001-01-16 | 2002-01-16 | Improved vane for variable nozzle turbocharger |
CZ20022873A CZ20022873A3 (en) | 2001-01-16 | 2002-01-16 | Variable geometry turbocharger assembly |
EP02713429.5A EP1352157B1 (en) | 2001-01-16 | 2002-01-16 | Variable geometry turbocharger with improved vane actuation |
US10/090,864 US6672059B2 (en) | 2001-01-16 | 2002-03-04 | Vane design for use in variable geometry turbocharger |
US10/178,754 US6729134B2 (en) | 2001-01-16 | 2002-06-24 | Variable geometry turbocharger having internal bypass exhaust gas flow |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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US09/761,277 US6419464B1 (en) | 2001-01-16 | 2001-01-16 | Vane for variable nozzle turbocharger |
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US10/090,864 Continuation-In-Part US6672059B2 (en) | 2001-01-16 | 2002-03-04 | Vane design for use in variable geometry turbocharger |
US10/178,754 Continuation-In-Part US6729134B2 (en) | 2001-01-16 | 2002-06-24 | Variable geometry turbocharger having internal bypass exhaust gas flow |
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US10/090,864 Expired - Fee Related US6672059B2 (en) | 2001-01-16 | 2002-03-04 | Vane design for use in variable geometry turbocharger |
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US10/090,864 Expired - Fee Related US6672059B2 (en) | 2001-01-16 | 2002-03-04 | Vane design for use in variable geometry turbocharger |
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EP (1) | EP1352157B1 (en) |
JP (1) | JP2004518062A (en) |
KR (1) | KR20020084114A (en) |
CN (1) | CN100422510C (en) |
CZ (1) | CZ20022873A3 (en) |
HU (1) | HUP0300055A2 (en) |
MX (1) | MXPA02007528A (en) |
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US8016551B2 (en) * | 2005-11-03 | 2011-09-13 | Honeywell International, Inc. | Reverse curved nozzle for radial inflow turbines |
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WO2008023034A1 (en) * | 2006-08-24 | 2008-02-28 | Abb Turbo Systems Ag | Diffuser of a radial flow compressor |
US7559199B2 (en) * | 2006-09-22 | 2009-07-14 | Honeywell International Inc. | Variable-nozzle cartridge for a turbocharger |
US8500395B2 (en) * | 2007-02-15 | 2013-08-06 | Borgwarner Inc. | Turbocharger vane |
WO2008124758A1 (en) * | 2007-04-10 | 2008-10-16 | Elliott Company | Centrifugal compressor having adjustable inlet guide vanes |
US20090067978A1 (en) * | 2007-05-24 | 2009-03-12 | Suljak Jr George T | Variable area turbine vane arrangement |
US8007229B2 (en) * | 2007-05-24 | 2011-08-30 | United Technologies Corporation | Variable area turbine vane arrangement |
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US20090133399A1 (en) * | 2007-11-27 | 2009-05-28 | Caterpillar Inc. | Turbocharger system implementing real time speed limiting |
US8257035B2 (en) * | 2007-12-05 | 2012-09-04 | Siemens Energy, Inc. | Turbine vane for a gas turbine engine |
US8105019B2 (en) * | 2007-12-10 | 2012-01-31 | United Technologies Corporation | 3D contoured vane endwall for variable area turbine vane arrangement |
GB0822474D0 (en) * | 2008-12-10 | 2009-01-14 | Cummins Turbo Tech Ltd | Variable geometry turbine nozzle ring |
CN101634233B (en) * | 2009-08-20 | 2011-07-20 | 康跃科技股份有限公司 | Pneumatic nozzle of variable geometry turbocharger (VGT) |
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US8480357B2 (en) | 2009-11-09 | 2013-07-09 | Honeywell International Inc. | Variable geometry turbocharger with guide pins |
US8511981B2 (en) * | 2010-07-19 | 2013-08-20 | Cameron International Corporation | Diffuser having detachable vanes with positive lock |
DE102010047251A1 (en) * | 2010-10-04 | 2011-12-01 | Voith Patent Gmbh | Control device for controlling gas flowing through exhaust gas turbocharger turbine for turbo compound system for e.g. passenger car, has wall and tension ring relatively rotated against each other by adjusting guide vanes |
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US9702299B2 (en) * | 2012-12-26 | 2017-07-11 | Honeywell International Inc. | Turbine assembly |
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US9845723B2 (en) * | 2014-11-24 | 2017-12-19 | Honeywell International Inc. | Adjustable-trim centrifugal compressor, and turbocharger having same |
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US9890649B2 (en) * | 2016-01-29 | 2018-02-13 | Pratt & Whitney Canada Corp. | Inlet guide assembly |
US10253648B2 (en) | 2016-03-04 | 2019-04-09 | General Electric Company | Modulated hybrid variable area turbine nozzle for gas turbine engine |
ITUA20164308A1 (en) | 2016-06-13 | 2017-12-13 | Nuovo Pignone Tecnologie Srl | Variable geometry assembly for turbomachinery and turbomachinery comprising said assembly |
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US10927702B1 (en) | 2019-03-30 | 2021-02-23 | Savant Holdings LLC | Turbocharger or turbocharger component |
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US10995684B1 (en) * | 2019-11-21 | 2021-05-04 | Internatinal Engine Intellectual Property Company, LLC. | Smart actuator learn command process |
US11530615B1 (en) * | 2022-03-01 | 2022-12-20 | Garrett Transportation I Inc. | Method for constructing a fixed-vane ring for a nozzle of a turbocharger turbine |
Family Cites Families (30)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE224977C (en) * | ||||
US2392200A (en) * | 1944-11-27 | 1946-01-01 | Gen Electric | Centrifugal compressor |
GB731822A (en) * | 1952-03-14 | 1955-06-15 | Power Jets Res & Dev Ltd | Improvements relating to turbines or compressors for operation with gaseous fluids |
US2976013A (en) * | 1955-08-17 | 1961-03-21 | Fairchild Engine & Airplane | Turbine construction |
US2904817A (en) * | 1956-02-24 | 1959-09-22 | Gen Electric | Rug tool having a turbine-driven rug brush |
US3495921A (en) * | 1967-12-11 | 1970-02-17 | Judson S Swearingen | Variable nozzle turbine |
US3697193A (en) * | 1970-12-10 | 1972-10-10 | Adrian Phillips | Fluidfoil section |
US4459083A (en) * | 1979-03-06 | 1984-07-10 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Shapes for rotating airfoils |
US4242040A (en) * | 1979-03-21 | 1980-12-30 | Rotoflow Corporation | Thrust adjusting means for nozzle clamp ring |
US4300869A (en) * | 1980-02-11 | 1981-11-17 | Swearingen Judson S | Method and apparatus for controlling clamping forces in fluid flow control assemblies |
US4502836A (en) * | 1982-07-02 | 1985-03-05 | Swearingen Judson S | Method for nozzle clamping force control |
CA1243993A (en) * | 1983-07-04 | 1988-11-01 | Westland Plc | Helicopter rotor blade |
US4657476A (en) * | 1984-04-11 | 1987-04-14 | Turbotech, Inc. | Variable area turbine |
JPS6170105A (en) * | 1984-09-13 | 1986-04-10 | Nissan Motor Co Ltd | Radial turbine with variable capacity |
DE3541508C1 (en) * | 1985-11-23 | 1987-02-05 | Kuehnle Kopp Kausch Ag | Exhaust gas turbocharger |
US4679984A (en) * | 1985-12-11 | 1987-07-14 | The Garrett Corporation | Actuation system for variable nozzle turbine |
US4804316A (en) * | 1985-12-11 | 1989-02-14 | Allied-Signal Inc. | Suspension for the pivoting vane actuation mechanism of a variable nozzle turbocharger |
US5035578A (en) * | 1989-10-16 | 1991-07-30 | Westinghouse Electric Corp. | Blading for reaction turbine blade row |
US5017091A (en) * | 1990-02-26 | 1991-05-21 | Westinghouse Electric Corp. | Free standing blade for use in low pressure steam turbine |
US5417548A (en) * | 1994-01-14 | 1995-05-23 | Midwest Research Institute | Root region airfoil for wind turbine |
US5562420A (en) * | 1994-03-14 | 1996-10-08 | Midwest Research Institute | Airfoils for wind turbine |
US5931636A (en) * | 1997-08-28 | 1999-08-03 | General Electric Company | Variable area turbine nozzle |
FR2767862B1 (en) * | 1997-09-03 | 1999-10-01 | Air Liquide | CRYOGENIC TURBINE WITH VARIABLE BLADES |
US5851104A (en) * | 1997-12-15 | 1998-12-22 | Atlas Copco Rotoflow, Inc. | Nozzle adjusting mechanism |
US6269642B1 (en) | 1998-10-05 | 2001-08-07 | Alliedsignal Inc. | Variable geometry turbocharger |
JP2000291440A (en) | 1999-04-06 | 2000-10-17 | Toufuji Denki Kk | Turbocharger |
JP2001289050A (en) | 1999-05-20 | 2001-10-19 | Hitachi Ltd | Variable capacity turbo supercharger |
JP2001173449A (en) | 1999-12-16 | 2001-06-26 | Toyota Motor Corp | Variable nozzle type turbocharger |
US6503058B1 (en) * | 2000-05-01 | 2003-01-07 | Zond Energy Systems, Inc. | Air foil configuration for wind turbine |
WO2012023981A2 (en) | 2010-08-17 | 2012-02-23 | St. Jude Medical, Inc. | Tip for medical implant delivery system |
-
2001
- 2001-01-16 US US09/761,277 patent/US6419464B1/en not_active Expired - Lifetime
-
2002
- 2002-01-16 CZ CZ20022873A patent/CZ20022873A3/en unknown
- 2002-01-16 KR KR1020027010145A patent/KR20020084114A/en not_active Application Discontinuation
- 2002-01-16 PL PL02357217A patent/PL357217A1/en unknown
- 2002-01-16 HU HU0300055A patent/HUP0300055A2/en unknown
- 2002-01-16 CN CNB02800079XA patent/CN100422510C/en not_active Expired - Lifetime
- 2002-01-16 MX MXPA02007528A patent/MXPA02007528A/en active IP Right Grant
- 2002-01-16 JP JP2002557646A patent/JP2004518062A/en active Pending
- 2002-01-16 WO PCT/US2002/001397 patent/WO2002057599A1/en not_active Application Discontinuation
- 2002-01-16 EP EP02713429.5A patent/EP1352157B1/en not_active Expired - Lifetime
- 2002-03-04 US US10/090,864 patent/US6672059B2/en not_active Expired - Fee Related
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---|---|---|---|---|
US20050106040A1 (en) * | 2002-12-30 | 2005-05-19 | Repple Walter O. | Thermal control of flowrate in engine coolant system |
GB2400633A (en) * | 2003-04-15 | 2004-10-20 | Honeywell Int Inc | Variable flow nozzle |
GB2400633B (en) * | 2003-04-15 | 2005-03-09 | Honeywell Int Inc | Variable flow nozzle for a turbocharger |
WO2005031120A1 (en) * | 2003-09-25 | 2005-04-07 | Honeywell International Inc. | Variable geometry turbocharger |
US7059129B2 (en) | 2003-09-25 | 2006-06-13 | Honeywell International, Inc. | Variable geometry turbocharger |
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US20050123394A1 (en) * | 2003-12-03 | 2005-06-09 | Mcardle Nathan J. | Compressor diffuser |
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US7255530B2 (en) | 2003-12-12 | 2007-08-14 | Honeywell International Inc. | Vane and throat shaping |
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WO2012036328A1 (en) * | 2010-09-15 | 2012-03-22 | (주)계양정밀 | Variable nozzle device and turbo charger provided with same |
CN103089344A (en) * | 2011-11-04 | 2013-05-08 | 萍乡市德博科技发展有限公司 | Blade double-supporting variable-section nozzle ring assembly for bi-directional positioning of poking disc |
WO2013162899A1 (en) * | 2012-04-24 | 2013-10-31 | Borgwarner Inc. | Vane pack assembly for vtg turbochargers |
CN104204445A (en) * | 2012-04-24 | 2014-12-10 | 博格华纳公司 | Vane pack assembly for VTG turbochargers |
US9518589B2 (en) | 2012-04-24 | 2016-12-13 | Borgwarner Inc. | Vane pack assembly for VTG turbochargers |
EP2733311A1 (en) * | 2012-11-16 | 2014-05-21 | ABB Turbo Systems AG | Nozzle ring |
US9909456B2 (en) | 2012-11-16 | 2018-03-06 | Abb Turbo Systems Ag | Nozzle ring |
US11346236B2 (en) * | 2018-07-12 | 2022-05-31 | Vitesco Technologies GmbH | Guide vane and turbine assembly provided with same |
US11578612B2 (en) * | 2018-09-06 | 2023-02-14 | Liebherr-Aerospace Toulouse Sas | Distributor for a turbomachine radial turbine, turbomachine comprising such a distributor and air conditioning system comprising such a turbomachine |
US20230235681A1 (en) * | 2020-06-23 | 2023-07-27 | Turbo Systems Switzerland Ltd. | Modular nozzle ring for a turbine stage of a continuous flow machine |
Also Published As
Publication number | Publication date |
---|---|
EP1352157B1 (en) | 2013-07-10 |
CN100422510C (en) | 2008-10-01 |
US6419464B1 (en) | 2002-07-16 |
CZ20022873A3 (en) | 2003-04-16 |
JP2004518062A (en) | 2004-06-17 |
KR20020084114A (en) | 2002-11-04 |
CN1455843A (en) | 2003-11-12 |
HUP0300055A2 (en) | 2003-04-28 |
PL357217A1 (en) | 2004-07-26 |
EP1352157A1 (en) | 2003-10-15 |
US20020187061A1 (en) | 2002-12-12 |
WO2002057599A1 (en) | 2002-07-25 |
US6672059B2 (en) | 2004-01-06 |
MXPA02007528A (en) | 2003-03-27 |
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