JP2007309316A - Guide vane device of axial flow turbine of exhaust driven supercharger - Google Patents

Guide vane device of axial flow turbine of exhaust driven supercharger Download PDF

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JP2007309316A
JP2007309316A JP2007120623A JP2007120623A JP2007309316A JP 2007309316 A JP2007309316 A JP 2007309316A JP 2007120623 A JP2007120623 A JP 2007120623A JP 2007120623 A JP2007120623 A JP 2007120623A JP 2007309316 A JP2007309316 A JP 2007309316A
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Prior art keywords
adjusting
adjusting ring
ring
guide vane
adjustment
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JP2007309316A5 (en
Inventor
Thomas Siewert
ジーヴェルト トーマス
Andre Voges
フォーゲス アンドレ
Wutz Dietmar
ヴッツ ディートマール
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MAN Energy Solutions France SAS
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MAN Diesel SA
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • 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
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • 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
    • 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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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)

Abstract

<P>PROBLEM TO BE SOLVED: To eliminate precise support of an adjusting ring by introducing symmetrical force over the circumference of the adjusting ring, in a guide vane device of an axial flow turbine for adjusting an angle position of a stationary blade 2 together to all stationary blades, by an adjusting lever 5 having a large number of stationary blades 2 rotatably arranged in a stationary blade holder 3 and attached to the respective stationary blades, the adjusting ring 6 cooperating with the whole adjusting levers 5, and an adjusting device acting on the adjusting ring for relatively rotating the adjusting ring to the stationary blade holder. <P>SOLUTION: The adjusting device acting on the adjusting ring 6 has a plurality of connecting devices 7, 8 and 9 symmetrically distributed to, arranged on and connected to the circumference of the adjusting ring. The respective connecting devices are respectively moved by actuators 10 oppositely arranged to the adjusting ring. These actuators are mutually synchronized so that the adjusting ring is autonomously aligned in the guide vane device in operation. <P>COPYRIGHT: (C)2008,JPO&INPIT

Description

本発明は、特許請求の範囲の請求項１の前文に記載の、特に重油燃料の往復動内燃機関における排気駆動式過給機の軸流タービンの案内羽根装置に関する。   The present invention relates to a guide vane device for an axial-flow turbine of an exhaust-driven supercharger, particularly in a heavy oil fuel reciprocating internal combustion engine, as described in the preamble of claim 1.

一般に、ターボチャージャ（排気駆動過給機）における排気ガスタービンの静翼（案内羽根）は、アクチュエータと機械的伝動機構を介して、運転状態に関係して調整される。可調整案内羽根装置は、それぞれ回動軸線を中心として回動可能な多数の静翼から成る静翼輪（静翼列）を備えている。その各静翼は、ロータ軸線の周りに同心的に配置され、一般に、調整リングによって調整される。かかる調整リングは連結装置を介してアクチュエータに連結され、そのアクチュエータはエンジンの運転状態に応じて制御して調整される。   In general, a stationary blade (guide vane) of an exhaust gas turbine in a turbocharger (exhaust-drive supercharger) is adjusted in relation to an operation state via an actuator and a mechanical transmission mechanism. The adjustable guide blade device includes a stationary blade ring (a stationary blade row) including a large number of stationary blades that can rotate about a rotation axis. Each vane is concentrically disposed about the rotor axis and is generally adjusted by an adjustment ring. The adjusting ring is connected to an actuator through a connecting device, and the actuator is controlled and adjusted according to the operating state of the engine.

即ち、例えば特許文献１に、特に重油燃料の往復動内燃機関における排気駆動式過給機の軸流タービンの案内羽根装置が示されている。その案内羽根装置は、タービン車室内に配置され排気ガス流量を制御するために調整装置により調整できる翼を備えている。従って、そのターボチャージャはタービンの可変な幾何学形状を有し、静翼ホルダに回動可能に配置された多数の静翼にそれぞれ調整レバーが付属され、これらの調整レバーと協働する調整リングが設けられ、その調整リングと静翼ホルダとの相対回転によって、静翼の排気ガス流れ方向に対する角度位置が、すべての静翼に対して一緒に調整される。   That is, for example, Patent Document 1 discloses a guide vane device for an axial flow turbine of an exhaust-driven supercharger, particularly in a heavy oil fuel reciprocating internal combustion engine. The guide vane device includes blades that are arranged in the turbine casing and can be adjusted by an adjusting device to control the exhaust gas flow rate. Therefore, the turbocharger has a variable geometry of the turbine, and an adjustment lever is attached to each of a large number of stationary blades rotatably arranged on the stationary blade holder, and the adjustment ring cooperates with these adjustment levers. And the angular position of the stationary blade relative to the exhaust gas flow direction is adjusted together for all the stationary blades by relative rotation between the adjusting ring and the stationary blade holder.

タービンランナおよび案内羽根装置の静翼ホルダは、ターボチャージャの車室内に互いに同心的に支持されている。案内羽根装置の静翼ホルダにおいて、タービンランナを取り囲む多数の静翼の各軸は、回動可能に支持されている。それらの軸は、半径方向に向けられた作用輪郭面を有する調整レバーを備えている。その作用輪郭面は、調整リングにおける内向き案内溝に回動可能に係合している。さらに調整リングは、ターボチャージャ車室内に静翼ホルダに対して同心的に回動可能に支持されている。調整リングは調整装置に機械的に連結され、例えばアクチュエータによって調整装置により動かされる。調整リングが静翼ホルダに対して相対回転されると、調整レバーおよび従って静翼が回動される。   The turbine runner and the stationary blade holder of the guide vane device are supported concentrically with each other in the passenger compartment of the turbocharger. In the stationary blade holder of the guide blade device, the shafts of a large number of stationary blades surrounding the turbine runner are rotatably supported. The shafts are equipped with adjusting levers having a working contour surface oriented in the radial direction. The action contour surface is rotatably engaged with an inward guide groove in the adjustment ring. Further, the adjustment ring is supported so as to be concentrically rotatable with respect to the stationary blade holder in the turbocharger casing. The adjustment ring is mechanically connected to the adjustment device and is moved by the adjustment device, for example by means of an actuator. When the adjustment ring is rotated relative to the vane holder, the adjustment lever and thus the vane is rotated.

調整装置が調整リングの円周に調整力を与えることによって、調整リングの円周に非対称的な力導入が行われる。そのため、一般に、調整リングは、案内羽根装置に、ないしは、静翼ホルダとタービン車室との間に、精密に支持されねばならず、従って、調整リングは、熱的影響（熱膨張）のために、その支持装置に場合により固着してしまうことがある。
独国特許出願公開第１０３１１２０５号明細書 The adjustment device applies an adjustment force to the circumference of the adjustment ring, so that an asymmetric force is introduced to the circumference of the adjustment ring. Therefore, in general, the adjusting ring must be precisely supported by the guide vane device or between the stationary blade holder and the turbine casing, and therefore the adjusting ring is due to thermal influence (thermal expansion). In addition, the support device may stick to the case.
German Patent Application No. 10311205

本発明の課題は、冒頭に述べた形式の案内羽根装置を、調整リングの円周にわたる対称的な力導入によって、調整リングの精密な支持を省くことができるように形成することにある。   It is an object of the present invention to form a guide vane device of the type described at the outset so that precise support of the adjustment ring can be dispensed with by introducing symmetrical forces around the circumference of the adjustment ring.

この課題は、本発明に基づいて、調整リングに作用する調整装置が、調整リングの円周に対称的に分布して配置され連結された複数の連結装置を有し、各連結装置がそれぞれ調整リングに相対して設けられたアクチュエータによって動かされ、これらのアクチュエータが、稼動中に案内羽根装置において調整リングの自律的な調心が行われる、ように互いに同期される、ことによって解決される。   This object is based on the present invention, in which the adjusting device acting on the adjusting ring has a plurality of connecting devices arranged and connected symmetrically distributed around the circumference of the adjusting ring, and each connecting device adjusts individually. This is solved by being moved by actuators provided relative to the ring, which are synchronized with each other such that the self-alignment of the adjustment ring takes place in the guide vane device during operation.

調整装置の連結装置の連結部の対称的分布によって、複数のアクチュエータが同期して回転する場合に、調整リングが自律的に心出しされる。これにより調整リングの精密な支持が不要となり、熱膨張が、固着ないしヒステリシスを生じさせることはない。即ち、連結部の対称的な分布によって、案内羽根装置の軸線に関して調整リングの同心的回転中心が常に保証される。   Due to the symmetrical distribution of the connecting portions of the connecting device of the adjusting device, the adjusting ring is centered autonomously when the plurality of actuators rotate synchronously. This eliminates the need for precise support of the adjustment ring, and thermal expansion does not cause sticking or hysteresis. In other words, the symmetrical distribution of the connecting part always ensures a concentric rotation center of the adjusting ring with respect to the axis of the guide vane device.

以下図を参照して本発明の実施例を詳細に説明する。   Hereinafter, embodiments of the present invention will be described in detail with reference to the drawings.

通常、タービンは、軸線を中心として回転可能なロータと、タービン車室１と、案内羽根装置とを有している。そのロータはタービンランナおよびこれに取り付けられた動翼を備え、案内羽根装置は、ロータ(タービン軸線Ａ)に対して軸対称に静翼ホルダ３に配置された多数の調節可能な静翼（案内羽根）２から成る静翼輪（静翼列）を備えている。各静翼２は、半径方向に延びる軸線４を中心とした回転によって、２つの終端位置の間で任意の角度位置に回動できる。   Usually, the turbine has a rotor that can rotate about an axis, a turbine casing 1, and a guide vane device. The rotor includes a turbine runner and a moving blade attached to the turbine runner, and the guide vane device includes a number of adjustable vanes (guides) disposed in the vane holder 3 in axial symmetry with respect to the rotor (turbine axis A). A stationary blade ring (stator blade row) composed of blades 2 is provided. Each stationary blade 2 can be rotated to an arbitrary angular position between two terminal positions by rotation about an axial line 4 extending in the radial direction.

案内羽根装置は、公知のように、タービンにおける排気ガス入口室と排気室との間でタービン車室１に保持されている（図２参照）。   As is well known, the guide vane device is held in the turbine casing 1 between the exhaust gas inlet chamber and the exhaust chamber of the turbine (see FIG. 2).

各静翼２に設けられた調整レバー５は、流路から半径方向外側に案内されている。調整レバー５はその外側に案内された部位が回動軸線を中心として回転可能に支持されている。その回転運動は、流路の外側に配置されタービン軸線Ａを中心として回転可能な調整リング６と、この調整リング６のトルクを各静翼２の調整レバー５に伝達する調整要素によって導かれる。   The adjusting lever 5 provided in each stationary blade 2 is guided radially outward from the flow path. The adjustment lever 5 is supported so that a portion guided to the outside of the adjustment lever 5 can rotate about the rotation axis. The rotational movement is guided by an adjustment ring 6 that is disposed outside the flow path and is rotatable about the turbine axis A, and an adjustment element that transmits the torque of the adjustment ring 6 to the adjustment lever 5 of each stationary blade 2.

調整リング６は静翼ホルダ３に関して回動可能に支持され、その調整リング６と静翼ホルダ３との相対的な回動は、各調整レバー５のそれらの軸線を中心とした回動を引き起こす。その調整レバー５によって、各静翼２もそれらの軸線を中心として回動される。排気ガス流れ方向における静翼２の位置に応じて、圧力ないし圧縮能力が制御される。これにより、内燃機関の種々の運転点において、調整リング６の回動によって、排気駆動式過給機の図示されていない圧縮機側において、空気質量流量および過給圧力の制御が行われ、その場合、静翼２によって、タービン（発生出力／回転数）およびこのタービン（軸）を介して圧縮機が、それぞれ制御される。調整リング６の回動は、連結装置７、８、９の形をした外部調整装置とアクチュエータ１０によって行われる。   The adjustment ring 6 is supported so as to be rotatable with respect to the stationary blade holder 3, and the relative rotation between the adjustment ring 6 and the stationary blade holder 3 causes the rotation of the respective adjustment levers 5 around their axes. . The stationary levers 2 are also rotated about their axes by the adjusting lever 5. The pressure or the compression capacity is controlled according to the position of the stationary blade 2 in the exhaust gas flow direction. Thereby, at various operating points of the internal combustion engine, the air mass flow rate and the supercharging pressure are controlled on the compressor side (not shown) of the exhaust drive supercharger by the rotation of the adjustment ring 6. In this case, the stationary blade 2 controls the turbine (generated output / rotation speed) and the compressor via the turbine (shaft). The adjustment ring 6 is rotated by an external adjustment device in the form of a coupling device 7, 8, 9 and an actuator 10.

即ち、調整リング６に作用する調整装置は、調整リング６の円周に対称的に分布して配置され連結された複数の連結装置（７、８、９）を有し、これらの連結装置はそれぞれ、タービン車室１に調整リング６に相対して設けられたアクチュエータ１０によって動かされる。それらのアクチュエータ１０は、稼動中、即ち、アクチュエータ１０の駆動状態において、案内羽根装置において調整リング６の自律的な調心が行われるように互いに同期され、即ち、調整リング６に作用する調整力が、案内羽根装置の軸線に関して調整リング６の同心的回転点が常に保証されるように、調整リング６の円周に一様に分布される。   That is, the adjusting device acting on the adjusting ring 6 has a plurality of connecting devices (7, 8, 9) arranged and connected symmetrically distributed around the circumference of the adjusting ring 6, and these connecting devices are Each is moved by an actuator 10 provided in the turbine casing 1 relative to the adjustment ring 6. The actuators 10 are synchronized with each other so that the adjusting ring 6 is autonomously aligned in the guide vane device during operation, that is, in the driving state of the actuator 10, that is, the adjusting force acting on the adjusting ring 6. Are uniformly distributed around the circumference of the adjustment ring 6 so that a concentric rotation point of the adjustment ring 6 is always guaranteed with respect to the axis of the guide vane device.

この実施例の場合、調整装置は、調整リング６の円周に互いに１８０°の円周角をずらして配置され連結された２個の連結装置（７、８、９）を有し、これらの連結装置（７、８、９）は、互いに同期されたそれら固有のアクチュエータ１０で動かされる。   In the case of this embodiment, the adjusting device has two connecting devices (7, 8, 9) arranged and connected to the circumference of the adjusting ring 6 with the circumferential angle of 180 ° shifted from each other. The coupling devices (7, 8, 9) are moved by their own actuators 10 synchronized with each other.

その両アクチュエータ１０は、調整力および力の方向に関して、静翼ホルダ３において調整リング６の回動可能な支持が保証されるように互いに同期して作動される。   The two actuators 10 are operated in synchronism with each other so as to guarantee a pivotable support of the adjustment ring 6 in the stationary blade holder 3 with respect to the adjustment force and the direction of the force.

アクチュエータ１０は、空気圧式あるいは液圧式調整シリンダとして、あるいは電動機として形成される。   The actuator 10 is formed as a pneumatic or hydraulic adjustment cylinder or as an electric motor.

本発明の対象として、勿論、他の有利な実施例も考えられる。その実施例の場合、調整装置は、調整リング６の円周に互いに１２０°の円周角をずらして配置され連結された３個の連結装置（７、８、９）を有し、これらの連結装置（７、８、９）も互いに同期されたそれら固有のアクチュエータ１０で動かされる。ここでも同様に、調整リング６の同心的回転点並びにその静翼ホルダ３における回動可能な支持が保証される。   Of course, other advantageous embodiments are also conceivable as objects of the invention. In the case of the embodiment, the adjusting device has three connecting devices (7, 8, 9) arranged and connected to the circumference of the adjusting ring 6 with a circumferential angle of 120 ° shifted from each other. The coupling devices (7, 8, 9) are also moved by their own actuators 10 synchronized with each other. Here as well, the concentric rotation point of the adjustment ring 6 and its pivotable support in the stationary blade holder 3 are ensured.

ここでは連結装置は、支持部（８）でタービン車室（１）の調整リング（６）に案内され、調整リング（６）に対してスピンドル駆動装置（９）と協働する軸（７）の形態を有している。   Here, the coupling device is guided by the support (8) to the adjusting ring (6) of the turbine casing (1) and is associated with the spindle drive (9) with respect to the adjusting ring (6). It has the form.

調整リング６は、連結装置（７、８、９）の連結部の範囲で軸７に案内されているのが有利である。ここでは調整リング６の運動を可能にするために調整リング６は弾力的に形成されているのが有利である。そのために、調整リング６は、静翼２の調整レバー５の連結部の間にくびれ部を有している。   The adjusting ring 6 is advantageously guided on the shaft 7 in the region of the connecting part of the connecting device (7, 8, 9). Here, in order to allow movement of the adjusting ring 6, it is advantageous that the adjusting ring 6 is formed elastically. For this purpose, the adjusting ring 6 has a constricted portion between the connecting portions of the adjusting lever 5 of the stationary blade 2.

本発明に基づく案内羽根装置の正面図。The front view of the guide blade apparatus based on this invention. タービン車室に設けられた状態の図１における本発明に基づく案内羽根装置の正面図。The front view of the guide blade apparatus based on this invention in FIG. 1 of the state provided in the turbine casing.

符号の説明Explanation of symbols

１ タービン車室
２ 静翼（案内羽根）
３ 静翼ホルダ
４ 回転軸線
５ 調整レバー
６ 調整リング
７ 連結要素
８ 連結要素
９ 連結要素
１０ アクチュエータ 1 Turbine casing 2 Static blade (guide vane)
3 Stator Blade Holder 4 Rotating Axis 5 Adjusting Lever 6 Adjusting Ring 7 Connecting Element 8 Connecting Element 9 Connecting Element 10 Actuator

Claims (8)

静翼ホルダ（３）に回動可能に配置された複数の静翼（２）を有し、各静翼（２）に付属された調整レバー（５）と、該調整レバー（５）全部と協働する調整リング（６）と、該調整リング（６）を静翼ホルダ（３）に対して相対回転させるために前記調整リング（６）に作用する調整装置とによって、すべての静翼（２）に対して静翼（２）の角度位置が一緒に調整される、特に重油燃料の往復動内燃機関における排気駆動式過給機の軸流タービンの案内羽根装置において、
調整リング（６）に作用する調整装置が、調整リング（６）の円周に対称的に分布して配置され連結された複数の連結装置（７、８、９）を有し、各連結装置（７、８、９）がそれぞれ、調整リング（６）に相対して設けられたアクチュエータ（１０）によって動かされ、これらのアクチュエータ（１０）が、稼動中に案内羽根装置において調整リング（６）の自律的な調心が行われるように互いに同期されることを特徴とする排気駆動式過給機の軸流タービンの案内羽根装置。 An adjustment lever (5) having a plurality of stationary blades (2) rotatably disposed on the stationary blade holder (3), attached to each stationary blade (2), and all the adjustment levers (5), All the stator blades (6) by the cooperating adjusting ring (6) and the adjusting device acting on the adjusting ring (6) to rotate the adjusting ring (6) relative to the stator blade holder (3). 2) The angular position of the stationary blade (2) is adjusted together with respect to 2), in particular in a guide vane device for an axial-flow turbine of an exhaust-driven supercharger in a reciprocating internal combustion engine of heavy oil fuel,
The adjusting device acting on the adjusting ring (6) has a plurality of connecting devices (7, 8, 9) arranged and connected symmetrically distributed around the circumference of the adjusting ring (6). (7, 8, 9) are each moved by an actuator (10) provided relative to the adjustment ring (6), and these actuators (10) are moved in the guide vane device during operation in the adjustment ring (6). A guide blade device for an axial-flow turbine of an exhaust-driven supercharger, wherein the guide blade devices are synchronized with each other so as to perform self-alignment. 調整装置が、調整リング（６）の円周に互いに１８０°の円周角をずらして配置され連結された２個の連結装置（７、８、９）を有し、各連結装置（７、８、９）が互いに同期されたそれら固有のアクチュエータ（１０）で動かされることを特徴とする請求項１に記載の案内羽根装置。   The adjusting device has two connecting devices (7, 8, 9) arranged and connected to the circumference of the adjusting ring (6) with a circumferential angle of 180 ° shifted from each other, and each connecting device (7, 8. Guide vane device according to claim 1, characterized in that 8, 9) are moved by their own actuators (10) synchronized with each other. 調整装置が、調整リング（６）の円周に互いに１２０°の円周角をずらして配置され連結された３個の連結装置（７、８、９）を有し、各連結装置（７、８、９）が互いに同期されたそれら固有のアクチュエータ（１０）で動かされることを特徴とする請求項１に記載の案内羽根装置。   The adjustment device has three connection devices (7, 8, 9) arranged and connected to the circumference of the adjustment ring (6) with a circumferential angle of 120 ° shifted from each other, and each connection device (7, 8. Guide vane device according to claim 1, characterized in that 8, 9) are moved by their own actuators (10) synchronized with each other. アクチュエータ（１０）が、空気圧式あるいは液圧式調整シリンダとして、あるいは電動機として形成されていることを特徴とする請求項１ないし３のいずれか１つに記載の案内羽根装置。   4. A guide vane device according to claim 1, wherein the actuator (10) is formed as a pneumatic or hydraulic adjustment cylinder or as an electric motor. 調整リング（６）が連結装置（７、８、９）の連結部の範囲で案内されていることを特徴とする請求項１に記載の案内羽根装置。   2. The guide vane device according to claim 1, wherein the adjusting ring (6) is guided in the range of the connecting portion of the connecting device (7, 8, 9). 調整リング（６）が弾力的に形成されていることを特徴とする請求項１ないし５のいずれか１つに記載の案内羽根装置。   6. The guide vane device according to claim 1, wherein the adjusting ring (6) is formed elastically. 調整リング（６）が静翼（２）の調整レバー（５）の連結部の間にくびれ部を有していることを特徴とする請求項６に記載の案内羽根装置。   The guide blade device according to claim 6, wherein the adjusting ring (6) has a constricted portion between the connecting portions of the adjusting lever (5) of the stationary blade (2). 各連結装置が、支持部（８）でタービン車室（１）の調整リング（６）に案内され、調整リング（６）に対してスピンドル駆動装置（９）と協働する軸（７）の形態を有していることを特徴とする請求項１に記載の案内羽根装置。   Each coupling device is guided by the support (8) to the adjusting ring (6) of the turbine casing (1), and the shaft (7) of the shaft (7) cooperating with the spindle drive (9) with respect to the adjusting ring (6). It has a form, The guide blade apparatus of Claim 1 characterized by the above-mentioned.
JP2007120623A 2006-05-18 2007-05-01 Guide vane device of axial flow turbine of exhaust driven supercharger Pending JP2007309316A (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107989743A (en) * 2017-12-07 2018-05-04 国家电网公司 A kind of Kaplan turbine water-saving and synergistic adjusting method and regulating system
CN113202621A (en) * 2021-06-14 2021-08-03 中国航发沈阳发动机研究所 Stator blade rotation angle adjusting mechanism

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3053083B1 (en) * 2016-06-22 2019-11-01 Safran Aircraft Engines RING OF WHEEL FAIRING IN AUBES
DE102017118795A1 (en) * 2017-08-17 2019-02-21 Ihi Charging Systems International Gmbh Adjustable distributor for a turbine, turbine for an exhaust gas turbocharger and turbocharger
FR3094790B1 (en) * 2019-04-05 2021-03-05 Safran Aircraft Engines System for monitoring a system for actuating a component of a turbomachine
CN111673495B (en) * 2020-04-30 2021-08-06 中国航发南方工业有限公司 Guide blade assembly turning machining clamp and turning machining method
CN112983563B (en) * 2021-05-10 2021-11-30 成都中科翼能科技有限公司 Bearing pull rod for supporting point between turbines of gas turbine and turbine supporting structure

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0626352A (en) * 1992-05-14 1994-02-01 Mitsubishi Heavy Ind Ltd Supercharger with variable nozzle
JP2000018046A (en) * 1998-07-02 2000-01-18 Toyota Motor Corp Turbocharger with variable nozzle vane
JP2003527521A (en) * 2000-03-17 2003-09-16 アーベーベー ターボ システムズ アクチエンゲゼルシャフト Guide blade device for axial exhaust turbine
JP2004509302A (en) * 2000-09-19 2004-03-25 ローベルト　ボツシユ　ゲゼルシヤフト　ミツト　ベシユレンクテル　ハフツング Disc brake
JP2005016727A (en) * 2003-06-24 2005-01-20 Robert Bosch Gmbh Disc brake with self-boosting action

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4307994A (en) * 1979-10-15 1981-12-29 General Motors Corporation Variable vane position adjuster
CA1270120A (en) * 1985-12-11 1990-06-12 Alliedsignal Inc. Suspension for the pivoting vane actuation mechanism of a variable nozzle turbocharger
ITMI991208A1 (en) * 1999-05-31 2000-12-01 Nuovo Pignone Spa DEVICE FOR THE POSITIONING OF NOZZLES OF A STATIC STAGE AND FOR THE COOLING OF ROTOR DISCS IN GAS TURBINES
DE10016745B4 (en) * 2000-04-04 2005-05-19 Man B & W Diesel Ag Axial flow machine with a nozzle comprising a number of adjustable guide vanes
JP3735262B2 (en) * 2001-02-27 2006-01-18 三菱重工業株式会社 Variable nozzle mechanism for variable capacity turbine and manufacturing method thereof
ITTO20010446A1 (en) * 2001-05-11 2002-11-11 Fiatavio Spa VANE FOR A STATOR OF A VARIABLE GEOMETRY TURBINE, IN PARTICULAR FOR AIRCRAFT ENGINES.
JP4040922B2 (en) * 2001-07-19 2008-01-30 株式会社東芝 Assembly type nozzle diaphragm and its assembly method
DE10238412A1 (en) * 2002-08-22 2004-03-04 Volkswagen Ag Turbocharger with variable turbine geometry for IC engines has guide blade adjusting ring born in three inner radial bearings
DE10311205B3 (en) * 2003-03-14 2004-09-16 Man B & W Diesel Ag Guiding device for a radial turbine of a turbocharger of a lifting piston I.C. engine operating with heavy oil has blades with shafts positioned in a housing part of the device facing a compressor of the turbocharger
DE102004023282A1 (en) * 2004-05-11 2005-12-01 Volkswagen Ag Exhaust-gas turbocharger for motor vehicle, has guide vane carrier with cascaded section having reduced outer diameter, which is smaller than inner diameter of radial inner surface of ring, such that section forms radial plain bearing
DE102004037082A1 (en) * 2004-07-30 2006-03-23 Volkswagen Ag Exhaust gas turbocharger for internal combustion engine of especially motor vehicle has first slide surface formed on bearing housing and axially guides adjustment ring on side facing away from guide vane carrier
DE102004043927A1 (en) * 2004-09-11 2006-04-13 Ihi Charging Systems International Gmbh Adjustment device for guide vanes of an exhaust gas turbocharger
DE102004057864A1 (en) * 2004-11-30 2006-06-01 Borgwarner Inc.(N.D.Ges.D.Staates Delaware), Auburn Hills Exhaust gas turbocharger, distributor for an exhaust gas turbocharger and blade lever for a distributor

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0626352A (en) * 1992-05-14 1994-02-01 Mitsubishi Heavy Ind Ltd Supercharger with variable nozzle
JP2000018046A (en) * 1998-07-02 2000-01-18 Toyota Motor Corp Turbocharger with variable nozzle vane
JP2003527521A (en) * 2000-03-17 2003-09-16 アーベーベー ターボ システムズ アクチエンゲゼルシャフト Guide blade device for axial exhaust turbine
JP2004509302A (en) * 2000-09-19 2004-03-25 ローベルト　ボツシユ　ゲゼルシヤフト　ミツト　ベシユレンクテル　ハフツング Disc brake
JP2005016727A (en) * 2003-06-24 2005-01-20 Robert Bosch Gmbh Disc brake with self-boosting action

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107989743A (en) * 2017-12-07 2018-05-04 国家电网公司 A kind of Kaplan turbine water-saving and synergistic adjusting method and regulating system
CN113202621A (en) * 2021-06-14 2021-08-03 中国航发沈阳发动机研究所 Stator blade rotation angle adjusting mechanism
CN113202621B (en) * 2021-06-14 2022-04-01 中国航发沈阳发动机研究所 Stator blade rotation angle adjusting mechanism

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CN101074612B (en) 2011-09-28

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