EP1301689A1 - Turbokompressor mit axial verschiebbaren leitschaufeln wobei die geometrie in längsrichtung unterschiedlich ist - Google Patents

Turbokompressor mit axial verschiebbaren leitschaufeln wobei die geometrie in längsrichtung unterschiedlich ist

Info

Publication number
EP1301689A1
EP1301689A1 EP00954699A EP00954699A EP1301689A1 EP 1301689 A1 EP1301689 A1 EP 1301689A1 EP 00954699 A EP00954699 A EP 00954699A EP 00954699 A EP00954699 A EP 00954699A EP 1301689 A1 EP1301689 A1 EP 1301689A1
Authority
EP
European Patent Office
Prior art keywords
turbine
piston
casing
fins
heat shield
Prior art date
Legal status (The legal status 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 status listed.)
Granted
Application number
EP00954699A
Other languages
English (en)
French (fr)
Other versions
EP1301689B1 (de
Inventor
Alain René AlliedSignal Turbo SA LOMBARD
Jean-Luc Hubert AlliedSignal Turbo SA PERRIN
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Garrett Motion France SAS
Original Assignee
Honeywell Garrett SA
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 Honeywell Garrett SA filed Critical Honeywell Garrett SA
Publication of EP1301689A1 publication Critical patent/EP1301689A1/de
Application granted granted Critical
Publication of EP1301689B1 publication Critical patent/EP1301689B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • 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
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F01D17/143—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path the shiftable member being a wall, or part thereof of a radial diffuser
    • 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
    • F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
    • 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

Definitions

  • the present invention generally relates to turbochargers with variable geometry. More specifically, a turbocharger is provided having a variable nozzle turbine inlet with sliding fins, with the fins entering through a slotted sheet heat shield suspended in the turbine housing and the fins having a stepped shape to ensure hermetic closure against the surface of the heat shield. Description of related art:
  • High efficiency turbochargers use variable geometry systems for turbine nozzle inlets to increase performance and efficiency aerodynamic.
  • Variable geometry systems for turbochargers have typically been of two types: rotary vane and piston.
  • the rotary vane type exemplified in US Patent Number 5,947,681, titled PRESSURE BALANCED DUAL AXLE VARIABLE NOZZLE TURBOCHARGER provides a plurality of individual vanes placed in the turbine inlet nozzle which can rotate to reduce or increase the area of the nozzle and the flow volume.
  • the piston type which is exemplified in US patents 5,214,920 and 5,231,831 both titled TURBOCHARGER APPARATUS, and U.S.
  • patent number 5,441,383 titled VARIABLE EXHAUST DRIVEN TURBOCHARGERS uses a cylindrical piston or wall which is displaceable concentrically with the axis of rotation of the turbine to reduce the area of the nozzle inlet.
  • the piston type variable geometry turbocharger incorporates fins having a fixed angle of attack with respect to the air flow, which are mounted either on the piston or on a fixed nozzle wall opposite the piston and which enter slots in the opposite surface during the movement of the piston.
  • variable geometry turbochargers of. piston type of the prior art the challenge has been to maximize the aerodynamic performance balanced by the tolerancing of the contact surfaces, especially the fins and receiving slots which are subjected to an extreme temperature variation and to mechanical stress, as well as providing, means for actuating the piston in a configuration which can be easily manufactured.
  • a turbocharger incorporating the present invention has a carcass having a turbine casing receiving exhaust gas from an exhaust manifold of an internal combustion engine at an intake and having an exhaust outlet, a casing compressor having an air intake and a first volute, and a central casing through the turbine casing and the compressor casing.
  • a turbine wheel is carried in the turbine casing to extract energy from the exhaust gas.
  • the turbine wheel is connected to a shaft which extends from the turbine housing through a shaft bore in the central housing and the turbine wheel has a substantially complete rear disc and multiple blades.
  • a bearing mounted in the shaft bore of the central casing supports the shaft for the rotary movement and a paddle wheel is connected to the shaft opposite the turbine wheel and enclosed in the compressor casing.
  • a substantially cylindrical piston is concentric with the turbine wheel and displaceable parallel to an axis of rotation of the turbine wheel.
  • a plurality of fins extend substantially 'parallel to the axis of rotation from a first end of the piston close to the rear disc.
  • a heat shield is engaged at its outer circumference between the turbine casing and the central casing and extends radially inward towards the axis of rotation.
  • the heat shield has a plurality of slots receiving the fins.
  • An actuator is provided to move the piston from a first position in which the first end is near the heat shield to a second position in which the first end is away from the screen thermal.
  • the vanes have a first portion sized to be 'received in the slots and a second portion or step, between the first piston and dimensioned to engage the surface of the heat shield and cover the slot with the piston in the first position.
  • FIG.l is an elevational view in cross section of a turbocharger using an embodiment of the invention
  • FIG.2 is a top view of the heat shield
  • FIG.3 is a bottom view of the piston with the fins attached
  • FIG.4 is a side view of one of the fins
  • FIG.5a is a partial side view of the turbocharger incorporating the present invention showing the detail of the step engagement of the fins of the heat shield with the piston in the closed position
  • FIG.5b is a partial side view of the turbocharger incorporating the present invention showing the detail of the step engagement of the fins of the heat shield with the piston in the open position
  • FIG. ⁇ a is a bottom view of the heat shield showing in broken lines the imprint of the step on the fins which closes the slots
  • FIG. ⁇ b is a detailed view of an alternative embodiment of the blade imprint . , and. of a step with the line of the step cord at an angle with respect to the line of the blade of the blade.
  • FIG. 1 shows an embodiment of the invention for a turbocharger 10 which incorporates a turbine casing 12, a central casing 14 and a compressor casing 16.
  • a turbine wheel 18 is connected by a shaft 20 to a compressor wheel 22.
  • the turbine wheel converts the energy of the exhaust gas from an internal combustion engine supplied from an exhaust manifold (not shown) to a volute 24 in the turbine casing
  • the exhaust gas is expanded through the turbine and leaves the turbine casing via an outlet 26.
  • the compressor casing incorporates an inlet 28 and an outlet volute 30.
  • a rear plate 32 is connected by bolts 34 to the compressor casing.
  • the backplate is, in turn, attached to the center shell with bolts (not shown).
  • a first ring seal 36 is engaged between the rear plate and the compressor casing and a second ring seal 38 is engaged between the rear plate and the central casing.
  • Bolts 40 and fixing washers 42 connect the turbine housing to the central housing.
  • Trunnion bearings 50 mounted in the shaft bore 52 of the central envelope support the rotating shaft.
  • a hose clamp 54 mounted on the shaft adjacent to the compressor wheel engages a forced thrust bearing 56 between the central casing and the rear plate in the illustrated embodiment.
  • a sleeve 58 is engaged between the clamp and the compressor wheel.
  • a rotary seal 60 such as a piston ring, provides a seal between the sleeve and the back plate.
  • a circlip 62 forces the journal bearing into the bore and a nut 64 forces the compressor wheel and bearing components on the shaft.
  • the variable geometry mechanism of the present invention includes a substantially cylindrical piston 70 entering the concentric turbine casing aligned with the rotary axis of the turbine.
  • the piston is longitudinally displaceable by a crosspiece 72, having three branches in the illustrated embodiment, attaching to the piston and attaching to an actuation shaft 74.
  • the actuation shaft enters a socket 76 extending to through the turbine housing and connects to an actuating device 77.
  • the actuating device is mounted on projections on the turbine housing using a support 78 and bolts 80.
  • the piston slides in the turbine housing by a low friction insert 82.
  • a cylindrical seal 84 is inserted between the piston and the insert.
  • the piston is movable from a closed position illustrated in FIG. 1, substantially reducing the area of the intake nozzle towards the turbine from the volute 24. In the fully open position, a radial projection 86 on the piston between in a count 88 which limits the stroke of the piston.
  • the fins 90 of the nozzle extend from the radial projection on the piston. In the closed position of the piston, the fins are housed in a stripped portion of the molded part of the central envelope.
  • a heat shield 92 is engaged between the turbine casing and the central casing.
  • the screen is of a shape adapted to extend into the cavity of the turbine casing from the interface between the central casing and the turbine casing and provides an internal wall to the intake nozzle of the turbine.
  • FIG. 2 shows the heat shield incorporating closed slots 96 to receive the fins 90. As shown in FIGS. 3 and 4, the fins have a first part 98 which is received in the slots and a second part 100 in the form step which is longer in rope and depth -to exceed the size of the slot. As shown in FIG.
  • FIG. 6b shows an alternative embodiment of the step vane with the step chord, represented by the line 106, established at an angle with respect to the dawn chord, represented by the line 104. This arrangement provides a modified angle of attack on the blade relative to the air flow in the open and closed positions of the piston for enhanced aerodynamic control.
  • the piston actuation system in the embodiment illustrated in the drawings is a pneumatic actuator 77 having a housing bottom 102 fixed to a support 78 as it is. illustrated in FIG.l.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)
EP00954699A 2000-07-19 2000-07-19 Turbokompressor mit axial verschiebbaren leitschaufeln wobei die geometrie in längsrichtung unterschiedlich ist Expired - Lifetime EP1301689B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/FR2000/002069 WO2002006636A1 (fr) 2000-07-19 2000-07-19 Turbocompresseur a ailettes coulissantes avec ailettes graduees

Publications (2)

Publication Number Publication Date
EP1301689A1 true EP1301689A1 (de) 2003-04-16
EP1301689B1 EP1301689B1 (de) 2006-09-20

Family

ID=8847165

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00954699A Expired - Lifetime EP1301689B1 (de) 2000-07-19 2000-07-19 Turbokompressor mit axial verschiebbaren leitschaufeln wobei die geometrie in längsrichtung unterschiedlich ist

Country Status (8)

Country Link
US (1) US7097432B1 (de)
EP (1) EP1301689B1 (de)
JP (1) JP2004504524A (de)
KR (1) KR100643093B1 (de)
CN (1) CN1289791C (de)
AU (1) AU2000267060A1 (de)
DE (1) DE60030894T2 (de)
WO (1) WO2002006636A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
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US9664193B2 (en) 2011-12-08 2017-05-30 Ihi Charging Systems International Gmbh Turbine for an exhaust gas turbocharger

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WO2004046509A1 (en) * 2002-11-15 2004-06-03 Honeywell International Inc. Variable nozzle for turbocharger
AU2003206001A1 (en) * 2003-02-19 2004-09-09 Honeywell International Inc. Nozzle device for a turbocharger and associated control method
AU2003206002A1 (en) * 2003-02-19 2004-09-09 Honeywell International Inc. Turbine having variable throat
US8197194B2 (en) 2004-05-03 2012-06-12 Honeywell International, Inc. Turbine of a turbocharger
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US8047772B2 (en) * 2005-03-30 2011-11-01 Honeywell International Inc. Variable geometry turbine for a turbocharger and method of controlling the turbine
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US7338254B2 (en) * 2005-11-29 2008-03-04 Honeywell International, Inc. Turbocharger with sliding piston assembly
EP1816317B1 (de) * 2006-02-02 2013-06-12 IHI Corporation Turbolader mit variabler Geometrie
CN101473124B (zh) * 2006-06-21 2013-03-27 株式会社Ihi 旋转机械的轴承构造、旋转机械、轴承构造的制造方法、以及旋转机械的制造方法
EP2094957B1 (de) * 2006-11-01 2016-06-29 BorgWarner, Inc. Turbinenhitzeschildanordnung
US7980816B2 (en) * 2007-08-27 2011-07-19 Honeywell International Inc. Retainer for a turbocharger
GB0805519D0 (en) * 2008-03-27 2008-04-30 Cummins Turbo Tech Ltd Variable geometry turbine
DE102008023552B4 (de) * 2008-05-14 2018-12-20 BMTS Technology GmbH & Co. KG Abgasturbolader für ein Kraftfahrzeug
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DE102009053238B4 (de) * 2009-11-13 2012-06-21 Continental Automotive Gmbh Turboladergehäuse mit einer Dichtungseinrichtung
JP5473762B2 (ja) * 2010-04-30 2014-04-16 三菱重工業株式会社 可変容量タービンおよびこれを備えた可変容量ターボチャージャ
KR101924920B1 (ko) * 2011-06-10 2018-12-04 보르그워너 인코퍼레이티드 복류식 터빈 하우징 터보차저
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JP5409741B2 (ja) * 2011-09-28 2014-02-05 三菱重工業株式会社 可変ノズル機構の開度規制構造および可変容量型ターボチャージャ
DE102011120555A1 (de) 2011-12-08 2013-06-13 Daimler Ag Leitgitter für eine Turbine eines Abgasturboladers sowie Turbine für einen Abgasturbolader
US9950382B2 (en) * 2012-03-23 2018-04-24 Pratt & Whitney Canada Corp. Method for a fabricated heat shield with rails and studs mounted on the cold side of a combustor heat shield
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US9664193B2 (en) 2011-12-08 2017-05-30 Ihi Charging Systems International Gmbh Turbine for an exhaust gas turbocharger

Also Published As

Publication number Publication date
JP2004504524A (ja) 2004-02-12
KR100643093B1 (ko) 2006-11-10
KR20030029785A (ko) 2003-04-16
EP1301689B1 (de) 2006-09-20
US7097432B1 (en) 2006-08-29
CN1454284A (zh) 2003-11-05
CN1289791C (zh) 2006-12-13
DE60030894T2 (de) 2007-09-06
DE60030894D1 (de) 2006-11-02
AU2000267060A1 (en) 2002-01-30
WO2002006636A1 (fr) 2002-01-24

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