US20110182749A1 - Turbocharger and adjustable blade therefor - Google Patents

Turbocharger and adjustable blade therefor Download PDF

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Publication number
US20110182749A1
US20110182749A1 US13/063,989 US200913063989A US2011182749A1 US 20110182749 A1 US20110182749 A1 US 20110182749A1 US 200913063989 A US200913063989 A US 200913063989A US 2011182749 A1 US2011182749 A1 US 2011182749A1
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US
United States
Prior art keywords
weight
adjustable blade
turbocharger
adjustable
exhaust gas
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.)
Abandoned
Application number
US13/063,989
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English (en)
Inventor
Gerald Schall
Melanie Gabel
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.)
BorgWarner Inc
Original Assignee
BorgWarner Inc
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 BorgWarner Inc filed Critical BorgWarner Inc
Assigned to BORGWARNER INC. reassignment BORGWARNER INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: GABEL, MELANIE, SCHALL, GERALD
Publication of US20110182749A1 publication Critical patent/US20110182749A1/en
Abandoned legal-status Critical Current

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/001—Ferrous alloys, e.g. steel alloys containing N
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/02—Ferrous alloys, e.g. steel alloys containing silicon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/46—Ferrous alloys, e.g. steel alloys containing chromium with nickel with vanadium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/48—Ferrous alloys, e.g. steel alloys containing chromium with nickel with niobium or tantalum
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/58—Ferrous alloys, e.g. steel alloys containing chromium with nickel with more than 1.5% by weight of manganese
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/166—Sliding contact bearing
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/50—Bearings

Definitions

  • the invention relates to an adjustable blade for turbocharger applications, particularly in a diesel engine, according to the preamble of claim 1 , and also to an exhaust gas turbocharger with an adjustable blade, according to the preamble of claim 5 .
  • Exhaust gas turbochargers are systems for increasing the power of piston engines.
  • an exhaust gas turbocharger the energy of the exhaust gases is utilized for increasing the power.
  • the power increase results from a rise in the mixture throughput per working stroke.
  • a turbocharger consists essentially of an exhaust gas turbine with a shaft and compressor, the compressor arranged in the intake tract of the engine being connected to the shaft, and the blade wheels located in the casing of the exhaust gas turbine and in the compressor rotating.
  • adjustable blades are additionally mounted rotatably in a blade bearing ring and are moved by means of an adjustment ring arranged in the turbine casing of the turbocharger.
  • the adjustable blades have to satisfy extremely stringent material requirements.
  • the material forming the adjustable blades must be heat-resistant, that is to say still show sufficient strength even at very high temperatures of up to about 900° C.
  • the material must have high wear resistance and also corresponding oxidation resistance, so that the corrosion or wear of the material is reduced, and, consequently, the resistance of the material under the extreme working conditions is still ensured.
  • material is to be resistant to erosive attacks. These physical properties of the material are also to be reflected in the component, that is to say the adjustable blade.
  • Heat-resistant materials for exhaust gas turbochargers or their individual components are known from EP 1 396 620 A1. What is considered suitable here is a material which has a specific composition, the surface of the components being capable of being coated with a chrome carbide layer, and the material having a low fraction of small, non-metallic inclusions. A heat resistance of the turbocharger or of its individual components of up to 700° C. or more is thereby to be achieved.
  • the object of the present invention is to provide an adjustable blade according to the preamble of claim 1 and a turbocharger according to the preamble of claim 5 , which have improved temperature and oxidation resistance, and erosion resistance under extreme temperatures, and also a corresponding wet corrosion resistance, which are distinguished by optimal tribological properties and, moreover, which exhibit a reduced susceptibility to wear.
  • an adjustable blade or an exhaust gas turbocharger comprising just such adjustable blades, a better temperature resistance of the component is achieved. This is also increased by a multiple by means of the dendritic carbide precipitations contained in the iron-based alloy, that is to say a carbide microstructure contained in the iron-based alloy and having fine ramifications and, furthermore, dispersions of nitrogen in the form of nitride structures.
  • An adjustable blade or an exhaust gas turbocharger is thus provided which contains the adjustable blades according to the invention, which has optimal temperature resistance in the range of up to 900° C., furthermore is highly heat-resistant, has high wear, erosion and corrosion resistance and, moreover, is also distinguished by very good sliding properties, along with reduced oxidizability.
  • the adjustable blade according to the invention remains dimensionally stable and therefore highly planar, that is to say is distinguished by a high strength of the material forming it.
  • carbide precipitations in the form of dendrites increase the stability of the iron-based alloy in that they form in the microstructure of the material fine ramifications which perform a supporting action, so that the strength of the material and therefore the strength of the adjustable blade according to the invention are markedly increased on account of their unique structure.
  • the dispersions of the element nitrogen in the form of nitride structures in this case additionally increase the wear performance and corrosion resistance.
  • the material forming the adjustable blade according to the invention or the adjustable blade moreover, exhibits optimal resistance to intercrystalline corrosion.
  • the maximum wear rate of the adjustable blade according to the invention in this case amounts to less than 0.08 mm for a bearing load of 10 to about 18 N/mm 2 , a sliding speed of 0.0025 m/s, a component temperature of about 500 to 900° C., a surface roughness Rz of 6.3, a test duration of 500 hours, a clock frequency of 0.2 Hz, an adjustment angle of 45°, a coefficient of friction of 0.28, a journal diameter of 4.7 mm, a pressure pulsation of more than 200 mbar, and an exhaust gas pressure of more than 1.5 bar, in the case of a diesel exhaust gas as the test medium.
  • the material planeness of the adjustable blade according to the invention amounts to less than 0.1 mm, in the case of a circumference with the diameter of 80 mm, during a thermal shock cycle test with a test time of 300 hours.
  • the material of the adjustable blade according to the invention can be welded by means of conventional welding methods, such as WIG, plasma and also EB methods.
  • the adjustable blade is distinguished by a specific composition which contains the components C: 0.1 to 2%, by weight, Cr: 18 to 43% by weight, Ni: 5 to 15% by weight, Mn: 8 to 16%, by weight, Si: ⁇ 1.3% by weight, Nb: 0.5 to 4% by weight, N: 0.1 to 3% by weight, V: 0.2 to 2.0% by weight, and Fe.
  • the adjustable blade according to the invention consists of a material which contains the following elements: C: 0.2 to 1.0% by weight, Cr: 20 to 32% by weight, Ni: 7 to 14% by weight, Mn: 9 to 14.5% by weight, Si: ⁇ 1% by weight, Nb: 0.75 to 3.5% by weight, N: 0.1 to 1.0% by weight, V: 0.3 to 1.6% by weight, and Fe.
  • An adjustable blade produced in this way not only has the high heat resistance of up to 900° C., but also markedly improved sliding properties.
  • the sliding wear is minimized here.
  • resistance to corrosion and erosion is maximized.
  • a material produced in this way and therefore the adjustable blade according to the invention thus have the following properties:
  • the adjustable blade according to the invention or the material forming it, the iron-based alloy is free of sigma phases.
  • Sigma phases are brittle, intermetallic phases of high hardness. They arise when a body-centered cubic metal and a face-centered cubic metal, the atomic radii of which are identical with only a slight deviation, meet one another. Such sigma phases are undesirable because of their embrittling action and also on account of the property of the matrix to extract chrome.
  • the material according to the invention is distinguished in that it is free of sigma phases. This counteracts the embrittlement of the material and increases its durability.
  • the reduction or avoidance of sigma phases is achieved in that the silicon content in the alloy material is lowered to less than 1.3% by weight and preferably to less than 1% by weight. Furthermore, it is advantageous here to employ austenite formers, such as, for example, manganese, nitrogen and nickel, if appropriate in combination.
  • Claim 5 defines, as an independently handleable article, an exhaust gas turbocharger which, as already described, comprises an adjustable blade which consists of an austenitic basic structure and which has or contains dendritic carbide precipitations.
  • FIG. 1 shows a perspective view, illustrated partially in section, of an exhaust gas turbocharger according to the invention.
  • FIG. 1 illustrates the turbocharger 1 according to the invention which has a turbine casing 2 and a compressor casing 3 connected thereto via a bearing casing 28 .
  • the casings 2 , 3 and 28 are arranged along an axis of rotation R.
  • the turbine casing is shown partially in section, in order to make clear the arrangement of a blade bearing ring 6 and a radially outer guide blade cascade 18 which is formed by the latter and which has a plurality of adjustable blades 7 distributed over the circumference and having rotary axes 8 .
  • Nozzle cross sections are thereby formed, which are larger or smaller, depending on the position of the adjustable blades 7 , and which act upon the turbine rotor 4 , located in the center on the axis of rotation R, to a greater or lesser extent with the engine exhaust gas supplied via a supply duct 9 and discharged via a central connection piece 10 , in order via the turbine rotor 4 to drive a compressor rotor 17 seated on the same shaft.
  • an actuating device 11 is provided. This may per se be of any desired design, but a preferred embodiment has a control casing 12 which controls the control movement of a tappet member 14 fastened to it, in order to convert the movement of said tappet member on an adjustment ring 5 , located behind the blade bearing ring 6 , into a slight rotational movement of said adjustment ring. Between the blade bearing ring 6 and an annular part 15 of the turbine casing 2 , a free space 13 for the adjustable blades 7 is formed. So that this free space 13 can be safeguarded, the blade bearing ring 6 has spacers 16 .
  • An alloy, from which the adjustable blades according to the invention were formed, was produced from the following elements according to a customary method.
  • the chemical analysis gave the following values for the elements: C: 0.2 to 0.5% by weight; Cr: 23 to 26.5% by weight; Ni: 9 to 13.5% by weight; Mn: 9 to 12.5% by weight; Si: max. 1.3% by weight; Nb: 0.75 to 1.75% by weight; V: 0.7 to 1.6% by weight; N: 0.1 to 0.4% by weight, the rest: iron.
  • the adjustable blades produced according to this example were distinguished by a tensile strength R m of 687 MPa (ASTM E 8M/EN 10002-1; at increased temperature: EN 10002-5).
  • the yield point R p 0.2 (measured according to standard methods) amounted to 337 MPa.
  • the elongation at break of the material (measured according to standard methods) amounted to 14.2%.
  • the hardness of the material (measured according to ASTM E 92/ISO 6507-1) amounted to 258 HE.
  • the coefficient of linear expansion (measured according to standard methods) amounted to 17.8 K ⁇ 1 (20 to 900° C.)
  • the material was subjected to a validation test series which comprised the following tests:
  • the component was distinguished in all the tests by excellent resistance to the acting forces.
  • the material therefore had extremely high wear resistance and outstanding oxidation resistance, so that corrosion and wear of the material under the specified conditions were markedly reduced, and, consequently, the resistance of the material was still ensured even over a long period of time.
  • the component according to the invention was subjected to a thermal cycle test, the thermal shocks being operated as follows:

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US13/063,989 2008-09-25 2009-09-15 Turbocharger and adjustable blade therefor Abandoned US20110182749A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102008048887.9 2008-09-25
DE102008048887 2008-09-25
PCT/US2009/056916 WO2010036534A2 (en) 2008-09-25 2009-09-15 Turbocharger and adjustable blade therefor

Publications (1)

Publication Number Publication Date
US20110182749A1 true US20110182749A1 (en) 2011-07-28

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US13/063,989 Abandoned US20110182749A1 (en) 2008-09-25 2009-09-15 Turbocharger and adjustable blade therefor

Country Status (6)

Country Link
US (1) US20110182749A1 (zh)
JP (1) JP2012503719A (zh)
KR (1) KR101576194B1 (zh)
CN (1) CN102149838A (zh)
DE (1) DE112009002014B4 (zh)
WO (1) WO2010036534A2 (zh)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102953980A (zh) * 2012-11-22 2013-03-06 无锡惠山泵业有限公司 油泵总成
US20140255245A1 (en) * 2011-10-20 2014-09-11 Borgwarner Inc. Turbocharger and a component therefor
US20160195006A1 (en) * 2015-01-07 2016-07-07 Borgwarner Inc. Variable turbine geometry turbocharger vane ring assembly retention device
US9534281B2 (en) 2014-07-31 2017-01-03 Honeywell International Inc. Turbocharger turbine housings formed from the stainless steel alloys, and methods for manufacturing the same
US9896752B2 (en) 2014-07-31 2018-02-20 Honeywell International Inc. Stainless steel alloys, turbocharger turbine housings formed from the stainless steel alloys, and methods for manufacturing the same
US10316694B2 (en) 2014-07-31 2019-06-11 Garrett Transportation I Inc. Stainless steel alloys, turbocharger turbine housings formed from the stainless steel alloys, and methods for manufacturing the same
US11434556B2 (en) 2018-10-12 2022-09-06 Borgwarner Inc. Austenitic alloys for turbochargers
US11454132B2 (en) 2018-10-05 2022-09-27 Vitesco Technologies GmbH Turbocharger, having a steel material for high-temperature applications
WO2023067317A1 (en) * 2021-10-18 2023-04-27 Alloyed Limited A heat-resistant austenitic stainless steel

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2014523501A (ja) * 2011-06-07 2014-09-11 ボーグワーナー インコーポレーテッド ターボチャージャ及びそのための構成要素
DE102020202736A1 (de) 2020-03-04 2021-09-09 Mahle International Gmbh Metallischer Werkstoff
DE102020128884A1 (de) 2020-11-03 2022-05-05 BMTS Technology GmbH & Co. KG Austenitische Stahllegierung und Turbinengehäuse oder Turbinengehäusebauteil für einen Abgasturbolader

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US7117596B2 (en) * 2001-08-03 2006-10-10 Akita Fine Blanking Co., Ltd. Variable blade manufacturing method and variable blade in VGS type turbo charger
US20060266439A1 (en) * 2002-07-15 2006-11-30 Maziasz Philip J Heat and corrosion resistant cast austenitic stainless steel alloy with improved high temperature strength

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US7117596B2 (en) * 2001-08-03 2006-10-10 Akita Fine Blanking Co., Ltd. Variable blade manufacturing method and variable blade in VGS type turbo charger
US20060266439A1 (en) * 2002-07-15 2006-11-30 Maziasz Philip J Heat and corrosion resistant cast austenitic stainless steel alloy with improved high temperature strength
US20050194073A1 (en) * 2004-03-04 2005-09-08 Daido Steel Co., Ltd. Heat-resistant austenitic stainless steel and a production process thereof

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140255245A1 (en) * 2011-10-20 2014-09-11 Borgwarner Inc. Turbocharger and a component therefor
US9359938B2 (en) * 2011-10-20 2016-06-07 Borgwarner Inc. Turbocharger and a component therefor
CN102953980A (zh) * 2012-11-22 2013-03-06 无锡惠山泵业有限公司 油泵总成
US9534281B2 (en) 2014-07-31 2017-01-03 Honeywell International Inc. Turbocharger turbine housings formed from the stainless steel alloys, and methods for manufacturing the same
US9896752B2 (en) 2014-07-31 2018-02-20 Honeywell International Inc. Stainless steel alloys, turbocharger turbine housings formed from the stainless steel alloys, and methods for manufacturing the same
US10316694B2 (en) 2014-07-31 2019-06-11 Garrett Transportation I Inc. Stainless steel alloys, turbocharger turbine housings formed from the stainless steel alloys, and methods for manufacturing the same
US20160195006A1 (en) * 2015-01-07 2016-07-07 Borgwarner Inc. Variable turbine geometry turbocharger vane ring assembly retention device
US10378434B2 (en) * 2015-01-07 2019-08-13 Borgwarner Inc. Variable turbine geometry turbocharger vane ring assembly retention device
US11454132B2 (en) 2018-10-05 2022-09-27 Vitesco Technologies GmbH Turbocharger, having a steel material for high-temperature applications
US11434556B2 (en) 2018-10-12 2022-09-06 Borgwarner Inc. Austenitic alloys for turbochargers
WO2023067317A1 (en) * 2021-10-18 2023-04-27 Alloyed Limited A heat-resistant austenitic stainless steel

Also Published As

Publication number Publication date
JP2012503719A (ja) 2012-02-09
KR20110063658A (ko) 2011-06-13
DE112009002014T5 (de) 2011-06-22
WO2010036534A3 (en) 2010-06-10
CN102149838A (zh) 2011-08-10
WO2010036534A2 (en) 2010-04-01
KR101576194B1 (ko) 2015-12-10
DE112009002014B4 (de) 2020-02-13

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Owner name: BORGWARNER INC., MICHIGAN

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:SCHALL, GERALD;GABEL, MELANIE;REEL/FRAME:025973/0551

Effective date: 20091002

STCB Information on status: application discontinuation

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