US20110171008A1 - Turbocharger and adjustment ring therefor - Google Patents

Turbocharger and adjustment ring therefor Download PDF

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Publication number
US20110171008A1
US20110171008A1 US13/062,770 US200913062770A US2011171008A1 US 20110171008 A1 US20110171008 A1 US 20110171008A1 US 200913062770 A US200913062770 A US 200913062770A US 2011171008 A1 US2011171008 A1 US 2011171008A1
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US
United States
Prior art keywords
weight
adjustment ring
turbocharger
exhaust gas
resistance
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
US13/062,770
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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 US20110171008A1 publication Critical patent/US20110171008A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • 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
    • 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
    • C22C38/44—Ferrous alloys, e.g. steel alloys containing chromium with nickel with molybdenum or tungsten
    • 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
    • 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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2201/00—Metals
    • F05C2201/04—Heavy metals
    • F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
    • 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 invention relates to an adjustment ring for turbocharger applications, particularly in a diesel engine, according to the preamble of claim 1 , and also to an exhaust gas turbocharger having an adjustment ring, 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 in order to increase 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 adjustment ring has to satisfy extremely stringent material requirements.
  • the material forming the adjustment ring 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.
  • These physical properties of the material are also to be reflected in the component, that is to say the adjustment ring.
  • 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 adjustment ring according to the preamble of claim 1 or a turbocharger according to the preamble of claim 5 , which has improved temperature and oxidation resistance, and corrosion resistance under extreme temperatures, and also corresponding wet corrosion resistance, which is distinguished by optimal tribological properties and, moreover, which exhibits a reduced susceptibility to wear.
  • An adjustment ring is thus provided, or an exhaust gas turbocharger is provided which contains the adjustment ring 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 and corrosion resistance and, moreover, is also distinguished by very good sliding properties, along with reduced oxidizability.
  • the adjustment ring 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, consequently, the strength of the material and therefore the strength of the adjustment ring according to the invention are markedly increased on account of the unique structure of the latter.
  • the dispersions of the element nitrogen in the form of nitride structures in this case additionally increase the wear performance and corrosion resistance.
  • the maximum wear rate of the adjustment ring according to the invention in this case amounts to less than 0.14 mm for a bearing load of about 40 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, with a diesel exhaust gas as the test medium.
  • the material plainness of the adjustment ring according to the invention amounts to less than 0.14 mm in the case of a circumference with the diameter of 80 mm.
  • the material of the adjustment ring according to the invention has a carbide hardness of the dendritic carbide precipitations of 450 HV1. This very high value ensures the deformation resistance and high wear resistance of the material.
  • the material of the adjustment ring according to the invention can be welded by means of conventional welding methods such as WIG, plasma and also EB methods.
  • the adjustment ring is distinguished by a specific composition which contains the components C: 0.4 to 1.7% by weight, Cr: 23 to 43% by weight, Ni: 5 to 15% by weight, Mn: 8 to 16% by weight, Si: ⁇ 1.3% by weight, Mo: 0.45 to 4% by weight, W: 0.3 to 3.1% by weight, and Fe.
  • the adjustment ring according to the invention consists of a material which contains the following elements: C: 0.6 to 1.5% by weight, Cr: 26 to 38% by weight, Ni: 5 to 13% by weight, Mn: 10 to 14.5% by weight, Si: ⁇ 1% by weight, Mo: 0.75 to 3.5% by weight, W: 0.5 to 2.6% by weight, and Fe.
  • An adjustment ring produced in this way shows not only the high heat resistance of up to 900° C., but also markedly improved sliding properties.
  • the sliding wear is minimized here.
  • the corrosion resistance and, in particular, also the oxidation resistance are maximized.
  • the adjustment ring 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 a slight deviation, meet one another. Such sigma phases are undesirable because of their embattling 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 adjustment ring 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 was produced from the following elements according to a customary method, an adjustment ring according to the invention being formed from this alloy.
  • the chemical analysis gave the following values for the elements: C: 0.7 to 1.2% by weight; Cr: 27 to 33% by weight; Ni: 7 to 11% by weight; Mn: 10 to 14% by weight; Si: max. 1% by weight; Mo: 0.75 to 1.7% by weight; W: 0.5 to 1.5% by weight; the rest: iron.
  • the adjustment ring produced according to this example was distinguished by a tensile strength R m of 805 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 661 MPa.
  • the elongation at break of the material (measured according to standard methods) amounted to 5.2%.
  • the hardness of the material (measured according to ASTM E 92/ISO 6507-1) amounted to 364 HB.
  • 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 thus 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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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Combustion & Propulsion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Supercharger (AREA)
US13/062,770 2008-09-25 2009-09-21 Turbocharger and adjustment ring therefor Abandoned US20110171008A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102008048885 2008-09-25
DE102008048885.2 2008-09-25
PCT/US2009/057620 WO2010036591A2 (en) 2008-09-25 2009-09-21 Turbocharger and adjustment ring therefor

Publications (1)

Publication Number Publication Date
US20110171008A1 true US20110171008A1 (en) 2011-07-14

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ID=42060371

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/062,770 Abandoned US20110171008A1 (en) 2008-09-25 2009-09-21 Turbocharger and adjustment ring therefor

Country Status (6)

Country Link
US (1) US20110171008A1 (de)
JP (1) JP2012503744A (de)
KR (1) KR20110063664A (de)
CN (1) CN102149911A (de)
DE (1) DE112009002021T5 (de)
WO (1) WO2010036591A2 (de)

Cited By (2)

* 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
US20180016930A1 (en) * 2016-07-13 2018-01-18 Bosch Mahle Turbo Systems Gmbh & Co. Kg Adjustment ring of a variable turbine geometry

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20140033080A (ko) * 2011-05-19 2014-03-17 보르그워너 인코퍼레이티드 오스테나이트 철계 합금, 상기 철계 합금으로 이루어진 터보차저 및 구성요소
CN103614663A (zh) * 2013-11-28 2014-03-05 柳城县鼎铭金属制品有限公司 一种耐磨合金及其应用
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

Citations (10)

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US4015100A (en) * 1974-01-07 1977-03-29 Avco Everett Research Laboratory, Inc. Surface modification
US4560408A (en) * 1983-06-10 1985-12-24 Santrade Limited Method of using chromium-nickel-manganese-iron alloy with austenitic structure in sulphurous environment at high temperature
US4711677A (en) * 1986-07-18 1987-12-08 The Garrett Corporation High temperature bushing alloy
US5019332A (en) * 1988-03-16 1991-05-28 Carpenter Technology Corporation Heat, corrosion, and wear resistant steel alloy
US6123748A (en) * 1996-11-30 2000-09-26 Federal Mogul Sintered Products Limited Iron-based powder
US20040213665A1 (en) * 2001-05-10 2004-10-28 Shinjiro Ohishi Exhaust gas assembly with improved heat resistance for vgs turbocharger, method for manufacturing heat resisting member applicable thereto, and method for manufacturing shaped material for adjustable blade applicable thereto
JP2004339562A (ja) * 2003-05-15 2004-12-02 Air Water Inc オーステナイト系金属の表面改質方法およびそれによって得られる耐熱金属製品ならびにターボ部品
US20050194073A1 (en) * 2004-03-04 2005-09-08 Daido Steel Co., Ltd. Heat-resistant austenitic stainless steel and a production process thereof
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
US7186077B2 (en) * 2002-08-23 2007-03-06 Daimlerchrysler A G Compressor, particularly in an exhaust gas turbocharger for an internal combustion engine

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CN1250759C (zh) * 2002-03-31 2006-04-12 林晖 耐热耐蚀铁基合金的制造方法及其制造的产品
JP2004269979A (ja) * 2003-03-10 2004-09-30 Toyota Central Res & Dev Lab Inc 耐熱鋳鋼、鋳鋼製耐熱部材およびその製造方法
WO2006010383A1 (en) * 2004-07-30 2006-02-02 Honeywell International Inc. Turbocharger component
JP4234107B2 (ja) * 2005-02-10 2009-03-04 三菱重工業株式会社 可変容量型排気ターボ過給機及び可変ノズル機構構成部材の製造方法
CN101505910B (zh) * 2006-08-09 2012-01-04 Ing商事株式会社 铁基耐蚀耐磨损性合金以及用于获得该合金的堆焊材料

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4015100A (en) * 1974-01-07 1977-03-29 Avco Everett Research Laboratory, Inc. Surface modification
US4560408A (en) * 1983-06-10 1985-12-24 Santrade Limited Method of using chromium-nickel-manganese-iron alloy with austenitic structure in sulphurous environment at high temperature
US4711677A (en) * 1986-07-18 1987-12-08 The Garrett Corporation High temperature bushing alloy
US5019332A (en) * 1988-03-16 1991-05-28 Carpenter Technology Corporation Heat, corrosion, and wear resistant steel alloy
US6123748A (en) * 1996-11-30 2000-09-26 Federal Mogul Sintered Products Limited Iron-based powder
US20040213665A1 (en) * 2001-05-10 2004-10-28 Shinjiro Ohishi Exhaust gas assembly with improved heat resistance for vgs turbocharger, method for manufacturing heat resisting member applicable thereto, and method for manufacturing shaped material for adjustable blade applicable thereto
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
US7186077B2 (en) * 2002-08-23 2007-03-06 Daimlerchrysler A G Compressor, particularly in an exhaust gas turbocharger for an internal combustion engine
JP2004339562A (ja) * 2003-05-15 2004-12-02 Air Water Inc オーステナイト系金属の表面改質方法およびそれによって得られる耐熱金属製品ならびにターボ部品
US20050194073A1 (en) * 2004-03-04 2005-09-08 Daido Steel Co., Ltd. Heat-resistant austenitic stainless steel and a production process thereof

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Cited By (4)

* 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
US20180016930A1 (en) * 2016-07-13 2018-01-18 Bosch Mahle Turbo Systems Gmbh & Co. Kg Adjustment ring of a variable turbine geometry
US10633999B2 (en) * 2016-07-13 2020-04-28 BMTS Technology GmbH & Co. KG Adjustment ring of a variable turbine geometry

Also Published As

Publication number Publication date
WO2010036591A3 (en) 2010-05-27
DE112009002021T5 (de) 2011-07-28
CN102149911A (zh) 2011-08-10
JP2012503744A (ja) 2012-02-09
WO2010036591A2 (en) 2010-04-01
KR20110063664A (ko) 2011-06-13

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AS Assignment

Owner name: BORGWARNER INC., MICHIGAN

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:SCHALL, GERALD;GABEL, MELANIE;REEL/FRAME:025973/0407

Effective date: 20091002

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION