EP0589072A1 - Turbocompresseur pour fonctionnement avec du carburant lourd - Google Patents

Turbocompresseur pour fonctionnement avec du carburant lourd Download PDF

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Publication number
EP0589072A1
EP0589072A1 EP92116081A EP92116081A EP0589072A1 EP 0589072 A1 EP0589072 A1 EP 0589072A1 EP 92116081 A EP92116081 A EP 92116081A EP 92116081 A EP92116081 A EP 92116081A EP 0589072 A1 EP0589072 A1 EP 0589072A1
Authority
EP
European Patent Office
Prior art keywords
protection layer
turbocharger
erosion protection
turbocharger according
turbine wheel
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.)
Withdrawn
Application number
EP92116081A
Other languages
German (de)
English (en)
Inventor
Claus Dr. Gerdes
Carlo M. Maggi
Marcel Zehnder
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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Priority to EP92116081A priority Critical patent/EP0589072A1/fr
Priority to PL93300425A priority patent/PL300425A1/xx
Priority to JP5233478A priority patent/JPH084544A/ja
Priority to KR1019930019187A priority patent/KR940007338A/ko
Publication of EP0589072A1 publication Critical patent/EP0589072A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades

Definitions

  • the invention is based on a turbocharger for heavy oil operation with an exhaust gas turbine which is exposed to the eroding effect of abrasive particles and has an erosion protection layer.
  • the invention relates to a state of the art, such as that from a lecture given by E. Müller, BBC Brown, Boveri & Cie., Baden / Switzerland at the SMM Hamburg symposium, September 1984 on the subject of "exhaust gas turbochargers in heavy oil use” results.
  • turbocharger components such as housings, nozzle rings, rotor blades and cover rings, which occur during the combustion of heavy oil in an engine, can cause damage which can impair the operating behavior of the engine or even cause it to fail being able to lead.
  • the invention has for its object to provide a turbocharger which is simple in construction and is characterized by a long service life and low maintenance requirements even when it is exposed to a high concentration of abrasive particles during operation .
  • the turbocharger according to the invention is distinguished from comparable turbochargers according to the prior art in that it is simple and inexpensive and nevertheless has a long service life. This is primarily a result of an easy-to-manufacture, well-adhering and extremely erosion-resistant surface, but is also due to the fact that the surface coating is primarily provided in areas of the turbocharger that not only have the direct but also the indirect effect of abrasive residues from the exhaust gas heavy oil powered engine is exposed.
  • Another advantage of the turbocharger according to the invention is that the erosion protection layers have a thermal insulation effect and thereby protect the material carrying the layers from thermal shocks.
  • FIG. 1 shows a turbocharger with an axially flowing exhaust gas turbine 1 and a compressor 2.
  • Exhaust gases from a motor (not shown) operated with heavy oil are guided in the direction of an arrow (not designated) via a gas inlet duct 3 into the exhaust gas turbine 1 of the turbocharger.
  • a gas inlet duct 3 After flowing through a nozzle ring 5 attached to an annular gas outlet flange 4 of the gas inlet channel 3, the exhaust gas is guided in the axial direction against the blades 6 of a turbine wheel 7, which is arranged on a common shaft 9 with a compressor wheel 8 provided in the compressor 2.
  • the nozzle ring 5 is adjoined by a cover ring 11 which delimits the turbine wheel 7 in the radial direction with almost no gap and is fastened to a housing 10 of the exhaust gas turbine 1.
  • the exhaust gas After flowing through the exhaust gas turbine 1, the exhaust gas is guided outward from the housing 10 of the exhaust gas turbine 1 in the direction of an arrow 12. Air flowing in the direction of arrows 13 is supplied to the compressor 2. This air is compressed by the compressor wheel 8 driven by the shaft 9. The compressed air is directed in the direction of arrows 14 into a duct 15 acting on the motor.
  • the surface areas of the exhaust gas turbine 1 which are exposed to the action of the abrasive particles are provided with an erosion protection layer which is applied to the protective layer-free surface of the exhaust gas turbine 1 in a thermal spraying process and contains carbide hard materials.
  • Such an erosion protection layer increases the erosion resistance of the exhaust gas turbine 1 and thus the lifespan of the turbocharger according to the invention compared to turbochargers with uncoated exhaust gas turbines by a multiple.
  • erosion protection layers 16 are provided on the components shown in FIGS. 2-6:
  • the erosion protection layer 16 is applied to an annular edge 17 adjoining the nozzle ring 5 and to the inner surface 18 of the cover ring 11.
  • This inner surface 18 is particularly strongly exposed to the eroding effect of the abrasive particles thrown tangentially outward from the turbine wheel 7 during operation of the turbocharger and should be of particularly thick design.
  • the erosion protection layer 16 is arranged in such a way that it forms at least part of the surface of the turbine wheel 7 in the region of the abrasive particles impinging on the turbine wheel 7 during operation of the turbocharger. At least the erosion protection layer 16 forms the surface of the tip 19 of the blade 6 in the region of the leading edge 20 of the blade 6 in each of the blades of the turbine wheel 7.
  • the erosion protection layer 16 is located at a nozzle-shaped constriction and at a cone-shaped widening which follows downstream of the constriction and extends towards the nozzle ring 5.
  • the erosion protection layer 16 forms at least the surfaces of the trailing edges 24, the surfaces of the sides of the guide blades 21 facing the turbine wheel 7 and the surfaces the sides of the retaining rings 22, 23 facing the turbine wheel 7.
  • the housing When there is a radial flow against the exhaust gas turbine, it is expedient to provide the housing with the erosion protection layer 16 at all points exposed to the eroding effect of the abrasive particles. If - as shown in FIG. 7 - the housing 10 surrounds the turbine wheel (not shown) in a spiral, in this embodiment of the turbocharger according to the invention the erosion protection layer 16 forms at least part of the inner surface of the housing 10 facing the turbine wheel.
  • An erosion protection layer is particularly recommended, which in addition to carbide has a matrix material made of a material with a comparatively high ductility compared to carbide as well as with long-term stability at the exhaust gas temperatures and with good adhesion to the protective layer-free material of the exhaust gas turbine 1.
  • the proportion of the matrix material should be considered the erosion control layer is at most 35 percent by weight, preferably between 15 and 25 percent by weight.
  • Such matrix materials not only have great stability at an exhaust gas temperature of possibly 700 ° C. and good adhesion to the materials used for the components of the exhaust gas turbine 1, they also bring about an elastic storage of the erosion-resistant, brittle and hard carbide particles, of which special Erosion and temperature resistant chromium carbide Cr3C2 has
  • the thermally sprayed erosion protection layer should have a thickness of between 50 and 300 ⁇ m, depending on the position in the exhaust gas turbine 1. At the turbine wheel 7, d. H. in particular at the tips 19 of the blades 6, it is sufficient if the thickness of the erosion protection layer 16 is at most 150 ⁇ m.
  • erosion protection layers of the same composition and same thickness were applied to comparable components of the exhaust gas turbine 1, such as the blades 6, and the quality of the applied protection layer was determined by measuring the relative erosion removal.
  • the erosion protection layer contained 20 to 25 percent by weight NiCr as the matrix material, in which the rest Cr3C2 was embedded in powder form. It was found that in all of these erosion protection layers applied by thermal spraying, there is a four to five-fold reduction in erosion removal compared to an erosion protection layer that is produced using a different method, for example by baking in an enamel has been.
  • erosion protection layers which were applied by plasma spraying
  • erosion protection layers which were applied by detonation spraying or by high-speed flame spraying, show an approximately 20% lower erosion removal.
  • An additional reduction of the erosion removal could be achieved with all thermally sprayed layers, which contained a certain matrix material, by a subsequent heat treatment.
  • the erosion removal of an erosion protection layer with CoCrAlY as a matrix material could be reduced by almost half compared to an untreated erosion protection layer after a 40-hour heat treatment at 400 ° C or a 4-hour heat treatment at 600 ° C. After 1000 hours of heat treatment at approx. 700 ° C, ie practically under operating conditions, this erosion removal was reduced by a few percent.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Plasma & Fusion (AREA)
  • Physics & Mathematics (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)
EP92116081A 1992-09-21 1992-09-21 Turbocompresseur pour fonctionnement avec du carburant lourd Withdrawn EP0589072A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP92116081A EP0589072A1 (fr) 1992-09-21 1992-09-21 Turbocompresseur pour fonctionnement avec du carburant lourd
PL93300425A PL300425A1 (en) 1992-09-21 1993-09-17 Turbosupercharger for heavy oil engines
JP5233478A JPH084544A (ja) 1992-09-21 1993-09-20 重油運転用ターボ過給器
KR1019930019187A KR940007338A (ko) 1992-09-21 1993-09-21 중유구동용 터보과급기

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP92116081A EP0589072A1 (fr) 1992-09-21 1992-09-21 Turbocompresseur pour fonctionnement avec du carburant lourd

Publications (1)

Publication Number Publication Date
EP0589072A1 true EP0589072A1 (fr) 1994-03-30

Family

ID=8210025

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92116081A Withdrawn EP0589072A1 (fr) 1992-09-21 1992-09-21 Turbocompresseur pour fonctionnement avec du carburant lourd

Country Status (4)

Country Link
EP (1) EP0589072A1 (fr)
JP (1) JPH084544A (fr)
KR (1) KR940007338A (fr)
PL (1) PL300425A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0961017A2 (fr) * 1998-05-28 1999-12-01 Mitsubishi Heavy Industries, Ltd. Revêtement de protection résistant aux températures élevées
WO2002092980A1 (fr) 2001-05-10 2002-11-21 Soghi Kogyo Co., Ltd. Ensemble de guidage de gaz d'echappement a surface reformee dans un turbocompresseur de type vgs et procede de reformage de surface des elements constitutifs de cet ensemble
WO2009006871A2 (fr) * 2007-07-09 2009-01-15 Mtu Aero Engines Gmbh Aube pour turbomachine
WO2009049796A1 (fr) * 2007-10-09 2009-04-23 Man Turbo Ag Composant traversé par du gaz chaud d'une turbomachine

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2002317641A (ja) * 2001-04-24 2002-10-31 Ishikawajima Harima Heavy Ind Co Ltd タービンハウジング内壁の溶射方法
JP4514985B2 (ja) * 2001-05-10 2010-07-28 株式会社アキタファインブランキング Ｖｇｓタイプターボチャージャにおける排気ガイドアッセンブリの構成部材の表面改質方法並びにこの表面改質方法を施した排気ガイドアッセンブリ
JP2002332851A (ja) * 2001-05-10 2002-11-22 Sogi Kogyo Kk 超合金により構成される耐久性を向上させたｖｇｓタイプターボチャージャの排気ガイドアッセンブリ
JP2002332857A (ja) * 2001-05-10 2002-11-22 Sogi Kogyo Kk 表面改質を施したｖｇｓタイプターボチャージャの排気ガイドアッセンブリ
JP4624595B2 (ja) * 2001-05-10 2011-02-02 株式会社アキタファインブランキング 表面改質を施したｖｇｓタイプターボチャージャの排気ガイドアッセンブリ
JP2002332553A (ja) * 2001-05-10 2002-11-22 Sogi Kogyo Kk 希土類元素等を添加した部材により構成される高温耐久性を向上させたｖｇｓタイプターボチャージャの排気ガイドアッセンブリ
JP6463640B2 (ja) * 2015-01-27 2019-02-06 川崎重工業株式会社 舶用排気タービン

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2006274A (en) * 1977-10-17 1979-05-02 United Technologies Corp Oxidation and Wear Resistant Coated Article
EP0482831A1 (fr) * 1990-10-18 1992-04-29 Praxair S.T. Technology, Inc. Production de revêtements à base de nickel et de carbure de chrome

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2006274A (en) * 1977-10-17 1979-05-02 United Technologies Corp Oxidation and Wear Resistant Coated Article
EP0482831A1 (fr) * 1990-10-18 1992-04-29 Praxair S.T. Technology, Inc. Production de revêtements à base de nickel et de carbure de chrome

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
DATABASE WPIL Week 8529, Derwent Publications Ltd., London, GB; AN 85-173611 & JP-A-60 077 968 (GENERAL ELECTRIC CO) 2. Mai 1985 *
PATENT ABSTRACTS OF JAPAN vol. 7, no. 254 (M-255)(1399) 11. November 1983 & JP-A-58 138 202 ( TOKYO SHIBAURA DENKI ) 17. August 1983 *
SCHIFF,MASCHINE,MEERSTECHNIK INT September 1984, SYMPOSIUM SMM HAMBURG Seiten 59 - 67 E. M]LLER 'abgasturbolader im schweröleinsatz' *

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0961017A2 (fr) * 1998-05-28 1999-12-01 Mitsubishi Heavy Industries, Ltd. Revêtement de protection résistant aux températures élevées
EP0961017A3 (fr) * 1998-05-28 2001-03-14 Mitsubishi Heavy Industries, Ltd. Revêtement de protection résistant aux températures élevées
US6548161B1 (en) 1998-05-28 2003-04-15 Mitsubishi Heavy Industries, Ltd. High temperature equipment
WO2002092980A1 (fr) 2001-05-10 2002-11-21 Soghi Kogyo Co., Ltd. Ensemble de guidage de gaz d'echappement a surface reformee dans un turbocompresseur de type vgs et procede de reformage de surface des elements constitutifs de cet ensemble
EP1396621A1 (fr) * 2001-05-10 2004-03-10 Soghi Kogyo Co., Ltd. Ensemble de guidage de gaz d'echappement a surface reformee dans un turbocompresseur de type vgs et procede de reformage de surface des elements constitutifs de cet ensemble
EP1396621A4 (fr) * 2001-05-10 2007-06-13 Akita Fine Blanking Co Ltd Ensemble de guidage de gaz d'echappement a surface reformee dans un turbocompresseur de type vgs et procede de reformage de surface des elements constitutifs de cet ensemble
WO2009006871A2 (fr) * 2007-07-09 2009-01-15 Mtu Aero Engines Gmbh Aube pour turbomachine
WO2009006871A3 (fr) * 2007-07-09 2009-03-26 Mtu Aero Engines Gmbh Aube pour turbomachine
WO2009049796A1 (fr) * 2007-10-09 2009-04-23 Man Turbo Ag Composant traversé par du gaz chaud d'une turbomachine
US9926629B2 (en) 2007-10-09 2018-03-27 Man Diesel & Turbo Se Hot gas-guided component of a turbomachine

Also Published As

Publication number Publication date
JPH084544A (ja) 1996-01-09
KR940007338A (ko) 1994-04-27
PL300425A1 (en) 1994-04-18

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