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EP3282130A1 - Système de couches, turbine et procédé de production - Google Patents

Système de couches, turbine et procédé de production Download PDF

Info

Publication number
EP3282130A1
EP3282130A1 EP16183478.3A EP16183478A EP3282130A1 EP 3282130 A1 EP3282130 A1 EP 3282130A1 EP 16183478 A EP16183478 A EP 16183478A EP 3282130 A1 EP3282130 A1 EP 3282130A1
Authority
EP
European Patent Office
Prior art keywords
layer
layer system
lsy
impeller
base element
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Withdrawn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
EP16183478.3A
Other languages
German (de)
English (en)
Inventor
Peter MARTINIUS
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.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to EP16183478.3A priority Critical patent/EP3282130A1/fr
Priority to EP17739949.0A priority patent/EP3472472B1/fr
Priority to PCT/EP2017/067260 priority patent/WO2018028908A1/fr
Priority to RU2019106322A priority patent/RU2708187C1/ru
Priority to CN201780048354.5A priority patent/CN109642583A/zh
Publication of EP3282130A1 publication Critical patent/EP3282130A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/226—Carbides
    • F05D2300/2263—Carbides of tungsten, e.g. WC

Definitions

  • the invention refers to a layer system comprising a base material of a base element, wherein said layer system extends in a border area of said base element up to an outer surface, wherein said layer system comprises at least one layer of cladding material provided onto the base material.
  • the invention relates to an impeller of a turbo-machine, in particular a turbo-compressor, in particular a centrifugal turbo-compressor, wherein said impeller comprises a base element of a base material comprising blades being arranged along a circumferential direction of a rotational axis, wherein said blades comprise a leading edge and a trailing edge.
  • the invention relates to a method to produce a layer system and a method to produce an impeller respectively according to the before mentioned type.
  • the specific focus of the invention is the avoidance of erosion in particular in turbo-machinery and in particular with regard to turbo-compressors.
  • the rotating parts, especially the impellers of the turbo machine may suffer from a dramatic decrease in lifetime due to severe erosion wear.
  • Dust particles carries by a process fluid through the machine for example so called 'black dust', may have hardnesses between 230 up to 600HV 0.01 (Vickers hardness test).
  • the rotating parts of pipeline compressors are quickly damaged in particular at the leading edge and the trailing edge of impeller blades.
  • the invention proposes a layer system, an impeller and a method to produce such a layer system or an impeller as according to the respective independent claims.
  • the respective dependent claims refer to beneficial embodiments of the invention.
  • the layer system according to the invention comprises said base material and one or several of cladding material layers provided onto the base material. Further said layer system comprises a compressive residual stress layer extending from said outer surface into at least the outermost layer of cladding material. In case of several cladding material layers provided on a base material as part of the layer system said compressive residual stress layer may extend through several layers of cladding material from said outer surface and even extend into the base material as well. Preferably said compressive residual stress layer extends only in the outermost layer of cladding material.
  • a preferred embodiment of the invention is provided by generating said layer or layers of cladding material by gas tungsten arc welding (GTAW).
  • GTAW gas tungsten arc welding
  • a base material is X3CrNiMo13-4 (martensitic alloy).
  • X3CrNiMo13-4 material number: 1.4313 according to EN10250
  • weight percent wt%
  • Stellite 21 is Element Minimum Maximum Carbon (C) 0.15 0.40 Mangan (Mn) 0 1.0 Chromium (Cr) 25 30 Silicon (Si) 0 1.5 Molybdenum (Mo) 4.5 7.0 Nickel (Ni) 1.5 3 Iron (Fe) 0 5.0 Tungsten (W) 0 0.5 Cobald (Co) base others 0 1.0
  • One preferred embodiment provides that at least two layers of cladding material are provided to the base material and most preferably three layers of cladding material are provided. Preferably all three layers are of the same chemical composition and most preferably all three layers are of Stellite 21.
  • Another preferred embodiment of the layer system is provided by giving a heat treatment of up to three hours at 570°C to the base element for at least one time to eliminate residual welding stresses. Surprisingly it was found that the subsequent heat treatment as proposed does not impair the desirable high hardness of the cladding.
  • the most preferred application of the invention is the production of an impeller of a turbo-machine, in particular a turbo-compressor, in particular a centrifugal turbo-compressor, wherein said impeller comprises a base element of a base material comprising blades being arranged along a circumferential direction of a rotational axis, wherein said blades comprise a leading edge and a trailing edge, wherein said leading edge and said trailing edge belong to a surface treatment zone, wherein at least part of said surface treatment zone is a layer system as described and defined in several embodiments above.
  • these impeller blades are attached to a hub section of said base element and are extending radially and/or axially from said hub section.
  • Said impeller can be designed as a so called open type or closed type.
  • flow channels are circumferentially delimited by said blades, a hub section and a shroud section being attached to the blades tips respectively defining the flow channels in axial-radial direction.
  • the hub section defines the flow channels in axial-radial direction (see also figure 1, 2 regarding the difference).
  • the layer system in particular the layer system of the impeller is produced applying the following steps:
  • a further substep is conducted by:
  • step 3 a further forth step can be conducted as:
  • a preferred embodiment of the impeller is provided by machining the base element with additional grooves respectively recesses compared to the ordinary impeller in the area of the surface treatment zone where the layer system according to the invention is provided.
  • Theses recesses may be provided cumulatively or alternatively like the following:
  • FIG. 1 and figure 2 respectively show a 2-dimensional longitudinal section through an impeller according to the invention along a rotational axis X.
  • the impeller IMP rotates during operation in a turbo-machine, in particular in a turbo-compressor TC around the rotational axis X.
  • Said impeller IMP comprises a based element BE of a base material BM comprising blades BLA being arranged along a circumferential direction CDR of said rotational axis X.
  • These blades BLA comprise a leading edge LE and a trailing edge TE.
  • the terms 'leading edge LE' and 'trailing edge TE' refer to a process fluid flow direction during operation for which the impeller IPM is fluid dynamically designed.
  • Said leading edge LE and said trailing edge TE belong to a surface treatment zone STZ.
  • a layer system LSY is provided to said surface treatment zone STZ.
  • This layer system LSY is shown in figure 4 schematically in a longitudinal section in detail in a border area (shown as a detail in Figure 4 ) of said base element BE.
  • Said layer system LSY comprises said base material BM of said base element BE and extends in said border area of said base element BE up to an outer surface OSF.
  • said layer system LSY comprises three layers of cladding material, a first layer LCM1, a second layer LCM2 and a third layer LCM3. This number of layers is an example which what was found to be advantageous.
  • Figure 3 shows schematically the steps of the method according to the invention to produce a layer system LSY as part of a base element BE here an impeller IMP.
  • this example of figure 3 refers to the impeller IMP but basically includes the generation of a layer system according to the invention to other parts as well preferably rotating parts of turbo-machines.
  • step 0 a raw part is provided, which is subsequently machined into the basic shape of an impeller IMP during steps 1), 2).
  • step 2) a surface treatment zone STZ is defined.
  • the impeller IMP is machined with additional grooves in the area of the leading edge LE and the trailing edge TE belonging to the surface treatment zone STZ of the base element BE. These additional grooves respectively recesses RE are provided to avoid any protrusion due to the provision of the layer system LSY in this areas.
  • the final impeller IMP is meant to have the same fluid dynamic properties as any conventional impeller IMP.
  • step 3) a) the surface treatment zone STZ defined during step 2) is transformed at least partly into said layer system LSY by the substeps of:
  • the resulting impeller IMP including the layer system LSY applied by gas tungsten arc welding cladding of Stellite 21 powder onto the base element BE or base material X3CrNiMo13-4 results in an erosion resistant rotating part having partly a high hardness of approximately 690HV0.01 after heat treatment. In these critical areas of the surface treatment zones STZ the impeller surface is therefore harder than the maximum particle hardness of approximately 600hv0.01.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP16183478.3A 2016-08-10 2016-08-10 Système de couches, turbine et procédé de production Withdrawn EP3282130A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP16183478.3A EP3282130A1 (fr) 2016-08-10 2016-08-10 Système de couches, turbine et procédé de production
EP17739949.0A EP3472472B1 (fr) 2016-08-10 2017-07-10 Système de couches, turbine et procédé de production
PCT/EP2017/067260 WO2018028908A1 (fr) 2016-08-10 2017-07-10 Système de couches, turbine, procédé de production
RU2019106322A RU2708187C1 (ru) 2016-08-10 2017-07-10 Крыльчатка и способ ее изготовления
CN201780048354.5A CN109642583A (zh) 2016-08-10 2017-07-10 层系统、叶轮及生产方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16183478.3A EP3282130A1 (fr) 2016-08-10 2016-08-10 Système de couches, turbine et procédé de production

Publications (1)

Publication Number Publication Date
EP3282130A1 true EP3282130A1 (fr) 2018-02-14

Family

ID=56618048

Family Applications (2)

Application Number Title Priority Date Filing Date
EP16183478.3A Withdrawn EP3282130A1 (fr) 2016-08-10 2016-08-10 Système de couches, turbine et procédé de production
EP17739949.0A Active EP3472472B1 (fr) 2016-08-10 2017-07-10 Système de couches, turbine et procédé de production

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP17739949.0A Active EP3472472B1 (fr) 2016-08-10 2017-07-10 Système de couches, turbine et procédé de production

Country Status (4)

Country Link
EP (2) EP3282130A1 (fr)
CN (1) CN109642583A (fr)
RU (1) RU2708187C1 (fr)
WO (1) WO2018028908A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3708774A1 (fr) * 2019-03-13 2020-09-16 Siemens Aktiengesellschaft Aube directrice et cascade fixe pour une turbomachine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2135698A1 (fr) * 2008-06-19 2009-12-23 General Electric Company Procédés de traitement d'articles métallique et articles fabriqués à partir de ces procédés
DE102009043097A1 (de) * 2009-09-25 2011-03-31 Siemens Aktiengesellschaft Laufschaufel zur Verwendung in Zweiphasenströmungen sowie Verfahren zum Herstellen einer solchen Laufschaufel
US20110229338A1 (en) * 2009-11-21 2011-09-22 Michael Voong Compressor wheel
EP2789713A1 (fr) * 2013-04-10 2014-10-15 General Electric Company Systèmes de revêtement résistant à l'érosion et procédés associés

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
TWI272993B (en) * 2002-10-09 2007-02-11 Ishikawajima Harima Heavy Ind Method for coating rotary member, rotary member, labyrinth seal structure and method for manufacturing rotary member
FR2861143B1 (fr) * 2003-10-20 2006-01-20 Snecma Moteurs Aube de turbomachine, notamment aube de soufflante et son procede de fabrication
GB0425088D0 (en) * 2004-11-13 2004-12-15 Holset Engineering Co Compressor wheel
US7304266B2 (en) * 2004-12-09 2007-12-04 General Electric Company Laser shock peening coating with entrapped confinement medium
CN100540208C (zh) * 2006-12-22 2009-09-16 沈阳大陆激光技术有限公司 一种离心压缩机流道叶片的修复工艺
IT1397057B1 (it) * 2009-11-23 2012-12-28 Nuovo Pignone Spa Girante centrifuga e turbomacchina
US9534499B2 (en) * 2012-04-13 2017-01-03 Caterpillar Inc. Method of extending the service life of used turbocharger compressor wheels
CN104279186A (zh) * 2014-09-17 2015-01-14 杭州杭氧透平机械有限公司 一种大流量超大直径半铣半焊闭式三元叶轮及制造方法
CN105200226A (zh) * 2015-08-21 2015-12-30 江苏大学 一种提高金属材料疲劳寿命的方法

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2135698A1 (fr) * 2008-06-19 2009-12-23 General Electric Company Procédés de traitement d'articles métallique et articles fabriqués à partir de ces procédés
DE102009043097A1 (de) * 2009-09-25 2011-03-31 Siemens Aktiengesellschaft Laufschaufel zur Verwendung in Zweiphasenströmungen sowie Verfahren zum Herstellen einer solchen Laufschaufel
US20110229338A1 (en) * 2009-11-21 2011-09-22 Michael Voong Compressor wheel
EP2789713A1 (fr) * 2013-04-10 2014-10-15 General Electric Company Systèmes de revêtement résistant à l'érosion et procédés associés

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3708774A1 (fr) * 2019-03-13 2020-09-16 Siemens Aktiengesellschaft Aube directrice et cascade fixe pour une turbomachine

Also Published As

Publication number Publication date
WO2018028908A1 (fr) 2018-02-15
RU2708187C1 (ru) 2019-12-04
EP3472472A1 (fr) 2019-04-24
CN109642583A (zh) 2019-04-16
EP3472472B1 (fr) 2020-04-22

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