EP1215366B1 - Aube de turbine - Google Patents

Aube de turbine Download PDF

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Publication number
EP1215366B1
EP1215366B1 EP01890337A EP01890337A EP1215366B1 EP 1215366 B1 EP1215366 B1 EP 1215366B1 EP 01890337 A EP01890337 A EP 01890337A EP 01890337 A EP01890337 A EP 01890337A EP 1215366 B1 EP1215366 B1 EP 1215366B1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
martensitic
hiping
impurities
rest
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.)
Expired - Lifetime
Application number
EP01890337A
Other languages
German (de)
English (en)
Other versions
EP1215366A2 (fr
EP1215366A3 (fr
Inventor
Gerhard Hackl
Gabriele Saller
Raimund Huber
Rupert Winkelmeier
Günter Schirninger
Michael Dipl. Ing. Stromberger
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.)
Voestalpine Boehler Edelstahl GmbH and Co KG
Original Assignee
Boehler Edelstahl GmbH and Co KG
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 Boehler Edelstahl GmbH and Co KG filed Critical Boehler Edelstahl GmbH and Co KG
Priority to SI200130995T priority Critical patent/SI1215366T1/sl
Publication of EP1215366A2 publication Critical patent/EP1215366A2/fr
Publication of EP1215366A3 publication Critical patent/EP1215366A3/fr
Application granted granted Critical
Publication of EP1215366B1 publication Critical patent/EP1215366B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C33/00—Making ferrous alloys
    • C22C33/02—Making ferrous alloys by powder metallurgy
    • C22C33/0257—Making ferrous alloys by powder metallurgy characterised by the range of the alloying elements
    • C22C33/0278—Making ferrous alloys by powder metallurgy characterised by the range of the alloying elements with at least one alloying element having a minimum content above 5%
    • C22C33/0285—Making ferrous alloys by powder metallurgy characterised by the range of the alloying elements with at least one alloying element having a minimum content above 5% with Cr, Co, or Ni having a minimum content higher than 5%
    • 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
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/42—Ferrous alloys, e.g. steel alloys containing chromium with nickel with copper
    • 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
    • C22C38/60—Ferrous alloys, e.g. steel alloys containing lead, selenium, tellurium, or antimony, or more than 0.04% by weight of sulfur
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/24—After-treatment of workpieces or articles
    • B22F2003/247—Removing material: carving, cleaning, grinding, hobbing, honing, lapping, polishing, milling, shaving, skiving, turning the surface
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/24—After-treatment of workpieces or articles
    • B22F2003/248—Thermal after-treatment
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B22F2998/10—Processes characterised by the sequence of their steps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2999/00—Aspects linked to processes or compositions used in powder metallurgy

Definitions

  • the invention relates to a turbine blade for steam or gas turbines and compressors, which blade is made of starting material by machining and thermally treated or annealed.
  • Turbine blades with a shape required for the respective use in the turbines and compressors can be made by the drop forging method by machining from a billet or by forging on a blank with a subsequent chip removal.
  • the starting material is prepared from forged in molds alloys by forging and / or rolling and optionally heat treated for further processing. It is known to use ingots, continuous billets or remelting blocks for the production of primary material.
  • Turbines for two-phase generators have a number of revolutions of 3000 and 3600 min -1, which provides high benefits of the same considerable stresses on the blades.
  • the turbine blades produced by the method described in the introduction have segregations over the cross-section and optionally in the axial or longitudinal direction, which result from the blockage solidification.
  • these inhomogeneities are stretched and partially reduced by diffusion, but perfect material homogeneity can not be achieved.
  • remelt blocks such as electro-slag remelting or vacuum remelting blocks is usually not complete isotropy of the alloy material achievable.
  • a turbine blade now has anisotropy with segregations extending eccentrically over the cross-section, then the heating and / or stressing thereof can lead to the emanation of the blade ends from the intended position, which has to be considered by the turbine manufacturer.
  • an enhanced segregation image may be disclosed by the magnetic powder method.
  • turbine construction turbine blades are required in view of a high Verhegbarkelt and safety of the heat engines, on the one hand have the highest possible material homogeneity and on the other hand have a low creep of the material at operating temperature.
  • the invention has the object to provide turbine blades, which are machined on the flow surfaces and meet the above requirements.
  • the advantages achieved by the invention are essentially that a, according to the powder metallurgical (PM) - produced semi-finished material is essentially free of segregation and a high material homogeneity of it ensured turbine blade ensures. Even with a high degree of deformation or a large longitudinal extension of the material, the homogeneity, in particular over the cross section is maintained, whereby no tendency of bending of the free blade ends is given.
  • PM powder metallurgical
  • the starting material after hot isostatic pressing HIP-en
  • as-HIP-ed undeformed (as-HIP-ed) machined
  • a particularly economical production of the turbine blade can be achieved.
  • an undeformed PM turbine blade that is to say in the so-called "AS-HIPED” state, can not have the desired mechanical material properties, it has been found that such a blade has in some cases even improved quality features.
  • the PM starting material consists of an iron-based alloy, which is free from ledeburit, is formed.
  • the PM process has been developed in particular for alloys which form primary precipitates, for example carbides, during solidification and this process can not be effective in the case of steels which have not ledeburit-free hardening, it has surprisingly been found that an essential quality assessment of the blade alloy material can be achieved .
  • a turbine blade for high thermal and mechanical, in particular dynamic loads and a lack of tendency to end bending in practical use can be produced if the PM starting material consists of a martensitic chromium steel with a composition of% by weight.
  • the synergetic effect of the alloying elements of the PM material is favorable in many respects for turbine blades.
  • the machinability of the material is significantly improved, on the other hand, while maintaining a certain Mn / S ratio, the mechanical properties remain unchanged even at frequent operating cycles at a high level.
  • the PM material consists of a soft-martensitic or nickel-martensitic steel having a composition of in% by weight.
  • B to 0.01
  • PM base material made of a nickel base or cobalt base alloy or an alloy containing less than 29 wt .-% iron is formed.
  • a chromium content is provided which is at least 14 wt .-% in order to bring nitrogen, which exerts a beneficial effect on the material properties, in solution.
  • the width of the samples was 1/4 of the side length D of the billet.
  • FIG. 3 A trial is in Fig. 3 shown schematically.
  • the Probeneinput took place in a holder 3, wherein a clamping piece 22 of a sample 2 was fixed in this. With different heating rates, a respective heating of the sample 2, which were then held at temperatures between 300 ° C and 550 ° C was carried out. In this case, a measurement of the deviation of the sample end opposite the clamping took place.

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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)
  • Manufacturing & Machinery (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Powder Metallurgy (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (6)

  1. Aube de turbine pour des turbines à vapeur ou à gaz, ou aube de compresseur d'un acier chromé martensitique, en pourcentage en poids, ayant une composition de chrome (Cr) 8,0 à 29,0 carbone (C) 0,1 à 0,4 azote (N) 0,005 à 0,3 (C + N) 0,11 à 0,4 molybdène (Mo) 0,5 à 2,0 vanadium (V) 0,08 à 1,0 silicium (Si) 0,05 à 0,6 manganèse (Mn) 0,05 à 2,0 soufre (S) 0,002 à 0,49 (Mn/S) 2,0 en minimum tungstène (W) jusqu'à 2,5 nickel (Ni) 3,0 en maximum niobium (Nb) jusqu'à 0,12 bore (B) jusqu'à 0,01 fer (Fe) le reste
    ainsi que des impuretés conditionnés par la fabrication, formée par un matériau préliminaire produit par la métallurgie des poudres (PM), en pulvérisant une fonte par atomisation à gaz au moyen d'azote et par compression isostatique à température élevée (HIP) du poudre, ledit matériau étant usiné par enlèvement de copeaux, et l'aube de turbine ou de compresseur ainsi fabriquée est traitée de manière thermique ou trempée et revenue et, à une température ambiante, a les propriété suivantes de matériau : résistance à la traction : Rm = au moins 700 N/mm2 limite élastique : R0,2 = au moins 550 N/mm2 allongement : A = au moins 15% striction : Z = au moins 10%.
  2. Aube de turbine ou de compresseur selon la revendication 1 d'un acier chromé martensitique, en pourcentage en poids, ayant une composition de Cr = 8,0 à 22,0, de préférence 9,0 à 16,0 C = 0,1 à 0,35 de préférence 0,15 à 0,3 N = 0,005 à 0,28 de préférence 0,1 à 0,24 (C+N) = 0,16 à 0,4 de préférence 0,21 à 0,29 Mo = 0,5 à 2,0 de préférence 0,8 à 1,8 V = 0,08 à 0,6 de préférence 0,12 à 0,4 Si = 0,05 à 0,5 de préférence 0,1 à 0,35 Mn = 0,05 à 2,0 de préférence 0,5 à 0,95 S = 0,002 à 0,39 de préférence 0,06 à 0,35 (Mn/S) = 2,0 en minimum de préférence 2,5 en minimum Ni = 2,4 en maximum de préférence 0,9 en maximum B = jusqu'à 0,01 Fe = le reste et des impuretés conditionnés par la fabrication.
  3. Aube de turbine pour des turbines à vapeur ou à gaz, ou aube de compresseur d'un acier martensitique doux ou martensitique à nickel, en pourcentage en poids, ayant une composition de C = 0,02 à 0,1 N = 0,001 à 0,098 (C+N) = 0,05 à 0,12 Si = 0,08 à 1,0 Mn = 0,1 à 2,0 Cr = jusqu'à 20,0 S = 0,003 à 0,49 (Mn/S) = 1,9 en minimum Mo = 0,6 à 3,0 V = jusqu'à 0,2 Ni = 3,0 à 8,0 Cu = 1,0 à 4,5 B = jusqu'à 0,01 Al = jusqu'à 0,08 Nb = jusqu'à 0,6 Fe = le reste et des impuretés conditionnés par la fabrication,
    formée par un matériau préliminaire produit par la métallurgie des poudres (PM), en pulvérisant une fonte par atomisation à gaz au moyen d'azote et par compression isostatique à température élevée (HIP) du poudre, ledit matériau étant usiné par enlèvement de copeaux, et l'aube de turbine ou de compresseur ainsi fabriquée est traitée de manière thermique ou trempée et revenue et, à une température ambiante, a les propriété suivantes de matériau : résistance à la traction : Rm = au moins 700 N/mm2 limite élastique : R0,2 = au moins 550 N/mm2 allongement : A = au moins 15% striction : Z = au moins 10%.
  4. Aube de turbine selon la revendication 3, formée d'un acier martensitique doux ou martensitique à nickel, en pourcentage en poids, ayant une composition de C = 0,02 à 0,08 de préférence 0,03 à 0,05 N = 0,001 à 0,05 de préférence 0,0015 à 0,039 Si = 0,08 à 0,5 de préférence 0,1 à 0,4 Mn = 0,1 à 1,9 de préférence 0,2 à 1,6 S = 0,003 à 0,39 de préférence 0,1 à 0,35 Cr = 9,0 à 20,0 de préférence 9,0 à 13,0 Mo = 0,6 à 2,0 de préférence 0,6 à 1,8 Ni = 3,0 à 7,9 de préférence 3,5 à 6,8 Cu = 1,0 à 4,4 Al = jusqu'à 0,04 Fe = le reste et des impuretés conditionnés par la fabrication.
  5. Aube de turbine selon une quelconque des revendications 1 à 4, où le matériau préliminaire est formé, après la compression isostatique à température élevée (HIPer) et après une déformation à chaud avec un dégrée de déformation d'au moins 2,5 fois, par un usinage par enlèvement de copeaux.
  6. Aube de turbine selon une quelconque des revendications 1 à 4, où le matériau préliminaire est usiné, après la compression isostatique à température élevée (HIPer), de préférence dans une moule proche à la mesure finale, sans déformation (comme HIPé), par enlèvement de copeaux.
EP01890337A 2000-12-15 2001-12-12 Aube de turbine Expired - Lifetime EP1215366B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SI200130995T SI1215366T1 (sl) 2000-12-15 2001-12-12 Turbinska lopatica

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
AT0209600A AT411028B (de) 2000-12-15 2000-12-15 Turbinenschaufel für dampf- oder gasturbinen sowie verdichter
AT209600 2000-12-15

Publications (3)

Publication Number Publication Date
EP1215366A2 EP1215366A2 (fr) 2002-06-19
EP1215366A3 EP1215366A3 (fr) 2004-10-13
EP1215366B1 true EP1215366B1 (fr) 2011-05-18

Family

ID=3689836

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01890337A Expired - Lifetime EP1215366B1 (fr) 2000-12-15 2001-12-12 Aube de turbine

Country Status (6)

Country Link
EP (1) EP1215366B1 (fr)
AT (2) AT411028B (fr)
DK (1) DK1215366T3 (fr)
ES (1) ES2363928T3 (fr)
PT (1) PT1215366E (fr)
SI (1) SI1215366T1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5368887B2 (ja) 2008-09-01 2013-12-18 ミネベア株式会社 マルテンサイト系ステンレス鋼および転がり軸受
DE102011003632A1 (de) * 2011-02-04 2012-08-09 Siemens Aktiengesellschaft Turboverdichterlaufrad und Verfahren zum Herstellen desselben
DE102020131031A1 (de) 2020-11-24 2022-05-25 Otto-Von-Guericke-Universität Magdeburg Martensitische Stahllegierung mit optimierter Härte und Korrosionsbeständigkeit

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB718382A (en) * 1950-11-25 1954-11-10 Sintercast Corp America Powder metallurgical method of shaping articles from high melting metals
DE1238676B (de) * 1962-05-31 1967-04-13 Gen Electric Verwendung einer Chromstahllegierung fuer Schmiedestuecke
NO131944C (fr) * 1970-12-28 1975-08-27 Kobe Steel Ltd
GB1582651A (en) * 1977-04-01 1981-01-14 Rolls Royce Products formed by powder metallurgy and a method therefore
WO1982000158A1 (fr) * 1980-07-08 1982-01-21 Salk Inst For Biological Studi Systeme d'amplification des genes eucaryotiques
JPS58217664A (ja) * 1982-06-11 1983-12-17 Toshiba Corp 蒸気タ−ビン動翼
US5584948A (en) * 1994-09-19 1996-12-17 General Electric Company Method for reducing thermally induced porosity in a polycrystalline nickel-base superalloy article
GB2315441B (en) * 1996-07-20 2000-07-12 Special Melted Products Limite Production of metal billets

Also Published As

Publication number Publication date
PT1215366E (pt) 2011-06-07
AT411028B (de) 2003-09-25
ATA20962000A (de) 2003-02-15
DK1215366T3 (da) 2011-09-12
ATE510107T1 (de) 2011-06-15
ES2363928T3 (es) 2011-08-19
EP1215366A2 (fr) 2002-06-19
EP1215366A3 (fr) 2004-10-13
SI1215366T1 (sl) 2011-08-31

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