EP2058415A1 - Geschmiedete austenitische Edelstahllegierungskomponenten und Verfahren dafür - Google Patents

Geschmiedete austenitische Edelstahllegierungskomponenten und Verfahren dafür Download PDF

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Publication number
EP2058415A1
EP2058415A1 EP08167894A EP08167894A EP2058415A1 EP 2058415 A1 EP2058415 A1 EP 2058415A1 EP 08167894 A EP08167894 A EP 08167894A EP 08167894 A EP08167894 A EP 08167894A EP 2058415 A1 EP2058415 A1 EP 2058415A1
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EP
European Patent Office
Prior art keywords
alloy
component
niobium
forged component
stainless steel
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.)
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Application number
EP08167894A
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English (en)
French (fr)
Inventor
George Albert Goller
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General Electric Co
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General Electric Co
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Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP2058415A1 publication Critical patent/EP2058415A1/de
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    • 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
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D6/00—Heat treatment of ferrous alloys
    • C21D6/004—Heat treatment of ferrous alloys containing Cr and Ni
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D6/00—Heat treatment of ferrous alloys
    • C21D6/005—Heat treatment of ferrous alloys containing Mn
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D7/00—Modifying the physical properties of iron or steel by deformation
    • C21D7/13—Modifying the physical properties of iron or steel by deformation by hot working
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
    • C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below
    • 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
    • C22C38/58—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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
    • C21D1/26—Methods of annealing
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D2211/00—Microstructure comprising significant phases
    • C21D2211/001—Austenite
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D2211/00—Microstructure comprising significant phases
    • C21D2211/004—Dispersions; Precipitations
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/25—Manufacture essentially without removing material by forging
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/171—Steel alloys

Definitions

  • the present invention generally relates to stainless steel alloys and their processing. More particularly, this invention relates to a forgeable austenitic stainless steel alloy and forgings formed therefrom that have desirable mechanical and environmental properties and very stable microstructures over long periods of time at operating temperatures seen by internal components of gas turbine engines.
  • Iron-nickel-chromium (Fe-Ni-Cr) austenitic stainless steel alloys have been developed that exhibit good strength, ductility, and oxidation and creep resistance at elevated operating temperatures, including those within the turbine section of a turbomachine.
  • austenitic stainless steel alloys are often formulated to contain carbide and nitride-forming elements such as niobium (columbium) and vanadium. Examples of such alloys include those disclosed in U.S. Patent Nos. 4,853,185 and 4,981,647 to Rothman et al . Controlled amounts of nitrogen, niobium, and carbon are typically specified in defined relationships to ensure the presence of "free" nitrogen and carbon. For example, niobium is often specified in an amount relative to the carbon content of the alloy.
  • Austenitic stainless steel alloys such as type 304, 347, 316, 321, etc., have stable austenitic microstructures at room temperature, but can suffer from loss of properties during extended exposures to high temperatures as a result of being prone to detrimental secondary phases formation, such as sigma phase.
  • the gas turbine industry has often used stainless steel alloys with high levels of austenite stabilizers, namely nickel, to eliminate the formation of these secondary phases.
  • Wrought stainless steel type 310 (nickel content of 19.0 - 22.0 weight percent) is a notable example of a stable austenitic stainless steel that is also forgeable, and therefore has been used to produce forged shroud components of gas turbine engines.
  • the present invention provides a forgeable austenitic stainless steel alloy and forging process capable of producing forged components that exhibit mechanical and environmental properties and metallurgical stability suitable for use in thermally and chemically hostile environments, such as those in gas turbine engines.
  • a forged component is produced from a forgeable austenitic stainless steel alloy containing, by weight, 18.0 to 22.0% chromium, 8.0 to 14.0% nickel, 4.0 to 7.0% manganese, 0.4 to 0.6% silicon, at least 0.2 up to 1.0% nitrogen, at least 0.05 up to 0.075% carbon; up to 0.3% molybdenum, up to 1.0% niobium, up to 0.2% cobalt, up to 4.5% aluminum, up to 0.1% boron, up to 0.1% vanadium, up to 1.0% tungsten, up to 5.0% copper, the balance iron and incidental impurities.
  • a forged component is produced from this alloy by preparing a melt of the alloy, forming a billet of the alloy, forging the alloy to form the component, solution heat treating the forged component, and then quenching the forged component and machining the forged component to produce the component, such as a component of a turbine shroud assembly.
  • a significant advantage of this invention is the ability of the austenitic stainless steel alloy to be forged to produce components that have desirable mechanical properties and very stable, fully austenitic microstructures that avoid deleterious second phase formation during long exposures at high temperatures.
  • Such mechanical and metallurgical properties are preferably comparable to and possibly better than wrought stainless steel type 310, while significantly reducing the level of nickel required in comparison to type 310 (19.0 - 22.0%).
  • the forgeable austenitic stainless steel alloy can exhibit fatigue and oxidation resistance capable of withstanding the internal conditions of a gas turbine engine, such as components of a shroud assembly surrounding the turbine blades of the engine.
  • the forgeable stainless steel alloy of the present invention is similar to the cast austenitic stainless steel alloy CF-8C, having a composition of, by weight, 0.08% maximum carbon, 2.00% maximum silicon, 1.50% maximum manganese, 18.0-21.0% chromium, 9.0-12.0% nickel, and 8x%C to 1.0% niobium, with the balance iron.
  • CF-8C is nominally identified with the wrought austenitic stainless steel alloy type 347, having a composition, by weight, of 0.08% maximum carbon, 1.00% maximum silicon, 2.00% maximum manganese, 17.0-19.0% chromium, 9.0-13.0% nickel, 10x%C minimum niobium, 0.03% maximum sulfur, and 0.045% maximum phosphorus, with the balance iron.
  • the forgeable stainless steel alloy of the present invention is similar to a cast austenitic stainless steel alloy disclosed in U.S. Patent No.
  • a critical different between the present invention and this prior art is the requirement of the invention for forgeability and long term phase stability, which demands mechanical and physical properties including ductility and metallurgical microstructures that are unnecessary for alloys used in the cast foundry condition, such as CF-8C and Maziasz et al., as well as many wrought alloys such as type 347.
  • the composition of the present alloy must be more narrowly tailored to achieve properties specific to forgeability than is necessary for similar alloys intended for use in cast or wrought form only.
  • FIG. 1 represents a fragmentary view of a longitudinal cross section through a turbine section of a gas turbine engine, and shows components of a shroud assembly 10 within the turbine section.
  • the shroud assembly 10 circumscribes the turbine rotor (not shown) of the gas turbine engine, such that a turbine blade 12 is shown in proximity to the shroud assembly 10.
  • the blade 12 is one of multiple blades mounted on the rotor, which rotates coaxially within the stationary shroud assembly 10.
  • the shroud assembly 10 comprises a shroud 14 and a hanger 16 by which the shroud 14 is supported.
  • the radially inward face of the shroud 14 faces the blade tips of the turbine rotor and minimizes the gas leakage path between the shroud assembly 10 and the rotor blade tips.
  • the shroud 14 and its hanger 16 are preferably fabricated as multiple individual sections, with shroud sections circumferentially adjoining each other to define a substantially continuous annular shape that surrounds the blade tips, and with hanger sections circumferentially adjoining each other to define a substantially continuous annular shape that surrounds and supports the shroud 14.
  • the hanger 16 is supported using hooks and retention clips from an annular outer casing 18 of the engine.
  • the shroud assembly 10 represented in Figure 1 is merely intended to assist with an understanding of the invention, and the invention is not limited to any particular configuration, shape, fastening technique, etc., depicted in Figure 1 .
  • the shroud 14, and more specifically each section of the shroud 14 is formed of a forgeable austenitic stainless steel alloy that exhibits high temperature strength and ductility, good low cycle fatigue properties, and good oxidation properties at operating temperatures sustained by the shroud 14.
  • the alloy also exhibits sufficient metallurgical stability to ensure that the performance of the shroud 14 is maintained at temperatures exceeding 700°C for extended periods of time, for example, in excess of 50,000 engine operating hours. Ranges for the alloy are set forth in Table I below.
  • Nominal Cr 18.0 to 22.0 19.0 to 21.0 20 Ni 8.0 to 14.0 8.0 to 10.0 9 Mn 4.0 to 7.0 4.0 to 6.0 4.5 Si 0.4 to 0.6 0.4 to 0.6 0.5 N 0.2 to 1.0 0.2 to 0.6 0.25 C 0.05 to 0.075 0.05 to 0.075 0.07 Nb 1.0 Max 0.5 to 1.0 0.7 Mo 0.3 Max 0.3 Max 0.2 Max Co 0.2 Max 0.2 Max 0.2 Max Al 4.5 Max 4.5 Max 4.5 Max 4.5 Max B 0.1 Max 0.1 Max 0.03 W 1.0 Max 0.5 Max 0.5 Max Cu 5.0 Max 5.0 Max 5.0 Max V 0.1 Max 0.1 Max Impurity S 0.03 Max Impurity Impurity P 0.045 Max Impurity Impurity Fe Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance Balance
  • compositional ranges differ significantly from other forgeable alloys currently used for shrouds of the type represented in Figure 1 , such as the type 310 stainless steel having a composition of, by weight, 0.25% maximum carbon, 1.50% maximum silicon, 2.00% maximum manganese, 24.0 to 26.0% chromium, 19.0 to 22.0% nickel, 0.03 % maximum sulfur, 0.045% maximum phosphorus, the balance iron.
  • the alloy of this invention must be sufficiently ductile and tough to permit the shroud 14 to be fabricated from the alloy by a suitable forging operation. As such, the alloy must have properties unneeded and unspecified for cast austenitic stainless steel alloys such as CF-8C.
  • the broadest chromium and nickel levels were patterned after the type 347 austenitic stainless steel (17.0-19.0 and 9.0-13.0 weight percent, respectively), though with higher and lower ranges, respectively, to achieve the desired stable microstructure for the forging alloy.
  • the specified minimum and maximum amounts for carbon are intended to control the formation of stable niobium carbides and prevent the formation of M23C6 carbides, resulting in increased microstructural stability when exposed to high temperatures for long durations.
  • the specified minimum and maximum amounts for silicon are intended to improve the castability of the alloy, enabling the casting of a billet from which a near-net-shape component can be forged.
  • manganese and nitrogen are tied together, as these elements cooperate to stabilize the austenitic phase in the alloy.
  • Manganese increases the solubility of nitrogen in austenite, which is beneficial for promoting the austenite stabilizing effect without decreasing the ductility or toughness of the alloy, especially at preferred nitrogen levels of up to 0.6 weight percent, more preferably up to 0.4 weight percent.
  • Manganese also stabilizes austenite, thereby preventing the formation of delta ( ⁇ ) ferrite (bcc crystal form of iron) in the microstructure, increases the solubility of carbon, thereby desirably reducing grain boundary carbide formation in the alloy.
  • manganese levels below 4% may result in a not fully austenitic structure, while manganese levels above 7% may adversely affect forgeability.
  • manganese and nitrogen are able to effectively stabilize the austenitic phase to the extent that deleterious secondary phases are avoided that otherwise form in other low-nickel forgeable austenitic stainless steels, such as type 347. Because the cost of manganese and nitrogen are considerably less than nickel, the material cost of the alloy is less than type 310.
  • niobium is preferably present in the alloy in an amount to yield a niobium:carbon ratio of at least 10:1 by weight to ensure the presence of niobium carbides.
  • Iron preferably constitutes the balance of the alloy. Aside from iron, the alloy is preferably limited to incidental impurities, such as phosphorus and sulfur, preferably at the lowest amounts possible. The total impurity content of the alloys is preferably less than 0.075 weight percent.
  • the alloy undergoes processing that includes preparing a melt of the alloy according to appropriate and known melting and deoxidation practices. An ingot/billet is then cast from the melt, followed by forging the ingot/billet to form a near-net-shape forged component, again according to known practices.
  • the component After forging, the component preferably undergoes a solution heat treatment, such as at a temperature of about 1070 to about 1200°C for a duration of about one hour per inch of forging thickness (four hours minimum), followed by a quench that is sufficiently rapid so that the resulting microstructure has a fully austenitic grain structure with well distributed carbides (including niobium carbides), does not contain M23C6 carbides or other deleterious phases, does not contain delta ferrite, and is free of segregation.
  • the mechanical properties of the heat treated and quenched forging are equal to or better than conventional 300 series stainless steels, and are capable of remaining so for extended periods of turbine operating time at temperatures exceeding 700°C. Following quenching, the forging is machined to produce the final dimensions required of the component.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Materials Engineering (AREA)
  • Organic Chemistry (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Forging (AREA)
  • Heat Treatment Of Steel (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08167894A 2007-11-09 2008-10-30 Geschmiedete austenitische Edelstahllegierungskomponenten und Verfahren dafür Withdrawn EP2058415A1 (de)

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Application Number Priority Date Filing Date Title
US11/937,591 US20090129967A1 (en) 2007-11-09 2007-11-09 Forged austenitic stainless steel alloy components and method therefor

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EP2058415A1 true EP2058415A1 (de) 2009-05-13

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US (1) US20090129967A1 (de)
EP (1) EP2058415A1 (de)
JP (1) JP2009120950A (de)
KR (1) KR20090048331A (de)

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EP2460904A3 (de) * 2010-12-03 2012-11-28 Bayerische Motoren Werke AG Austenitischer Stahl für die Wasserstofftechnik
EP2947171A1 (de) * 2014-05-20 2015-11-25 CRS Holdings, Inc. Legierung aus austenitischem edelstahl
EP3054108A1 (de) * 2015-02-06 2016-08-10 United Technologies Corporation Gehäusestrukturen für einen gasturbinenmotor
CN113388790A (zh) * 2021-06-08 2021-09-14 常州腾飞特材科技有限公司 一种06Cr19Ni10N奥氏体不锈钢管及其生产工艺

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US8484978B2 (en) * 2009-11-12 2013-07-16 General Electric Company Fuel nozzle assembly that exhibits a frequency different from a natural operating frequency of a gas turbine engine and method of assembling the same
US10145306B2 (en) * 2013-01-16 2018-12-04 United Technologies Corporation Heat shield for gas turbine engine gearbox
FR3003271B1 (fr) * 2013-03-13 2015-04-17 Areva Np Acier inoxydable pour forgeage a chaud et procede de forgeage a chaud utilisant cet acier
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
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
KR101614622B1 (ko) 2014-12-26 2016-04-22 주식회사 포스코 연료전지용 오스테나이트계 스테인리스강
KR102626122B1 (ko) 2015-12-14 2024-01-16 스와겔로크 컴패니 용체화 어닐링 없이 제조된 고합금 스테인리스강 단조품
US20180340438A1 (en) * 2017-05-01 2018-11-29 General Electric Company Turbine Nozzle-To-Shroud Interface
BR102018068426A2 (pt) * 2018-09-12 2020-03-24 Mahle Metal Leve S.A. Válvula de alívio para um turbocompressor e processo para fabricação de válvula de alívio
DE102018133255A1 (de) * 2018-12-20 2020-06-25 Voestalpine Böhler Edelstahl Gmbh & Co Kg Superaustenitischer Werkstoff

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EP0446188A1 (de) * 1990-02-26 1991-09-11 Sandvik Aktiebolag Rostfreier Stahl
WO1996014447A1 (en) * 1994-11-02 1996-05-17 Sandvik Ab Use of a nonmagnetic stainless steel
EP1219720A2 (de) * 2000-12-14 2002-07-03 Caterpillar Inc. Hitzebeständiger, Korrosionsfester und rostfreier Gussstahl mit guter Warmfestigkeit und Ducktilität
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