• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    1519370 Coated nickel and cobalt alloys UNITED TECHNOLOGIES CORP 26 Aug 1976 [11 Sept 1975] 35521/76 Heading B2E A thermally protected Ni or Co superalloy, e.g. for use in combustion chambers, transition ducts and afterburner liners in gas turbine engines, has a metal bond coat which is an alloy of 15-40% G, 10-25% Al, up to 1% ythrium, the balance being a mixture of Fe, Co and Ni or a mixture of Ni and Co. The bond coat is overlaid with a zirconia base ceramic material. The concentration of ceramic may vary continuously from 0 at the bond coat to 100%. The coatings may be applied by plasma spraying.
    公开号:SU1505441A3
    申请号:SU762395497
    申请日:1976-09-09
    公开日:1989-08-30
    发明作者:Уильям Говард Джордж；Эндрюс Грей Дельтон；Кэррол Крутенат Ричард
    申请人:Юнайтед Текнолоджиз Корпорейшн (Фирма)；
    IPC主号:
    专利说明:

    This invention relates to a refractory industry, preferably to coatings to protect structures made of nickel-cobalt based alloys.
    The aim of the invention is to increase durability.
    Before applying a superalloy based on nickel and cobalt on the product, the surface is first thoroughly cleaned ot dirt, grease and other impurities, and then sandblasted with an abrasive material. The coating is applied by vapor deposition, which is formed from the melt deposited material heated to the appropriate temperature, in a vacuum chamber at 10 Torr or lower pressure. The initial signal, which is melted and evaporated by the electron beam, has approximately the same chemical composition as the final coating.
    Before starting the deposition, the products are preferably heated for 5-6 minutes to 95Aj: 28 ° C and this temperature is maintained further during the coating process. The duration of the deposition may vary, but is controlled so that the resulting coating has a thickness of 0.08-0.18 mm. After coating, cooling to below 538 ° C in a non-oxidizing atmosphere follows. After coating, the products can be subjected to additional heat treatment for 1 hour at 1037 + 14 ° C in vacuum to ensure a more durable connection of the coating with the material.
    o ate lu

    cm
    3150
    rial basics and facilitate subsequent shot blasting.
    Coated products may be shot-blasted with dry glass beads with a diameter of 0.18-0.28 or an intensity equivalent to 19 N. After this product may be subjected to heat treatment for 4 hours at 1080 + 14 ° C in an atmosphere of dry argon, hydrogen or in a vacuum and then cooled in a stictive atmosphere at a rate equivalent to that of natural cooling in air. The products treated in this way have a coating (excluding the diffusion zone) with a thickness of 0.08-0.18 mm.
    Example 1 For high temperature specimens from MAR-M 509 (containing, wt.%: Nickel 10; chromium 23.5; cobalt 55; tungsten 7; tantalum 3.5; titanium 0.2; carbon 0.6; zirconium 0.5) Coatings are applied from known and proposed compositions. In the first case, a binder coating was used, including BO% by weight of nickel, 20% by weight of chromium and 5% by weight of aluminum, in the second case a binding coating containing 25% by weight of chromium, 15% by weight of aluminum, 0.2% by weight % yttria and the rest nickel. In this and in another case, the thickness
    the coating was approximately 0.13 mm and was applied by vapor deposition. Magnesium-stabilized ZrO, j layers with a thickness of 0.26 mm were applied onto the substrate with a bonding coating using plasma spraying. Samples coated with a coating were subjected to cyclic tests at high temperature, during which they were heated for 5 minutes prior to installation in the plant by burning rocket fuel and then cooled for 1 minute by blowing air. The duration of one cycle was 6 minutes. For 1 h was carried out 10 cycles. In samples with a known coating, approximately 50% of the binder coating was peeled off after 2000 cycles (after 200 hours). In samples with a pre-stackable coating, less than 50% of the samples were destroyed after 6000 cycles (600 h). It should be noted that in the samples with a known coating, a noticeable oxidation of the coating material after peeling was observed after the peeling of the binder material. In some
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    0 5 0
    with Q
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    five
    Occasionally, oxidation of the exposed base material also occurred. In samples with the proposed coating oxidation was not observed; their bonding coating is significantly more resistant to oxidation.
    Example 2. A cobalt superalloy MAR-M 509 was applied to the turbine blades of the proposed and proposed coatings and tested in a serial gas turbine. In samples with a known coating, the binder coating contained, in wt.%: Ni 20; Cr 24; A1 15; With the rest. In the samples with the proposed coating, the binder coating had the same composition, but additionally contained 0.75 wt.% Yttrium. In both cases, the thickness of the binder coating was approximately 0.13 mm. Plasma spraying was used to deposit turbine blades of both types of zirconia stabilized with magnesium oxide stabilized to a thickness of about 0.38 mm. The coated blades were mounted into a serial turbine and subjected to standard tests under stringent conditions. Every 1000 cycles the turbine was partially disassembled to inspect the blades. In blades with a known coating, substantial destruction of the ceramic material was observed in less than 1000 cycles, whereas in blades with the proposed coating, significant destruction of the ceramic material occurred only after more than 2000 cycles.
    Example 3. The samples for high-temperature tests from MAR-M 200 + Hf (composition, wt.%: Cr 9; Co 10; W 12; C1 1; Ti2; A1 5; / B 0,015; Hf 7; Ni else) were applied coatings with known and proposed binding coatings. The known coating contained 20 wt.% Cr, 10 wt.% A1, the rest Co. The proposed coating had the same composition, but contained an additional 6% by weight of Y. Both coatings were applied by plasma spraying. A coating of zirconia stabilized with magnesium oxide (20% MgO; 80% ZrOj) was applied over the metal binder coating by plasma spraying. The thickness of the metal bonding coating was approximately
    0.13 MM, tol1dina ceramic coating, tee - about 0.25 mm. The samples thus coated were tested in a BbicjKo-temperature device in which they were heated for 5 t-ma to 982 ° and then cooled for 1 fin by blowing air, as a result of which thermal stresses occurred in them. The samples with the proposed coatings were kept for about 7000 cycles ( after which a significant peeling of the ceramic layer was observed). Samples with a known coating showed significant peeling already in about
    after 2000 cycles. I
    Example 4. Samples for
    high temperature tests from MAR-M 200 + H (of the same composition as in example 3) were coated with two different types of binder coating. The first coating (known contained 18 wt.% Cr; 13 wt.% A1, the rest of Co. The second coating (proposed) had the same composition as the first, but contained an additional 7 wt.% W. Both coatings were applied by plasma spray coating. A metallic zirconia coating stabilized with magnesium oxide (23% MgO; 77% ZrOj) was applied over the metal bonding coatings by plasma deposition. The thickness of the bonding adhesive coating was approximately 0.13 mm, and the ceramic coating thickness was 0.30 The samples thus coated were tested in a high temperature. Aturus device, where they were heated for 5 minutes to 1010 s, and then cooled for 1 minute by blowing air, as a result of which thermal stresses occurred. Samples with the proposed coating were kept for about 8000 cycles (after which significant exfoliation of the ceramic coating.) In samples with a known coating, substantial exfoliation was observed already after about 2500 cycles.
    Example 5. On the blades of a gas turbine, made of material MAR-M 200, put two types of coatings of the same composition as in example 2. The blades had internal air cooling. The blades supplied with thermocouples were mounted into a gas turbine together with wings made of MAR-M 200 coated with nickel, which
    g) about 15
    20 25 DL s to D5, „
    five
    ba: chrome, aluminum and yttria of the same composition as in example 2, I D without a ceramic coating. During accelerated tests, it was found that the average temperature with ceramic coating of life was about 83 ° C lower than the blades that did not contain a ceramic coating. Such a decrease in temperature contributes to an increase in the duration of the life of the legs. The blades with pok; tiem from nickel, cobalt, chromium;), alum} and yttrium without a ceramic coating revealed the following:; natural oxidation of the coating after 3000 kg. In the blades with a ceramic coating and a bonding coating of 1-: nickel, coba, chromium and aluminum on the surface, the KepaNni4ecKoro coating was significantly depleted after about 2000 cycles and lost its additive properties as a result of penetration through the coating after about 4000 complete cycles. The blades with ceramic pits: tpsm and bonding; they were practically uncovered after 10,000 cycles with a coating of nickel, 1 cob, zlta, chromium, aluminum and yttrium, after which the test was stopped. Thus, a decrease in temperature makes the ceraga coating more favorable for oxidation resistance, because the rate of
    oxidation is temperature dependent. I
    Example 6. A panel coated with 67.5 wt.% Cobalt, 20 wt.% Chromium, 12 wt.% Aluminum, 0.5 wt.% Yttrium, 17 wt.% Magnesium oxide stabilized zirconia, with a thickness of a coat 0.022 and 0.035 cm were subjected to aging at 980 ° C, after which two minutes were cooled at room temperature. During test 1PI after 100 cycles, a satisfactory adhesion of the coating to the alloy exposed to the substrate was found. Samples are coated for about 7,000 cycles.
    权利要求:
    Claims (1)
    [1]
    Invention Formula
    Coating to protect the iike.ch alloy and cobalt construction from high temperatures, consisting of a layer of a metal binder containing chromium, nickel or cobalt, and a layer of magnesium oxide stabilized with magnesium oxide, tl and ch by that.
    7 15054418
    with the aim of resistance, metal-Chrom20-25
    Lytic Binder Sedale Optional Aluminum 12-15
    contains aluminum and yttrium and has a Yttrium of 0.2-0.75
    composition, wt.%: Nickel and cobalt Else
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    同族专利:
    公开号 | 公开日
    FR2323656B1|1983-01-14|
    DE2640829A1|1977-03-17|
    CH609731A5|1979-03-15|
    IL50375D0|1976-10-31|
    PL120368B1|1982-02-27|
    YU42647B|1988-10-31|
    BE845193A|1976-12-01|
    JPS5233842A|1977-03-15|
    CA1068178A|1979-12-18|
    YU220076A|1982-08-31|
    DE2640829C2|1986-07-31|
    NO148114C|1983-08-10|
    SE440238B|1985-07-22|
    IN145818B|1978-12-30|
    AU1693276A|1978-02-23|
    DK370176A|1977-03-12|
    BR7605892A|1977-08-16|
    DK151901B|1988-01-11|
    SE7609304L|1977-03-12|
    NO763047L|1977-03-14|
    AU504802B2|1979-11-01|
    JPS5917189B2|1984-04-19|
    IL50375A|1979-05-31|
    GB1519370A|1978-07-26|
    DK151901C|1988-06-06|
    FR2323656A1|1977-04-08|
    IT1064979B|1985-02-25|
    NO148114B|1983-05-02|
    引用文献:
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    US3091548A|1959-12-15|1963-05-28|Union Carbide Corp|High temperature coatings|
    GB1214743A|1968-01-24|1970-12-02|Imp Metal Ind Kynoch Ltd|Improvements in or relating to oxidation-resistant coatings|
    US3754903A|1970-09-15|1973-08-28|United Aircraft Corp|High temperature oxidation resistant coating alloy|
    US3676085A|1971-02-18|1972-07-11|United Aircraft Corp|Cobalt base coating for the superalloys|
    US3758233A|1972-01-17|1973-09-11|Gen Motors Corp|Vibration damping coatings|
    US3837894A|1972-05-22|1974-09-24|Union Carbide Corp|Process for producing a corrosion resistant duplex coating|GB2100621B|1981-06-30|1984-07-18|United Technologies Corp|Strain tolerant thermal barrier coatings|
    GB2101910B|1981-07-14|1984-09-19|Westinghouse Electric Corp|Improvements in or relating to thermally protected alloys|
    JPH0311367B2|1984-01-13|1991-02-15|Hitachi Ltd|
    DE3446479A1|1984-12-20|1986-07-03|BBC Aktiengesellschaft Brown, Boveri & Cie., Baden, Aargau|METAL FASTENER|
    IL84067A|1986-10-30|1992-03-29|United Technologies Corp|Thermal barrier coating system|
    US5098797B1|1990-04-30|1997-07-01|Gen Electric|Steel articles having protective duplex coatings and method of production|
    US5105625A|1990-11-23|1992-04-21|General Motors Corporation|Mounting for a ceramic scroll in a gas turbine machine|
    US5180285A|1991-01-07|1993-01-19|Westinghouse Electric Corp.|Corrosion resistant magnesium titanate coatings for gas turbines|
    CA2091472A1|1992-04-17|1993-10-18|William R. Young|Whisker-anchored thermal barrier coating|
    AU1875595A|1994-02-16|1995-09-04|Sohl, Charles E.|Coating scheme to contain molten material during gas turbine engine fires|
    GB9617267D0|1996-08-16|1996-09-25|Rolls Royce Plc|A metallic article having a thermal barrier coating and a method of application thereof|
    JP4520626B2|2000-11-27|2010-08-11|池袋琺瑯工業株式会社|Glass lining construction method|
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    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    US61243975A| true| 1975-09-11|1975-09-11|
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