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TW201024430A - Ultra-high strength stainless alloy strip, a method of making same, and a method of using same for making a golf club head - Google Patents

Ultra-high strength stainless alloy strip, a method of making same, and a method of using same for making a golf club head Download PDF

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TW201024430A
TW201024430A TW098137054A TW98137054A TW201024430A TW 201024430 A TW201024430 A TW 201024430A TW 098137054 A TW098137054 A TW 098137054A TW 98137054 A TW98137054 A TW 98137054A TW 201024430 A TW201024430 A TW 201024430A
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ingot
strip
golf club
club head
temperature
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TW098137054A
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Chinese (zh)
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TWI417402B (en
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Theodore Kosa
David E Wert
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Crs Holdings Inc
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    • 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
    • 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
    • C21D6/001—Heat treatment of ferrous alloys containing 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
    • C21D6/02—Hardening by precipitation
    • 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
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C21D8/02—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips
    • C21D8/021—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips involving a particular fabrication or treatment of ingot or slab
    • 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
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C21D8/02—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips
    • C21D8/0221—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips characterised by the working steps
    • C21D8/0226—Hot rolling
    • 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
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C21D8/02—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips
    • C21D8/0221—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips characterised by the working steps
    • C21D8/0236—Cold rolling
    • 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
    • C22C38/04—Ferrous alloys, e.g. steel alloys containing manganese
    • 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
    • C22C38/06—Ferrous alloys, e.g. steel alloys containing aluminium
    • 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
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/44—Ferrous alloys, e.g. steel alloys containing chromium with nickel with molybdenum or tungsten
    • 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
    • C22C38/50—Ferrous alloys, e.g. steel alloys containing chromium with nickel with titanium or zirconium
    • 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
    • C22C38/54—Ferrous alloys, e.g. steel alloys containing chromium with nickel with boron
    • 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
    • C21D2211/008—Martensite

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Golf Clubs (AREA)
  • Heat Treatment Of Articles (AREA)
  • Heat Treatment Of Sheet Steel (AREA)

Abstract

A stainless steel strip article is disclosed. The article is formed from a corrosion resistant alloy having the following composition in weight percent, about: C 0.03 max. Mn 1.0 max. Si 0.75 max. P 0.040 max. S 0.020 max. Cr 10.9-11.1 Ni 10.9-11.1 Mo 0.9-1.1 Ti 1.5-1.6 Al 0.25 max. Nb 0.7-0.8 Cu 1 max. B 0.010 max. N 0.030 max. The balance is iron and usual impurities. The elongated thin strip article provides a room temperature tensile strength of at least about 280 ksi (1930.5 MPa) in the solution treated and age hardened condition. A method of making the strip article and a method of using it to make a golf club are also disclosed.

Description

201024430 六、發明說明： 【發明所屬之技術領域】 本發明係關於不鏽鋼條材料及特定言之係關於一種具有 極高抗拉強度之不鏽鋼條物件，一種製造該不鏽鋼條物件 之方法，及一種使用該條材料製造高爾夫球杆頭之方法。 【先前技術】 高爾夫球杆製造商不斷尋找一種高強度面板材料。極高 強度可製造更薄的面板截面，及因此更輕，其提供設計者 在球杆頭設計中之更多靈活性。此外，耐腐蝕材料較非-不鏽鋼材料佳，此係因為其不需要在使用期間可去除之表 面塗層或鍍覆之故。 該問題之目前解決方案包括使用諸如CUSTOM 455合 金之標準PH不鏽合金及諸如CUSTOM 465及CUSTOM 475 合金之最近設計的不鏽合金。然而，CUSTOM 455及 CUSTOM 405合金無法提供在新高爾夫設計中所需之強度 等級。CUSTOM 475合金提供極高強度，但其亦為高度合 金，使其既對球杆製造商而言為昂貴且亦為高爾夫球杆製 造方法所較不能容忍。 此外，很多球杆頭通常係使用具有一面板之一鑄件體來 製造。鑄件體材料通常係由諸如17-4 PH或15-5 PH不鏽鋼 之沉澱可硬化不鏽鋼形成。高爾夫球杆通常係藉由將該面 板焊接至該鑄件體然後加熱處理整個組裝以得到最終性質 來製造。用於球杆之鑄件體的合金通常具有約1900°F (103 8°C )之溶液溫度，然而習知面板材料具有1550°F至 144341.doc 201024430 18〇〇T(843°c至98rc)範圍之溶液溫度。在熱處理溫度中 之不相配導致球杆體或者面板材料或兩者在組裝球杆頭之 後提供不及於即經熱處理條件中之最優性質。此外， CUSTOM 475合金經常同時需要不同的製造方法，此係因 為合金不能在球杆頭組裝後再溶解之故。 【發明内容】 克服習知材料之缺點相當大程度係藉由根據本發明之不 鏽鋼條物件達成。根據本發明之一態樣，提供由耐腐蝕合 ® I形成之不鏽鋼條物件，該財腐姓合金包括以下各者，以 重量百分數計約： C 最多0.03 Μη 最多10 Si 最多0·75 P 最多〇·〇40 S 最多〇·〇20 Cr 10.9-11.1 Ni 10.9-11·1 Mo 0.9-1.1 Ti 1.5-1.6 A1 最多0·25 Nb 0.7-0.8 Cu 最多1 B 最多0 · 010 N 最多0·030 144341.doc 201024430 及其餘為鐵及常見雜f。經拉長之薄條提供在所處理之溶 液中及老化硬化條件下至少約28〇 ksi(i93()5胸)之室溫 抗拉強度。 根據本發明之另一態樣，提供一種製造薄條物件之方 法該方法包括鑄造具有以上提出之重量百分數之組成的 j腐蝕&金以形成一鑄錠之步驟。將該鑄錠熱加工以形成 、盈拉長之條材_。然冑使該條材料在肖間與溫度之條件下 進行熱處理以提供在室溫下至少約28〇 ksi(i93〇 5 Mb)之 最終抗拉強度。 根據本發明之又一態樣，提供一種製造高爾夫球杆頭之 方法'亥方法包括鑄造具有以上所提之重量百分數之組成 的耐腐蝕合金以形成一鑄錠。將該鑄錠熱加工以形成一經 拉長之條物件，然後使該條物件在時間與溫度之條件下熱 處理以助於該條材料之可機械加工性及可加工性。然後使 該條材料進行機器加工以形成一用於高爾夫球杆頭之面 板。該方法包括由耐腐蝕沉澱可硬化鋼合金形成一高爾夫 球杆頭體之進一步步驟。將該面板焊接於高爾夫球杆頭 體。接著在時間與溫度之條件下使組裝進行熱處理足以對 高爾夫球杆頭體提供所需等級之硬度及強度及對面板提供 於室溫下至少約280 ksi( 1930.5 MPa)之最終抗拉強度。 【實施方式】 本發明之一較佳實施例包括一具有以下以重量百分數計 之組成的經拉長之條物件： C 最多0.03 144341.doc 201024430 Μη 最多1.0 Si 最多0.75 P 最多0.040 S 最多0.020 Cr 10·9-11.! Ni 10·9-11.ι Mo 0-9-1.! Ti 1.5-1.6 A1 最多0.25 Nb 07-0.8 Cu 最多1 B 最多0.010 N 最多0.030 其餘為鐵及常見雜質。 使用真空感應熔煉（VIM)將合金紐合物較佳地熔融。將 $鏽鋼铸造成-或多個鑄㈣具。就額外的清潔性而言， 罾㈣Μ步驟後對合金進行真空電弧再熔煉。固化後，藉由 中間壓製錄旋以形成小胚然後熱輕壓該小胚以形成經拉長 t條而使合金形成條。或者，該條材料可藉由自約19〇〇卞 至2250 F(103 8C至1232。〇之起始溫度熱輥壓鑄錠而形 成。該條可提供於藉由於約11〇〇卞至135〇卞（593它至 732 C )下加熱約2至8小時然後在空氣中冷卻之過度老化條 件或者，對較佳可機械加工性及可加工性而言，在約 1900 F至1950卞（1038。(：至1065。〇下加熱條材料約i小時， 144341.doc 201024430 在空氣中冷卻，在約_10(^(_73 3。〇下冷凍約8小時，且 然後將其於空氣中升溫至室a。較錢，在進行熱處理之 前將條材料冷輥壓至最終或接近最終厚度。根據:發明之 條材料可在連續熔爐内，隨著時間及溫度之相應調節而進 行溶液處理。 不像諸如CUSTOM 475不鏽鋼合金之已知高強度不鑛鋼 合金’根據本發明之合金條可在不明顯喪失性質，尤其不 喪失強度下經兩次溶液處理。換言之，本發明之不鏽鋼條 材料可提供於經處理之溶液及在冷凍條件，處理成組份， 然後再溶解，再冷凍，並在組裝成高爾夫球杆頭以後老化 硬化以提供所需高強度及硬度。 作為一根據本發明之經拉長之條物件之實例，係熔融及 處理較小杆頭。藉由VIM+VAR熔融400 11)(181.41^)杆頭， 然後鑄造為8英对（2〇·3 cm)直徑之铸錠。vaR铸錠之重量 百分數組成見於表1。合金其餘成分為鐵及常見雜質。 表1 C Μη Si P S Cr Ni Mo Ή Cb B N ~~i Ce 0.005 0.05 0.04 <0.005 <0.0005 11.05 11.02 1.01 1.56 0.79 0.0019 0.0016 0.001 在約2300°F(1260°C)下使鑄錠均質化16個小時，然後自 約2〇00°F (1093°C )之起始溫度將其壓製成4-inx8-in(10 cmx20.3 cm)小胚。自約2250°F(1232°C)之起始溫度將該小 胚熱報壓成7.5 in.寬χ0·15 in.厚（19 cm寬x3.8 mm厚）條。 然後將該條研磨成0.135 in.(3.4 mm)厚，接著冷輥壓成 0.1103 in.(2.8 mm)厚。使該條藉由在約1146°F(619°C )下加 144341.doc 201024430 …5.5 j _而進行過度老化處理。冷卻i室溫&，將該條 材料研磨成0.1083 in.(2.75 mm)之最終厚度。 標準條抗拉空白组係自該經過度老化之條以縱向及橫向 方向粗切削。空白組為分別在185〇卞（1〇1〇。〇、19〇〇卞 (1038°C)、1950°F(1065°C)、及2000卞（1093。〇下進行溶液 處理1小時然後空氣冷卻。將經溶液處理之空白組在_ 100°F(-73.3°C )下進一步急冷8小時，且然後使其在空氣令 回升至室溫。接著粗機器加工該等空白組以提供約1/2英 吋寬χ2英吋長（1.27 cm寬χ5.08 cm長）之測量截面。使自每 一溶液處理之粗機器加工空白組在約900卞（482。(：）至約 975°F(524°C)之範圍下老化4小時，然後空氣冷卻。在老化 後完成測試樣品之機器加工，然後在室溫下進行測試。 室溫抗拉及硬度測試之結果呈現於下表2-4中，包括以 °F(°C )計之溶液處理溫度（溶液溫度）及老化溫度（老化溫 度），以ksi(MPa)計之0.2%補償降伏強度（Y.S.)及極限抗拉 強度（U.T.S.)，及以HRC計之洛氏（Rockwell)C級硬度（硬 度）。 144341.doc 201024430 表2 溶液溫度 老化溫度 方向 轉· 硬度 (HRC) 1850T (1010°〇 950〇F(510〇C) L 258(1779) 266(1834) .... 52.0 258(1779) 267(1841) ____ 258(1779) 268(1848) .... T 260 (1792) 272(1875) —— 260 (1792) 273(1882) —— 245 (1689) 272(1875) —— 975T (524°〇 L 244 (1682) 252 (1737) — 50.5 244 (1682) 253 (1744) — 245 (1689) 253 (1744) — T 248 (1710) 258 (1779) —— 246 (1696) 256 (1765) —— 245 (1689) 255 (1758) —— 144341.doc 10- 201024430 表3 溶液溫度 老化溫度 方向 Y.S. U.T.S. El.% 硬度 (HRC) 260(1792) 284(1958) 4.8 L 261(1799) 286(1972) 4.3 259(1785) 284(19058) 4.8 900〇F(482〇C ) 264 (1820) 287(1979) 4.3 53.5 T 257 (1772) 282(1944) 2.8 258 (1779) 285(1965) 4.2 259 (1785) 282(1944) 4.0 L 257 (1772) 281(1937) 4.2 925°F 256 (1765) 281(1937) 4.1 53.5 (496°C) 247 (1703) 285 (1965) 3.9 T 260 (1792) 285 (1965) 4.1 1900T 257 (1772) 285 (1965) 4.2 (1038°〇 250(1723) 274(1889) 6.2 L 252(1737) 273(1882) 6.7 249(1716) 273(1882) 6.4 950〇F(510〇C ) 251 (1730) 277(1910) 6.5 52.0 T 250 (1723) 277(1910) 6.0 251 (1730) 276(1903) 6.7 234 (1613) 258(1779) 7.3 L 235 (1620) 256(1765) 7.1 975〇F 235 (1620) 259(1785) 6.9 50.5 (524〇C) 243 (1675) 264 (1820) 6.8 T 240 (1654) 261 (1799) 6.6 242 (1668) 263 (1813) 6.6 144341.doc -11 - 201024430 表4 溶液溫度 老化溫度 方向 Y.S. U.T.S. EI.% 硬度 (HRC) * * 4.6 L 氺 4.1 900Τ(482°〇 氺 氺 4.7 53.5 * * 5.4 T * 氺 4.2 本 氺 4.8 1950T (1065°〇 * 氺 5.3 L * 氺 5.2 950T (510°〇 * 氺 4.3 264 (1820) 275 (1896) 5.3 52.5 Τ 267 (1841) 179 (1923) 4.9 260 (1792) 276 (1903) 5.3 248(1710) 282(1944) 5.9 L 253(1744) 283(1951) 5.0 255(1758) 282(1944) 5.5 900°F(482〇C) 261 (1799) 286(1972) 4.6 53.5 Τ 258 (1779) 291(2006) 5.1 260 (1792) 287(1979) 4.7 2000T (1093°〇 253 (1744) 276(1903) 5.7 L 254 (1751) 277(1910) 5.2 950〇F 255 (1758) 276 (1903) 5.2 53.0 (510°C) 260 (1792) 281 (1937) 4.7 Τ 261 (1799) 282 (1944) 4.6 263 (1813) 282 (1944) 5.0 *針對該等樣品，強度資料遺失。然而，測試操作者回想 出對於H900樣品U.T.S.為高於280 ksi(1930.5 MPa)，及對 於H950樣品 U.T.S.稍微低於 280 ksi(193 0.5 MPa)。 144341.doc -12- 201024430 /則試樣时之金相學分析顯示在卞（丨)及 測。Fuom：)下處理之材料溶液具有約astm8之粒度。 在1950 F(1G65 C )下處理之材料溶液具有約astm 7 8之粒 度。在漏v(1G9rc)下處理之㈣溶液具有 約 ASTM 2-3 之粒度。此處及整個由姓·安 rf» 個甲研案中，ASTM粒度意指如根據 ， ASTM標準測試方法E-112測定之平均粒度。 在表2 3及4中呈示之結果顯示較佳溶液溫度約19⑼。ρ (1038°c)至約195昨（贿。〇。同樣地，為使材料提供所 • 冑280 ksi(1930.5 MPa)U.T.S·，較佳老化溫度為約9崎至 925T(482°C至496。〇。在圖中_UTS對溶液及老化溫 度組合之圖表。 在表中呈示之數據顯示由在本中請案中描述之合金組合 物製得之條物件可達到280 ksi (193〇 5 Mpa)或更高之 U.T.S.。該條材料較其他可達到彼強度等級之不鏽鋼組合 物之重金屬合金甚少’導致較低合金成本。另外，該條材 #在不犧牲強度或餘度性質下可受到多於_次之溶液加熱 處理。本發明之該條材料較佳在約1900 1950卞（1们8_ l〇65°C)範圍之溫度下進行溶液加熱處理，使此組合物之 高爾夫球杆面板與最常料高爾夫球杆頭體之騎可硬化 不鏽鋼鑄造合金之溶液處理溫度完全一致。因此，可以組 裝組態進行溶液處理並老化硬化面板及高爾夫球杆頭以 使不僅球杆頭體，而且使與高爾夫球接觸之面板得到最大 硬度及強度。 熟習此項技術者將可理解在不脫離本發明之寬廣創作概 144341.doc 201024430 念下’可對以上所述之實施例進行變化及改變。因此，應 瞭解本發明不限於所描述之特定實施例，但希望涵蓋在如 上所述之本發明之範圍與精神内及在隨附申請專利範圍中 提出之所有改變與變化。 【圖式簡單說明】 圖1係以老化溫度作為函數之抗拉強度之圖表。201024430 VI. Description of the Invention: [Technical Field of the Invention] The present invention relates to a stainless steel strip material and, in particular, to a stainless steel strip article having extremely high tensile strength, a method of manufacturing the stainless steel strip article, and a use thereof This method of making a golf club head. [Prior Art] Golf club manufacturers are constantly looking for a high strength panel material. Extremely high strength creates a thinner panel section and, therefore, is lighter, providing designers with more flexibility in the club head design. In addition, corrosion resistant materials are preferred over non-stainless steel materials because they do not require a surface coating or plating that can be removed during use. Current solutions to this problem include the use of standard PH stainless alloys such as CUSTOM 455 alloys and recently designed stainless alloys such as CUSTOM 465 and CUSTOM 475 alloys. However, CUSTOM 455 and CUSTOM 405 alloys do not provide the level of strength required in new golf designs. CUSTOM 475 alloy offers extremely high strength, but it is also highly alloyed, making it both expensive for club manufacturers and less tolerable for golf club manufacturing methods. In addition, many club heads are typically manufactured using a cast body having one of the panels. The cast body material is typically formed from a precipitation hardenable stainless steel such as 17-4 PH or 15-5 PH stainless steel. Golf clubs are typically manufactured by welding the panel to the casting body and then heat treating the entire assembly to obtain the final properties. Alloys for castings of clubs typically have a solution temperature of about 1900 °F (103 8 °C), whereas conventional panel materials have 1550 °F to 144341.doc 201024430 18〇〇T (843°c to 98rc) Range of solution temperatures. The mismatch in the heat treatment temperature causes the club body or panel material or both to provide optimum properties in less than the heat treated condition after assembly of the club head. In addition, CUSTOM 475 alloys often require different manufacturing methods at the same time because the alloy cannot be dissolved after the club head is assembled. SUMMARY OF THE INVENTION The disadvantages of overcoming conventional materials are achieved to a large extent by stainless steel strip articles in accordance with the present invention. According to one aspect of the present invention, there is provided a stainless steel strip article formed of corrosion resistant alloy I, the perishable alloy comprising the following, in terms of weight percent: C up to 0.03 Μη up to 10 Si up to 0·75 P up to 〇·〇40 S Most 〇·〇20 Cr 10.9-11.1 Ni 10.9-11·1 Mo 0.9-1.1 Ti 1.5-1.6 A1 Up to 0·25 Nb 0.7-0.8 Cu Up to 1 B Up to 0 · 010 N Up to 0·030 144341.doc 201024430 The rest and the iron and common miscellaneous f. The elongated strip provides a room temperature tensile strength of at least about 28 〇 ksi (i93 () 5 chest) in the treated solution and under aging hardening conditions. According to another aspect of the present invention, there is provided a method of making a thin article comprising the steps of casting a corrosion & gold having the composition of the above-mentioned weight percentage to form an ingot. The ingot is hot worked to form a stretched strip. The strip is then heat treated under inter-axial and temperature conditions to provide a final tensile strength of at least about 28 〇 ksi (i93 〇 5 Mb) at room temperature. According to still another aspect of the present invention, there is provided a method of manufacturing a golf club head, the method comprising casting a corrosion-resistant alloy having the composition of the above-mentioned weight percentage to form an ingot. The ingot is hot worked to form an elongated article and then thermally treated under conditions of time and temperature to aid in machinability and processability of the article. The strip of material is then machined to form a panel for a golf club head. The method includes the further step of forming a golf club head from a corrosion resistant precipitation hardenable steel alloy. The panel is welded to the golf club head. The assembly is then heat treated under conditions of time and temperature sufficient to provide the golf club head with the desired level of hardness and strength and to provide the panel with a final tensile strength of at least about 280 ksi (1930.5 MPa) at room temperature. [Embodiment] A preferred embodiment of the present invention comprises an elongated article having the following composition in weight percent: C up to 0.03 144341.doc 201024430 Μη up to 1.0 Si up to 0.75 P up to 0.040 S up to 0.020 Cr 10·9-11.! Ni 10·9-11.ι Mo 0-9-1.! Ti 1.5-1.6 A1 Up to 0.25 Nb 07-0.8 Cu Up to 1 B Up to 0.010 N Up to 0.030 The balance is iron and common impurities. The alloyed alloy is preferably melted using vacuum induction melting (VIM). Cast $ rust steel into - or multiple cast (four) pieces. For additional cleanliness, the alloy is subjected to vacuum arc remelting after the step (4). After solidification, the alloy is formed into a strip by recording by intermediate pressing to form a small embryo and then thermally pressing the small embryo to form an elongated t-bar. Alternatively, the strip may be formed by a hot roll die casting from about 19 Torr to 2250 F (103 8 C to 1232. The starting temperature of the crucible may be provided by about 11 〇〇卞 to 135 〇) The over-aging condition of heating (卞 it to 732 C) for about 2 to 8 hours and then cooling in air or, in terms of better machinability and workability, is about 1900 F to 1950 卞 (1038). (: to 1065. Underarm heating strip material for about i hours, 144341.doc 201024430 Cooled in air, frozen at about _10 (^73 3 〇 under the arm for about 8 hours, and then warmed it to the room in the air a. More expensive, the strip material is cold rolled to the final or near final thickness before the heat treatment. According to the invention, the strip material can be processed in a continuous furnace with corresponding adjustment of time and temperature. Known high-strength non-mineral steel alloys of CUSTOM 475 stainless steel alloys. The alloy strips according to the invention can be treated twice without significant loss of properties, in particular without loss of strength. In other words, the stainless steel strip material of the invention can be supplied to Treated solution and frozen Conditions, processed into components, then redissolved, re-frozen, and age hardened after assembly into a golf club head to provide the desired high strength and hardness. As an example of an elongated article according to the present invention, Melt and process smaller heads. Melt 400 11) (181.41^) heads with VIM+VAR, then cast into 8 in. (2〇·3 cm) ingots. The weight percent composition of vaR ingots is found in Table 1. The remaining components of the alloy are iron and common impurities. Table 1 C Μη Si PS Cr Ni Mo Ή Cb BN ~~i Ce 0.005 0.05 0.04 <0.005 <0.0005 11.05 11.02 1.01 1.56 0.79 0.0019 0.0016 0.001 at about 2300 °F The ingot was homogenized at (1260 ° C) for 16 hours and then pressed into a 4-inx8-in (10 cm x 20.3 cm) small embryo from an initial temperature of about 2 00 °F (1093 °C). The small embryo is hot-pressed into a strip of 7.5 in. width χ0·15 in. thick (19 cm wide x 3.8 mm thick) from an onset temperature of about 2250 °F (1232 °C). 0.135 in. (3.4 mm) thick, followed by a chill roll to a thickness of 0.1103 in. (2.8 mm). This is made by adding 144341.doc 201024430 ... 5.5 j _ at about 1146 °F (619 °C). Over-aging treatment line. Cooling &, rt i strip material is milled to a 0.1083 in. (2.75 mm) ultimate thickness. The standard strip tensile blank is rough cut from the longitudinally aged strip in the longitudinal and transverse directions. The blank group was solution treated at 185 〇卞 (1〇1〇.〇, 19〇〇卞(1038°C), 1950°F (1065°C), and 2000卞(1093〇) for 1 hour and then air. Cooling. The solution treated blanks were further quenched for 8 hours at _100 °F (-73.3 °C) and then allowed to warm up to room temperature in air. The blanks were then machined to provide about 1 Measurement section of /2 inches wide and 2 inches long (1.27 cm wide and 5.08 cm long). The rough machining blank set from each solution is approximately 900 卞 (482. (:) to approximately 975 °F). Aging for 4 hours in the range of (524 ° C), then air cooling. After the aging, the test sample was machined and then tested at room temperature. The results of room temperature tensile and hardness tests are shown in Table 2-4 below. Medium, including solution treatment temperature (solution temperature) and aging temperature (aging temperature) in °F (°C), 0.2% compensation yield strength (YS) and ultimate tensile strength (UTS) in ksi (MPa) , and Rockwell C grade hardness (hardness) in terms of HRC. 144341.doc 201024430 Table 2 Solution temperature aging temperature Turning Hardness (HRC) 1850T (1010°〇950〇F(510〇C) L 258(1779) 266(1834) .... 52.0 258(1779) 267(1841) ____ 258(1779) 268(1848 ) .. T 260 (1792) 272(1875) —— 260 (1792) 273(1882) —— 245 (1689) 272(1875) —— 975T (524°〇L 244 (1682) 252 (1737) — 50.5 244 (1682) 253 (1744) — 245 (1689) 253 (1744) — T 248 (1710) 258 (1779) — 246 (1696) 256 (1765) — 245 (1689) 255 (1758) — — 144341.doc 10- 201024430 Table 3 Solution Temperature Aging Temperature Direction SYSTS El.% Hardness (HRC) 260 (1792) 284 (1958) 4.8 L 261 (1799) 286 (1972) 4.3 259 (1785) 284 (19058) 4.8 900〇F(482〇C) 264 (1820) 287(1979) 4.3 53.5 T 257 (1772) 282(1944) 2.8 258 (1779) 285(1965) 4.2 259 (1785) 282(1944) 4.0 L 257 (1772 ) 281(1937) 4.2 925°F 256 (1765) 281 (1937) 4.1 53.5 (496°C) 247 (1703) 285 (1965) 3.9 T 260 (1792) 285 (1965) 4.1 1900T 257 (1772) 285 ( 1965) 4.2 (1038°〇250(1723) 274(1889) 6.2 L 252(1737) 273(1882) 6.7 249(1716) 273(1882) 6.4 950〇F(510〇C) 251 (1730) 277(1910) 6.5 52.0 T 250 (1723) 277(1910) 6.0 251 (1730) 276(1903) 6.7 234 (1613) 258(1779) 7.3 L 235 (1620) 256(1765) 7.1 975〇F 235 (1620) 259(1785) 6.9 50.5 (524〇C) 243 (1675) 264 (1820) 6.8 T 240 (1654) 261 (1799 ) 6.6 242 (1668) 263 (1813) 6.6 144341.doc -11 - 201024430 Table 4 Solution Temperature Aging Temperature Direction SYSTS EI.% Hardness (HRC) * * 4.6 L 氺4.1 900Τ(482°〇氺氺4.7 53.5 * * 5.4 T * 氺 4.2 氺 4.8 1950T (1065°〇* 氺5.3 L * 氺5.2 950T (510°〇* 氺4.3 264 (1820) 275 (1896) 5.3 52.5 Τ 267 (1841) 179 (1923) 4.9 260 ( 1792) 276 (1903) 5.3 248 (1710) 282 (1944) 5.9 L 253 (1744) 283 (1951) 5.0 255 (1758) 282 (1944) 5.5 900 °F (482〇C) 261 (1799) 286 (1972 ) 4.6 53.5 Τ 258 (1779) 291 (2006) 5.1 260 (1792) 287 (1979) 4.7 2000T (1093°〇253 (1744) 276(1903) 5.7 L 254 (1751) 277(1910) 5.2 950 F 255 (1758) 276 (1903) 5.2 53.0 (510°C) 260 (1792) 281 (1937) 4.7 Τ 261 (1799) 282 (1944) 4.6 263 (1813) 282 (1944) 5.0 *For these samples, The strength data is lost. However, the test operator recalled that the U.T.S. for the H900 sample was higher than 280 ksi (1930.5 MPa), and for the H950 sample U.T.S. was slightly lower than 280 ksi (193 0.5 MPa). 144341.doc -12- 201024430 / The metallographic analysis of the sample is shown in 卞(丨) and measured. The material solution treated under Fuom:) has a particle size of about astm8. The material solution treated at 1950 F (1G65 C ) has a particle size of about astm 7 8 . The (iv) solution treated under the leak v (1G9rc) has a particle size of about ASTM 2-3. Here and throughout the surname, the ASTM particle size means the average particle size as determined by ASTM Standard Test Method E-112. The results presented in Tables 2 and 4 show a preferred solution temperature of about 19 (9). ρ (1038 ° c) to about 195 yesterday (bri. 〇. Similarly, in order to provide the material 胄 280 ksi (1930.5 MPa) UTS ·, the preferred aging temperature is about 9 s to 925 T (482 ° C to 496 〇. In the figure, _UTS is a combination of solution and aging temperature. The data presented in the table shows that the article made from the alloy composition described in the present application can reach 280 ksi (193〇5 Mpa). Or higher UTS. This material is less than other heavy metal alloys that can reach the strength grade of the stainless steel composition' resulting in lower alloy cost. In addition, the strip # can be subjected to without sacrificing strength or redundancy properties. More than _ times solution heat treatment. The strip material of the present invention is preferably subjected to solution heat treatment at a temperature in the range of about 1900 1950 卞 (1 -8 〇 65 ° C) to make the golf club panel of the composition. The solution treatment temperature is exactly the same as that of the most commonly used golf club head riding hardenable stainless steel casting alloy. Therefore, it is possible to assemble the configuration for solution treatment and age the hardened panel and the golf club head so that not only the club head but also Make contact with golf balls The panel is subjected to maximum hardness and strength. It will be understood by those skilled in the art that variations and modifications can be made to the above-described embodiments without departing from the broad inventive concept of the present invention 144341.doc 201024430. Therefore, the present invention should be understood. The invention is not limited to the specific embodiments described, but it is intended to cover all modifications and variations within the scope and spirit of the invention as set forth in the appended claims. Temperature as a graph of the tensile strength of the function.

144341.doc •14·144341.doc •14·

Claims (1)

201024430 七、申請專利範圍： 1. 一種由耐腐蝕合金形成之經拉長之薄條物件，該耐腐钱 合金包括以下成份，以重量百分數計約： C 最多0.03 Μη 最多l.O Si 最多0.75 P 最多0.040 S 最多0.020 Cr 10.9-11.1 Ni 10.9-11.1 Mo 〇.9-1.1 Ti 1 · 5 -1.6 Al 最多0.25 Nb 0.7-0.8 Cu 最多1 B 最多0.010 N 最多0.030 片見雜質 ，该經拉長之薄條物件在所處 ’ 八、α丨不仍Ί1· # p/jT胃 的溶液中及老化硬化條件下具有至少約！㈣$黯之 溫抗拉強度。 2. 如請求項！之經拉長之條物件，其中該條具有約m 至2.8 mm之厚度。 3. 如請求们或2之經拉長之條物件，其中該合金具有主 尺寸不大於約ASTM 7-8之平均粒度。 I4434l.doc 201024430 4.如請求項1至3中任一項之經拉長之條物件，其具有約53_ 54HRC之硬度。 5· —種製造如請求項i之薄條物件之方法，其包括以下步 驟： 铸造耐腐蝕合金以形成一鑄錠； 機械處理該鑄錠以形成經拉長之條材料；及然後 在時間及溫度之條件下熱處理該經拉長之條材料以提 供在至溫下至少約1930.5 MPa之極限抗拉強度。 6·如請求項5之方法，其中熱處理該經拉長之條材料之該 步驟包括以下步驟： 春 在約1038-1G93C之溫度下加熱該經拉長之條材料；及 然後 在約482 C至約510 C之溫度下加熱該經拉長之條材料。 7·如請求項6之方法，其中該第一加熱步驟包括在約刪_ l〇65°C之溫度下加熱該合金及該方法在該等加熱步驟之 間包括以下步驟： 將該合金快速冷卻至約_73.3t ;及然後 ❹ 維持該合金於約_73.rc下一段足以將該合金中之任何 奥斯田鐵（austenite)實質上完全轉變為麻田散鐵 (martensite)之時間。 · 8.如請求項5至7中任一項之方法，其中機械處理缚旋之該 ， 步驟包括以下步驟： 壓製该禱鍵以形成一小胚；及然後 熱輥壓該小胚以形成經拉長之條材料。 144341.doc -2- 201024430 9. 如凊求項5至7中任一項之方法，其中機械處理鎢錠之該 步驟包括熱輥壓該鑄鍵以形成經拉長之條材料。 10. 如4求項9之方法，其中該熱輥壓步驟包括將該小胚加 熱至約 1038-1232。(：。 11· 一種由如請求項1之經拉長之條材料製造一高爾夫球杆 頭之方法’其包括以下步驟： 鑄造耐腐蝕合金以形成一鑄錠； 機械處理該鑄錠形成經拉長之條材料； ® 在用以改善該材料之機械可加工性及可加工性的時間 及溫度之條件下熱處理該經拉長之條材料； 切割該經拉長之條材料以形成一用於高爾夫球杆頭之 面板； 由耐腐蝕之可沉澱硬化之鋼合金形成一高爾夫球杆頭 體； 將該面板焊接至該高爾夫球杆頭體以形成一高爾夫球 杆頭組裝；及然後 A 在對該高爾夫球杆頭組裝提供硬度及強度及對該面板 提供在室溫下至少約1930.5 MPa之極限抗拉強度的時間 與溫度之條件下熱處理該高爾夫球杆頭組裝。 12.如請求項11之方法，其中熱處理高爾夫球杆頭組裝之該 步驟包括以下步驟： 在約1038-10931之溫度下加熱該經拉長之條材料；及 然後 在約482°C至約51(TC之溫度下加熱該經拉長之條材 144341.doc 201024430 料。 13.如請求項12之方法，其中第一加熱步驟包括在約1〇38_ l〇65°C之溫度下加熱該高爾夫球杆頭組裝，且該方法在 該等加熱步驟之間包括以下步驟： 將該高爾夫球杆頭組裝快速地冷卻至約_73 3〇c ;及然後 維持該高爾夫球杆頭組裝於約_73 ；rc 一段足以將合金 中之任何奥斯田鐵（austenite)實質上完全地轉變為麻田 散鐵（martensite)之時間。 Μ.如請求則至"中任一項之方法’其中機械處理鑄錠之 該步驟包括以下步驟： 壓製該鑄錠以形成一小胚；及然後 熱輕壓該小胚以形成該經拉長之條材料。 .如請求項H13中之任-項之方法，其中機械處理麟 之該步驟包括熱輕壓該鑄錠以形成經拉長之條材料。 16.如請求項14或15之方法，其ψ姑私 、中該熱輥壓步驟包括將該鑄 錠或小胚加熱至約1038-1232。^。 17·如請M U之Μ ’其中熱處理經拉長之條材料之該步 驟包括在約593·7^下使該條材料過度老化之步驟。 18.如請求項11至13中任一項之 去’其中機械處理錄錠之 該步驟包括以下步驟·· 壓製該鑄錠以形成一小胚； 之條材料；及然後 減少其厚度至最終或接近 熱輥壓該小胚以形成經拉長 冷輥壓該經拉長之條材料以 最終尺寸。 I44341.doc 201024430 項之方 19.如請求項11至13中任一 該步驟包括以下步驟： 法，其中機械處理铸錠之 長之條材料；及然後 以減少其厚度至最終或接近 熱輥壓該鑄錠以形成經拉 冷輥壓該經拉長之條材料 最終尺寸。 20.如請求項18或19之方法，其中該熱輥壓步驟包括將該鑄 錠或小胚加熱至約1038-123 2。〇。 144341.doc201024430 VII. Patent application scope: 1. An elongated thin strip object formed of corrosion-resistant alloy, the corrosion-resistant alloy includes the following components, in terms of weight percentage: C up to 0.03 Μη max. lO Si up to 0.75 P up to 0.040 S up to 0.020 Cr 10.9-11.1 Ni 10.9-11.1 Mo 〇.9-1.1 Ti 1 · 5 -1.6 Al up to 0.25 Nb 0.7-0.8 Cu up to 1 B up to 0.010 N up to 0.030 pieces see impurities, the elongated thin The article has at least about at least in the solution of '8, α丨, Ί1·#p/jT stomach and aging hardening conditions! (4) The temperature tensile strength of $黯. 2. As requested! An elongated article, wherein the strip has a thickness of from about m to 2.8 mm. 3. An elongated article as claimed or 2, wherein the alloy has an average size of no greater than about ASTM 7-8. The elongated article of any one of claims 1 to 3 having a hardness of about 53 _ 54 HRC. 5. A method of making a thin article of claim i, comprising the steps of: casting a corrosion resistant alloy to form an ingot; mechanically treating the ingot to form an elongated strip of material; and then at time and The elongated strip of material is heat treated under temperature conditions to provide an ultimate tensile strength of at least about 1930.5 MPa to ambient temperature. 6. The method of claim 5, wherein the step of heat treating the elongated strip of material comprises the steps of: heating the elongated strip of material at a temperature of about 1038-1 G93 C; and then at about 482 C to The elongated strip of material is heated at a temperature of about 510 C. 7. The method of claim 6, wherein the first heating step comprises heating the alloy at a temperature of about 65 ° C and the method comprises the steps of: heating the alloy rapidly between the heating steps To about _73.3t; and then 维持 maintain the alloy at about _73.rc for a period of time sufficient to substantially completely convert any of the austenite in the alloy to martensite. 8. The method of any one of claims 5 to 7, wherein the mechanically treating the binding, the step comprising the steps of: pressing the prayer key to form a small embryo; and then hot rolling the small embryo to form a Stretched strip material. The method of any one of clauses 5 to 7, wherein the step of mechanically treating the tungsten ingot comprises hot rolling the cast key to form an elongated strip of material. 10. The method of claim 9, wherein the hot rolling step comprises heating the small embryo to about 1038-1232. (11. A method of manufacturing a golf club head from the elongated strip material of claim 1) comprising the steps of: casting a corrosion-resistant alloy to form an ingot; mechanically treating the ingot to form a pull-up Long strip of material; heat treating the elongated strip of material at a time and temperature to improve the mechanical processability and processability of the material; cutting the elongated strip of material to form a a golf club head panel; a golf club head formed from a corrosion resistant precipitation hardenable steel alloy; the panel is welded to the golf club head body to form a golf club head assembly; and then A is in the pair The golf club head assembly provides for hardness and strength and heat-treating the golf club head assembly under conditions that provide the panel with time and temperature of at least about 1930.5 MPa ultimate tensile strength at room temperature. The method wherein the step of heat treating the golf club head assembly comprises the steps of: heating the elongated strip of material at a temperature of about 1038-10931; and then at about 482 The method of claim 12, wherein the first heating step comprises at about 1〇38_l〇65°C, from °C to about 51 (the temperature of TC is heated to the elongated strip 144341.doc 201024430. Heating the golf club head assembly at temperature, and the method includes the steps of: heating the golf club head assembly to approximately _73 3 〇c; and then maintaining the golf club head Assembled at approximately _73; rc for a period of time sufficient to substantially convert any austenite in the alloy to a martensite. 如. If requested, to any of the methods The step of mechanically treating the ingot comprises the steps of: pressing the ingot to form a small embryo; and then thermally pressing the small embryo to form the elongated strip of material. As claimed in claim H13 - The method of the present invention, wherein the step of mechanically treating the lining comprises thermally pressing the ingot to form an elongated strip of material. 16. The method of claim 14 or 15, wherein the hot rolling step comprises The ingot or small embryo is heated to about 1038-1232. ^ 17. If MU is selected Μ 'This step of heat-treating the elongated strip material includes the step of over-aging the strip at about 593·7^. 18. As required by any of claims 11 to 13. 'The step of mechanically processing the ingot comprises the steps of: pressing the ingot to form a small embryo; strip material; and then reducing the thickness thereof to the final or near hot rolling of the small embryo to form an elongated chill roll Pressing the elongated strip material to a final size. I44341.doc 201024430 Item 19. The method of any of claims 11 to 13 includes the steps of: mechanically treating the length of the ingot material; The ingot is then reduced by reducing its thickness to a final or near hot roll to form a stretched roll to compress the final length of the strip of material. The method of claim 18 or 19, wherein the hot rolling step comprises heating the ingot or the small embryo to about 1038-123 2 . Hey. 144341.doc
TW098137054A 2008-10-31 2009-10-30 Very high-strength stainless alloy strip, manufacturing method thereof and method for manufacturing golf club head using the extremely high-strength stainless alloy strip TWI417402B (en)

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