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First stage dual-alloy turbine wheel

  • US 8,262,817 B2
  • Filed: 06/11/2007
  • Issued: 09/11/2012
  • Est. Priority Date: 06/11/2007
  • Status: Active Grant
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1. A method of manufacturing a first-stage turbine adapted for receiving high energy air directly from a combustion chamber in a gas turbine engine, the method comprising the steps of:

  • hot isostatic pressing a first alloy comprising about 0.02 to about 0.04 wt % carbon, 0 to about 0.15 wt % manganese, 0 to about 0.20 wt % silicon, 0 to about 0.015 wt % phosphorous, 0 to about 0.015 wt % sulfur, 0 to about 0.06 wt % zirconium, 0 to about 0.05 wt % tungsten, 0 to about 0.50 wt % iron, 0 to about 0.10 wt % copper, 0 to about 0.0010 wt % lead, 0 to about 0.00005 wt % bismuth, 0 to about 0.0250 wt % oxygen, 0 to about 0.0060 wt % nitrogen, about 14 to about 16 wt % chromium, about 16 to about 18 wt % cobalt, about 4.5 to about 5.5 wt % molybdenum, about 3.35 to about 3.65 wt % titanium, about 3.85 to about 4.15 wt % aluminum, and about 0.015 to about 0.025 wt % boron, and the balance nickel in the form of a powder, with the maximum allowable oxygen content depending on the size of the powder, to form a disk having an outer surface;

    casting a unitary blade ring having an inner surface from a second alloy comprising about 0.07 to about 0.20 wt % carbon, 0 to about 0.10 wt % manganese, 0 to about 0.10 wt % silicon, 0 to about 0.015 wt % phosphorus, 0 to about 0.015 wt % sulfur, about 12.20 to about 13 wt % chromium, about 8.5 to about 9.5 wt % cobalt, about 1.7 to about 2.10 wt % molybdenum, about 3.85 to about 4.5 wt % tungsten, about 3.85 to about 4.50 wt % tantalum, about 3.85% to about 4.15 wt % titanium, about 3.2 to about 3.60 wt % aluminum, about 7.30 to about 7.70 wt % aluminum and titanium combined, about 0.75 to about 1.05 wt % hafnium, about 0.010 to about 0.020 wt % boron, about 0.03 to about 0.14 wt % zirconium, 0 to about 0.50 wt % iron, 0 to about 0.10 wt % columbium, and the balance nickel, the unitary blade ring comprising an annular member, and blades that are integrally formed with the annular member;

    joining the disk and the unitary blade ring; and

    solution heat treating the joined disk and unitary blade ring.

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