Dual alloy turbine blade

Details Dual alloy turbine blade Dual alloy turbine blade

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/30 (2006.01) B23P 15/02 (2006.01) F01D 5/28 (2006.01)

Patent

CA 2060884

2060884 9101433 PCTABS00003 A composite turbine blade (20) having a single crystal airfoil section (22), a single crystal platform (26), and a composite attachment section (24). The attachment section (24) is comprised of a thin layer (34) of single crystal material overlying and metallurgically bonded, along interfacial bond lines (36), to a core (30) made of a fined grained, polycrystalline superalloy. The layer (34) has an external configuration having ridges (27) and grooves (28) for removably attaching to a complementary groove in a turbine disk. The blade is prepared by casting a single crystal body with a cavity within the attachment section (24), and then filling the attachment section with the polycrystalline superalloy to form a composite structure. Filling is preferably accomplished by plasma spraying the cavity with the superalloy, and hot isostatically compacting the sprayed superalloy to minimize porosity. The composite structure is then heat treated to develop an optimized microstructure in the dual alloy attachment section (24). The resulting turbine blade (20) has improved life resulting from reduced low cycle fatigue susceptibility of the composite attachment section (24).

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