A hybrid airfoil for a gas turbine engine according to an exemplary embodiment of this disclosure can include a leading edge portion, a trailing edge portion, and an intermediate portion between the leading edge portion and the trailing edge portion. The leading edge portion can be made of a first m
A hybrid airfoil for a gas turbine engine according to an exemplary embodiment of this disclosure can include a leading edge portion, a trailing edge portion, and an intermediate portion between the leading edge portion and the trailing edge portion. The leading edge portion can be made of a first material, the trailing edge portion can be made of a second material, and the intermediate portion can be made of a third material. At least two of the first material, the second material and the third material are different materials.
대표청구항▼
1. A hybrid airfoil for a gas turbine engine, comprising: a leading edge portion;a trailing edge portion;an intermediate portion between said leading edge portion and said trailing edge portion, wherein said intermediate portion is a solid section of the hybrid airfoil that excludes any radial passa
1. A hybrid airfoil for a gas turbine engine, comprising: a leading edge portion;a trailing edge portion;an intermediate portion between said leading edge portion and said trailing edge portion, wherein said intermediate portion is a solid section of the hybrid airfoil that excludes any radial passages, and wherein said leading edge portion is made of a first material, said trailing edge portion is made of a second material, and said intermediate portion is made of a third material, and at least two of said first material, said second material and said third material are different materials;a rib disposed between said leading edge portion and said intermediate portion, wherein a protrusion of one of said rib and said intermediate portion is received within a pocket of the other of said rib and said intermediate portion; andan intermediate bonding layer between said rib and said intermediate portion. 2. The hybrid airfoil as recited in claim 1, wherein said first material and said second material are metallic materials. 3. The hybrid airfoil as recited in claim 1, wherein said third material is one of a ceramic material and a ceramic matrix composite (CMC) material. 4. The hybrid airfoil as recited in claim 1, wherein said first material is a metallic material and said second material is a non-metallic material. 5. The hybrid airfoil as recited in claim 1, wherein said airfoil is a turbine vane. 6. A hybrid airfoil for a gas turbine engine, comprising: a leading edge portion;a trailing edge portion;an intermediate portion between said leading edge portion and said trailing edge portion, wherein said leading edge portion is made of a first material, said trailing edge portion is made of a second material, and said intermediate portion is made of a third material, and at least two of said first material, said second material and said third material are different materials; andwherein a portion between said leading edge portion and said intermediate portion includes a pocket that receives a non-metallic portion, wherein a connection interface is established between said leading edge portion and said non-metallic portion. 7. The hybrid airfoil as recited in claim 6, comprising an intermediate bonding layer disposed between said portion and said non-metallic portion. 8. A hybrid airfoil for a gas turbine engine, comprising: a hybrid airfoil body including: a metallic portion;a non-metallic portion; andan intermediate bonding layer disposed between said metallic portion and said non-metallic portion;wherein said intermediate bonding layer includes a variation in composition and structure gradually over volume between said metallic portion and said non-metallic portion. 9. The hybrid airfoil as recited in claim 8, wherein said intermediate bonding layer includes a gradient between said metallic portion and said non-metallic portion. 10. The hybrid airfoil as recited in claim 8, wherein said non-metallic portion includes one of a ceramic material and a ceramic matrix composite (CMC) material and said metallic portion includes one of a cobalt based super alloy material and a nickel based super alloy material. 11. A hybrid airfoil for a gas turbine engine, comprising: a hybrid airfoil body including: a metallic portion;a non-metallic portion; andan intermediate bonding layer disposed between said metallic portion and saidnon-metallic portion;wherein said intermediate bonding layer includes a functionally graded material (FGM). 12. A hybrid airfoil for a gas turbine engine, comprising: a hybrid airfoil body including: a metallic portion;a non-metallic portion; andan intermediate bonding layer disposed between said metallic portion and said non-metallic portion;wherein said intermediate bonding layer is mechanically trapped between said metallic portion and said non-metallic portion. 13. A hybrid airfoil for a gas turbine engine, comprising: a hybrid airfoil body including: a metallic portion;a non-metallic portion; andan intermediate bonding layer disposed between said metallic portion said non-metallic portion;wherein said non-metallic portion is received within a pocket of said metallic portion.
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이 특허에 인용된 특허 (19)
Morrison, Jay A.; Merrill, Gary B.; Lane, Jay E.; Campbell, Christian X.; Thompson, Daniel G.; Carelli, Eric V.; Taut, Christine, Ceramic composite vane with metallic substructure.
Morrison, Jay A.; Campbell, Chris; Merrill, Gary Brian; Lane, Jay Edgar; Thompson, Daniel George; Albrecht, Harry A.; Shteyman, Yevgeniy P., Ceramic matrix composite gas turbine vane.
John E. Holowczak ; Karl M. Prewo ; Jayant S. Sabnis ; William K. Tredway, Hybrid monolithic ceramic and ceramic matrix composite airfoil and method for making the same.
Chen Otis Y. (West Hartford CT) Craig Harold M. (West Hartford CT) Allen Glenn M. (Ellington CT) Jarmon David C. (Kensington CT), Process for making a hybrid ceramic article.
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