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A platform for research: civil engineering, architecture and urbanism
TURBINE BLADE OF CERAMIC MATRIX MATERIAL
A turbine blade (10) of ceramic matrix composite material comprises a root (12) for attaching the turbine blade (10) to a disk, an airfoil (14) shaped to interact with hot gasses moving through the gas path of a gas turbine engine and cause rotation of the turbine blade (10), and a platform (16) having an attachment side facing the root (12) and a gas path side facing the airfoil (14). The platform (16) is arranged between the root (12) and the airfoil (14) and shaped to extend outwardly from the root (12) and the airfoil (14) in order to block gasses from the gas path migrating toward the root (12) when the turbine blade (10) is used in a gas turbine engine. The turbine blade (10) includes core fiber-reinforcement plies (20) that form part of the root (12) and the airfoil (14) without forming part of the platform (16), at least one gas path fiber-reinforcement ply (22) that forms part of the airfoil (14) and the platform (16), and attachment fiber-reinforcement plies (24) that form part of the root (12) and the platform (16). The number of attachment fiber-reinforcement plies (24) is greater than the number of gas path fiber-reinforcement plies (22) so that radial forces induced on the platform (16) are largely transferred to the root (12) without having to pass between fiber-reinforcement plies (20, 22, 24) of the turbine blade (10).
TURBINE BLADE OF CERAMIC MATRIX MATERIAL
A turbine blade (10) of ceramic matrix composite material comprises a root (12) for attaching the turbine blade (10) to a disk, an airfoil (14) shaped to interact with hot gasses moving through the gas path of a gas turbine engine and cause rotation of the turbine blade (10), and a platform (16) having an attachment side facing the root (12) and a gas path side facing the airfoil (14). The platform (16) is arranged between the root (12) and the airfoil (14) and shaped to extend outwardly from the root (12) and the airfoil (14) in order to block gasses from the gas path migrating toward the root (12) when the turbine blade (10) is used in a gas turbine engine. The turbine blade (10) includes core fiber-reinforcement plies (20) that form part of the root (12) and the airfoil (14) without forming part of the platform (16), at least one gas path fiber-reinforcement ply (22) that forms part of the airfoil (14) and the platform (16), and attachment fiber-reinforcement plies (24) that form part of the root (12) and the platform (16). The number of attachment fiber-reinforcement plies (24) is greater than the number of gas path fiber-reinforcement plies (22) so that radial forces induced on the platform (16) are largely transferred to the root (12) without having to pass between fiber-reinforcement plies (20, 22, 24) of the turbine blade (10).
TURBINE BLADE OF CERAMIC MATRIX MATERIAL
TURBINENSCHAUFEL AUS KERAMISCHEM FASERVERBUNDWERKSTOFF
AUBE D'UNE TURBINE EN MATÉRIAU À MATRICE CÉRAMIQUE
SIPPEL AARON D (author) / VETTERS DANIEL K (author) / FREEMAN TED J (author) / THOMAS DAVID J (author)
2020-01-29
Patent
Electronic Resource
English
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