Interturbine vane with multiple air chambers
A gas turbine engine has a mid turbine frame disposed between turbine rotor assemblies. The mid turbine frame includes hollow airfoils radially extending through an annular gas path duct. The airfoils each include a double-walled leading edge structure to define a front chamber separated from a rear...
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Main Authors | , |
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Format | Patent |
Language | English |
Published |
04.11.2014
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Subjects | |
Online Access | Get full text |
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Summary: | A gas turbine engine has a mid turbine frame disposed between turbine rotor assemblies. The mid turbine frame includes hollow airfoils radially extending through an annular gas path duct. The airfoils each include a double-walled leading edge structure to define a front chamber separated from a rear chamber defined in the remaining space within the airfoil. |
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Bibliography: | Application Number: US201313942876 |