Invention Application
US20160090841A1 GAS TURBINE ENGINE BLADE SLOT HEAT SHIELD 审中-公开
燃气涡轮发动机叶片炉盖

GAS TURBINE ENGINE BLADE SLOT HEAT SHIELD
Abstract:
A gas turbine engine rotor assembly includes a rotor disk with a slot. A rotor blade has a root supported within the slot. A heat shield is arranged in a cavity in the slot between the root and the rotor disk. An axial retention feature is configured to axially maintain the heat shield within the slot.
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