Integrated ceramic matrix composite rotor disk geometry for a gas turbine engine

摘要

A CMC disk for a gas turbine engine includes a CMC hub defined about an axis and a multiple of CMC airfoils integrated with the CMC hub.

主权项

1. A CMC disk for a gas turbine engine comprising:
a multiple of CMC airfoils integrated with a CMC hub, said CMC hub defined about an axis, said CMC hub defining a full hoop inner shroud that projects forward and aft of said CMC airfoils and a rail extending radially inwards from said shroud to an innermost bore, said rail including first and second axial sides, with one of said first and second axial sides being substantially perpendicular to said axis and the other of said first and second axial sides tapering to said innermost bore such that an axially narrowest dimension of said rail is at said innermost bore, wherein said one of said first and second axial sides that is substantially perpendicular to said axis includes a radially outer end that meets said inner shroud at a filet and a radially inner end at said innermost bore.