| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide an additional disk for a gas turbine engine. <P>SOLUTION: CMC disks 64A, 64B and 64C for a gas turbine engine 20 include CMC hubs 68A, 68B and 68C defined about an axis, and a plurality of CMC airfoils 66A, 66B and 66C integrated with the respective CMC hubs. The CMC disks 64A, 64B and 64C for the gas turbine engine 20 include the plurality of CMC airfoils 66A, 66B and 66C integrated with the respective CMC hubs 68A, 68B and 68C, and rails 80A, 80C integrated with the respective CMC hubs on sides opposite to the plurality of airfoils. The rails define rail platforms adjacent to the plurality of airfoils and tapered to a rail inner bore. <P>COPYRIGHT: (C)2013,JPO&INPIT |
