| CPC F01D 5/3007 (2013.01) [F01D 5/02 (2013.01); F02C 7/36 (2013.01); F01D 5/3084 (2013.01); F05D 2220/32 (2013.01); F05D 2240/24 (2013.01); F05D 2260/40311 (2013.01); F05D 2300/6033 (2013.01)] | 20 Claims |

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1. A turbine for a gas turbine engine, comprising:
a shaft rotatable about a longitudinal axis;
a turbine rotor including one or more rows of turbine blades and a disk assembly coupled to the shaft, wherein each of the turbine blades includes an airfoil section extending radially outwardly from a root section relative to the longitudinal axis, and each of the turbine blades comprises a ceramic matrix composite (CMC) material;
wherein the disk assembly includes one or more metallic disks each having an attachment region extending radially between an inner boundary and an outer boundary, the outer boundary is established by an outer periphery of the respective disk, the attachment region defines an array of slots distributed about the outer periphery, each of the slots extends radially inwardly from the outer boundary to the inner boundary, and each of the slots is dimensioned to receive the root section of a respective one of the turbine blades to mount the turbine blades to the disk assembly;
wherein the inner boundary establishes a live rim radius relative to the longitudinal axis, the outer boundary establishes a dead rim radius relative to the longitudinal axis, each of the one or more disks establishes a disk ratio of the live rim radius to the dead rim radius, and the disk ratio is greater than or equal to 0.8:1 for at least one disk of the one or more disks; and
wherein the attachment region includes an array of attachment members that define the array of slots, a minimum width of each of the attachment members establishes a first width, a minimum width of each of the slots establishes a second width, and a ratio of the first width of each one of the respective attachment members to the second width of an adjacent one of the slots is less than or equal to 0.5:1.
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