Non-integral blade and platform segment for rotor

1. A rotor comprising:

a rotor hub;

a plurality of blades mounted in a circumferentially-spaced arrangement on the rotor hub; and

a plurality of platform segments circumferentially arranged, respectively, between neighboring ones of the plurality of blades, the plurality of platform segments including core gas-path defining surfaces, each of the plurality of platform segments being mounted with a freedom to circumferentially move relative to the respective neighboring ones of the plurality of blades, the plurality of platform segments including non-gas path defining surfaces disposed opposite from the core gas path defining surfaces and hooks projecting from the non-gas path defining surfaces, the hooks interlocking with corresponding hooks of attachment members that are distinct from the rotor hub and that are secured to the rotor hub, the attachment members engaging radially inwardly facing surfaces of the rotor hub with respect to a rotational axis of the rotor hub.

2. The rotor as recited in claim 1 , wherein the radially inwardly facing surfaces of the rotor hub are located radially inwards of a plurality of slots in which the plurality of blades are mounted.

3. The rotor as recited in claim 1 , wherein each of the plurality of platform segments includes two axially-spaced apart hooks.

4. The rotor as recited in claim 3 , wherein the two axially-spaced apart hooks are radially offset from one another.

5. The rotor as recited in claim 4 , wherein one of the two axially-spaced apart hooks is interlocked with a corresponding hook of an attachment member that is secured to the rotor hub, and the other of the two axially-spaced apart hooks engages a radially inwardly facing surface of the rotor hub with respect to a rotational axis of the rotor hub.

6. The rotor as recited in claim 1 , wherein there is a circumferential gap between each of the plurality of platform segments and at least one of the respective neighboring ones of the plurality of blades.

7. The rotor as recited in claim 1 , wherein the plurality of blades include respective ceramic airfoil bodies.

8. The rotor as recited in claim 7 , wherein the ceramic airfoil bodies have a first composition and the plurality of platform segments have a second composition that differs from the first composition in chemical formulation.

9. The rotor as recited in claim 8 , wherein the second composition is metallic.

10. The rotor as recited in claim 7 , wherein the plurality of platform segments include respective ceramic platform bodies.

11. The rotor as recited in claim 1 , wherein the plurality of platform segments include, respectively, pockets disposed opposite from the core gas-path defining surfaces, and further comprising damper members located, respectively, in the pockets.

12. The rotor as recited in claim 1 , wherein the plurality of blades includes, respectively, serrated root portions received in corresponding slots the rotor hub.

13. A method of damping in a rotor, the method comprising:

providing a rotor hub, a plurality of blades mounted in a circumferentially-spaced arrangement on the rotor hub and a plurality of platform segments circumferentially arranged, respectively, between neighboring ones of the plurality of blades, each of the plurality of platform segments including, respectively, core gas-path defining surfaces, the plurality of platform segments including non-gas path defining surfaces disposed opposite from the core gas-path defining surfaces and hooks projecting from the non-gas path defining surfaces, the hooks interlocking with corresponding hooks of attachment members that are distinct from the rotor hub and that are secured to the rotor hub, the attachment members engaging radially inwardly facing surfaces of the rotor hub with respect to a rotational axis of the rotor hub; and

damping vibration in the rotor with circumferential movement of the plurality of platform segments relative to the respective neighboring ones of the plurality of blades.