Turbine rotor blade assembly and method of assembling same

1. A rotor blade assembly for a rotor of a gas turbine engine having an axis of rotation, said rotor blade assembly comprising:

a shank portion formed from a ceramic matrix composite (CMC) material;

a platform portion formed from the same CMC material as that of said shank portion, said platform portion coupled to said shank portion, wherein said platform portion and said shank portion cooperate to at least partially define two opposing side portions of said rotor blade assembly, wherein said opposing side portions are angularly separated with respect to the axis of rotation;

a damper; and

a damper retention apparatus, wherein at least a portion of said damper retention apparatus is coupled to said shank portion, said damper retention apparatus comprises at least one angled bracket apparatus extending toward a circumferentially adjacent rotor blade assembly, wherein said at least one angled bracket apparatus comprises a first portion and a second portion, said second portion coupled to said first portion, said first portion and said second portion define an angle therebetween, said first portion coupled to said shank portion, said second portion extends outwardly from said shank portion toward an adjacent shank portion of the circumferentially adjacent rotor blade assembly, wherein said damper retention apparatus comprises a CMC insert coupled to an interface defined by a side wall of said shank portion and an underside of said platform portion via a first interference fit and the CMC insert is coupled to the platform underside, the interface, and the second portion, wherein a pocket is formed within said CMC insert, said pocket is sized and oriented to receive at least a portion of said damper via a second interference fit, and

wherein said damper is retained in said damper retention apparatus via the second interference fit.

2. A rotor blade assembly in accordance with claim 1 , wherein said at least one angled bracket apparatus is formed from the same CMC material as that of said shank portion and said platform portion.

3. A rotor blade assembly in accordance with claim 2 , wherein said at least one angled bracket apparatus is formed substantially unitarily with said shank portion and said platform portion.

4. A rotor blade assembly in accordance with claim 1 further comprising:

said at least one angled bracket apparatus coupled to a first side of said two opposing side portions; and

said CMC insert coupled to a second side of said two opposing side portions.

5. A rotor assembly for a gas turbine engine having an axis of rotation, said rotor assembly comprising:

a rotor disk defining a periphery thereon;

a plurality of rotor blades coupled to said periphery of said rotor disk, said plurality of rotor blades positioned substantially circumferentially adjacent to each other in an angularly spaced relationship with respect to the axis of rotation, wherein each of said rotor blades comprises:

a shank portion formed from a ceramic matrix composite (CMC) material;

a platform portion formed from the same CMC material as that of said shank portion, said platform portion coupled to said shank portion, wherein said platform portion and said shank portion cooperate to at least partially define two opposing side portions of each of said rotor blades, wherein said opposing side portions are angularly separated with respect to the axis of rotation;

a damper; and

a damper retention apparatus, wherein at least a portion of said damper retention apparatus is coupled to said shank portion, said damper retention apparatus comprises at least one angled bracket apparatus extending toward said circumferentially adjacent rotor blade, wherein said at least one angled bracket apparatus comprises a first portion and a second portion, said second portion coupled to said first portion, said first portion and said second portion define an angle therebetween, said first portion coupled to said shank portion, said second portion extends outwardly from said shank portion toward an adjacent shank portion of the circumferentially adjacent rotor blade assembly, wherein said damper retention apparatus comprises a CMC insert coupled to an interface defined by a side wall of said shank portion and an underside of said platform portion via a first interference fit and the CMC insert is coupled to the platform underside, the interface, and the second portion, wherein a pocket is formed within said CMC insert, said pocket is sized and oriented to receive at least a portion of said damper via a second interference fit, and

wherein said damper is retained in said damper retention apparatus via the second interference fit.

6. A rotor assembly in accordance with claim 5 , wherein said at least one angled bracket apparatus is formed from a substantially similar CMC material as that of said shank portion and said platform portion.

7. A rotor assembly in accordance with claim 6 , wherein said at least one angled bracket apparatus is formed substantially unitarily with said shank portion and said platform portion.

8. A rotor assembly in accordance with claim 5 further comprising:

said at least one angled bracket apparatus coupled to a first side of said two opposing side portions; and

said CMC insert coupled to a second side of said two opposing side portions,

wherein, said at least one angled bracket apparatus coupled to a first of said rotor blades and said CMC insert coupled to said circumferentially adjacent rotor blade are complementary such that said angled bracket apparatus, said CMC insert, and the damper positioned between said at least one angled bracket apparatus and said platform portion remain substantially in position via a series of interference fits throughout acceleration, deceleration, and substantially stationary operation of said rotor assembly.

9. A method of assembling a rotor blade assembly, said method comprising:

forming a shank portion from a ceramic matrix composite (CMC) material;

forming a platform portion from the same CMC material as that of the shank portion;

coupling the platform portion to the shank portion, wherein the platform portion and the shank portion cooperate to at least partially define two opposing side portions of the rotor blade assembly, wherein the opposing side portions are angularly separated with respect to an axis of rotation of a rotor of a gas turbine engine;

forming a damper retention apparatus comprising:

forming at least one angled bracket apparatus comprising forming a first portion of the at least one angled bracket apparatus; forming a second portion of the at least one angled bracket apparatus; coupling the first portion to the second portion, wherein the first portion and the second portion define an angle therebetween; coupling the first portion to the shank portion; and circumferentially extending the second portion away from the shank portion;

forming a CMC insert;

coupling the CMC insert to an interface defined by a side wall of the shank portion and an underside of the platform portion by a first interference fit and the CMC insert is coupled to the platform underside, the interface, and the second portion; and

forming a pocket within the CMC insert such that the pocket is sized and oriented to receive at least a portion of the damper via a second interference fit;

and inserting a damper into said damper retention apparatus, wherein said damper is retained in said damper retention apparatus via the second interference fit.

10. A method in accordance with claim 9 , wherein forming at least one angled bracket apparatus comprises forming the at least one angled bracket apparatus from the same CMC material as that of the shank portion and the platform portion.

11. A method in accordance with claim 10 further comprising forming the at least one angled bracket apparatus substantially unitarily with the shank portion and the platform portion.