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A composite blade assembly and a method of assembling a composite blade are provided. The composite blade assembly includes a composite blade having a radially inner root. A composite blade assembly includes a first platform and a circumferentially adjacent second platform abutting the first platfor

A composite blade assembly and a method of assembling a composite blade are provided. The composite blade assembly includes a composite blade having a radially inner root. A composite blade assembly includes a first platform and a circumferentially adjacent second platform abutting the first platform at a platform joint. Each of the first platform and the second platform includes a radially outer surface and a radially inwardly extending attachment member. The platform joint includes a slot extending through adjacent edges of the first platform and the second platform. The slot is configured to receive the radially inner root and the radially inner root is configured to be sandwiched between the attachment members. The blade assembly includes an adhesive system configured to join the radially inner root of the composite blade and the attachment members into a unitary structure, and a retaining clip configured to bias the attachment members towards each other.

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1. A composite blade assembly comprising: a composite blade comprising a radially inner root, a radially outer tip, and an airfoil extending therebetween, said radially inner root comprising a dovetail; a first platform and a circumferentially adjacent second platform abutting said first platform at

1. A composite blade assembly comprising: a composite blade comprising a radially inner root, a radially outer tip, and an airfoil extending therebetween, said radially inner root comprising a dovetail; a first platform and a circumferentially adjacent second platform abutting said first platform at a platform joint, each of said first platform and said second platform comprising a radially outer surface and a radially inwardly extending attachment member, said platform joint comprising an axially extending slot extending through adjacent edges of said first platform and said second platform, said slot configured to receive said radially inner root, said radially inner root configured to be sandwiched between said attachment members; an adhesive system configured to join said radially inner root of said composite blade and said attachment members into a unitary structure; and a retaining clip configured to bias said attachment members towards each other, wherein said retaining clip comprises a bias member coupled to a pair of legs extending orthogonally from said bias member so as to engage with circumferentially opposite faces of said attachment members, and wherein the attachment members are separated with respect to each other by a gap into which the radially inner root is received. 2. The assembly of claim 1, wherein said retaining clip is formed of at least one of a metallic material and a composite material. 3. The assembly of claim 1, wherein said retaining clip is configured to exert a clamping force on said attachment members and said radially inner root of said composite blade. 4. The assembly of claim 1, wherein said retaining clip is configured to resist a separation of said composite blade and said composite blade assembly. 5. The assembly of claim 1, wherein said composite blade comprises a composite blade of a booster compressor. 6. A method of assembling a separable blade, said method comprising: providing a compressor blade including a radially outer tip, a radially inner root, and an airfoil extending therebetween; providing a pair of platform members, each platform member comprising a radially outer platform surface and a radially inwardly extending attachment member; joining the compressor blade and the attachment members together; and clamping the compressor blade and the attachment members together using a retaining clip, wherein said retaining clip comprises a bias member coupled to a pair of legs extending orthogonally from said bias member so as to engage with circumferentially opposite faces of said attachment members, and wherein the attachment members are separated with respect to each other by a gap into which the radially inner root is received. 7. The method of claim 6, wherein each platform member comprises an axially extending slot in adjacent edges of the radially outer platform surfaces of the pair of platform members. 8. The method of claim 6, wherein joining the compressor blade and the attachment members together comprises using an adhesive applied to adjacent faces of the compressor blade and the attachment members. 9. The method of claim 6, wherein joining the compressor blade and the attachment members together comprises bonding the compressor blade and the attachment members together. 10. The method of claim 6, wherein clamping the compressor blade and the attachment members together using the bias member comprises attaching a respective retaining clip leg to each of the circumferentially opposing faces of the attachment members. 11. The method of claim 10, wherein attaching the retaining clip leg to circumferentially opposing faces of the attachment members comprises biasing the circumferentially opposing faces of the attachment members using the bias member coupled to said respective retaining clip legs. 12. The method of claim 10, wherein attaching the retaining clip leg to circumferentially opposing faces of the attachment members comprises adhering the retaining clip leg to the circumferentially opposing faces of the attachment members and the compressor blade. 13. A turbofan engine comprising: a core engine including a multistage compressor; a booster compressor powered by a power turbine driven by gas generated in said core engine; and a composite blade assembly comprising: a composite blade comprising a radially inner root, a radially outer tip, and an airfoil extending therebetween, said radially inner root comprising a dovetail; a first platform and a circumferentially adjacent second platform abutting said first platform at a platform joint, each of said first platform and said second platform comprising a radially outer surface and a radially inwardly extending attachment member, said platform joint comprising an axially extending slot extending through adjacent edges of said first platform and said second platform, said slot configured to receive said radially inner root, said radially inner root configured to by sandwiched between said attachment members; and a retaining clip formed of at least one of a metallic material and a composite material and configured to bias said attachment members towards each other, wherein said retaining clip comprises a bias member coupled to a pair of legs extending orthogonally from said bias member so as to engage with circumferentially opposite faces of said attachment members, and wherein the attachment members are separated with respect to each other by a gap into which the radially inner root is received. 14. The engine of claim 13, further comprising an adhesive system configured to join said radially inner root of said composite blade and said attachment members into a unitary structure. 15. The engine of claim 13, wherein said retaining clip is configured to exert a clamping force on said attachment members and said radially inner root of said composite blade. 16. The system of claim 13, wherein said retaining clip is configured to resist a separation of said composite blade and said composite blade assembly.