A blade root shim comprises a base, a suction side shim wall, a pressure side shim wall, and a contact relief region. The base extends longitudinally between a leading shim end and a trailing shim end. The suction side shim wall extends along the base and corresponds to a suction side blade root bea
A blade root shim comprises a base, a suction side shim wall, a pressure side shim wall, and a contact relief region. The base extends longitudinally between a leading shim end and a trailing shim end. The suction side shim wall extends along the base and corresponds to a suction side blade root bearing surface. The pressure side shim wall, spaced circumferentially apart from the suction shim wall, corresponds to a pressure side blade bearing surface. The contact relief region is formed into an upper wall portion of either the suction side shim wall or the pressure side shim wall.
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1. A blade root shim comprising a base extending longitudinally between a leading shim end and trailing shim end;a suction side shim wall extending along the base, the suction side shim wall corresponding to a suction side blade root bearing surface;a pressure side shim wall spaced circumferentially
1. A blade root shim comprising a base extending longitudinally between a leading shim end and trailing shim end;a suction side shim wall extending along the base, the suction side shim wall corresponding to a suction side blade root bearing surface;a pressure side shim wall spaced circumferentially apart from the suction shim wall, the pressure side shim wall corresponding to a pressure side blade bearing surface; anda contact relief region formed into an upper wall portion of either the suction side shim wall or the pressure side shim wall;wherein at least one of the pressure side shim wall and the suction side shim wall includes a lower wall portion curved upwardly and outwardly from the base, and the upper wall portion is curved upwardly and inwardly from the lower wall portion; andwherein the contact relief region is formed into the upper wall portion of the at least one of the leading shim end and the trailing shim end. 2. The shim of claim 1, comprising a plurality of contact relief regions, each contact relief region formed into the upper wall portion of at least one of the pressure side shim wall, and the suction side shim wall. 3. The shim of claim 1, wherein the base is curved transversely to the longitudinal direction between the suction side shim wall and pressure side shim wall. 4. The shim of claim 1, wherein the contact relief region includes at least one cutout formed into both the upper wall portion and the lower wall portion. 5. The shim of claim 1, wherein the contact relief region includes at least one cutout having a longitudinal dimension of at least 5% of a longitudinal distance between the leading shim end and the trailing shim end. 6. The shim of claim 1, wherein the pressure side shim wall and the suction side shim wall are arranged at a shim broach angle of at least 5°. 7. A blade assembly comprising: a blade having an airfoil section and a root section; anda shim disposed over the blade root section, the shim comprising a base, suction side and pressure side shim walls extending from the base, a leading shim end, a trailing shim end, and a contact relief region aligned with a portion of the blade root section;wherein at least one of the pressure and suction side shim walls includes a lower wall portion curved upwardly and outwardly from the base, and the upper wall portion is curved upwardly and inwardly from the lower wall portion; andwherein the contact relief region is formed into the upper wall portion of at least one of the leading shim end and the trailing shim end. 8. The blade assembly of claim 7, wherein the contact relief region is aligned with a high load portion of the blade root section. 9. The blade assembly of claim 8, wherein the blade airfoil section and root section each comprise a ceramic matrix composite (CMC) substrate. 10. The blade assembly of claim 9, wherein the CMC substrate comprises woven silicon carbide fibers coated with boronitride particles and retained in a silicon carbide matrix. 11. The blade assembly of claim 9, further comprising at least one protective coating layer disposed over the root section comprising the CMC substrate. 12. The blade assembly of claim 7, wherein the shim comprises a resilient metal substrate with a low friction coating layer disposed on at least one shim surface. 13. The blade assembly of claim 7, wherein the blade airfoil section and root section each comprise a organic matrix composite (OMC) substrate. 14. A gas turbine rotor assembly comprising: a plurality of rotor blades each including an airfoil section, and a root section;a rotor disc including a plurality of circumferentially distributed blade retention slots corresponding to the plurality of rotor blades, each retention slot having at least one bearing surface mating with a bearing surface disposed on the blade root sections; anda blade root shim disposed between one of the plurality of rotor blades and a corresponding blade retention slot, the blade root shim including a contact relief region formed into at least an upper portion of the blade root shim and aligned with a portion of the blade root section;wherein at least one of a pressure side shim wall and a suction side shim wall includes a lower wall portion curved upwardly and outwardly from a base of the shim, and an upper wall portion which is curved upwardly and inwardly from the lower wall portion; andwherein the contact relief region is formed into the upper wall portion of at least one of a leading shim end and a trailing shim end. 15. The rotor assembly of claim 14, wherein the contact relief region is aligned with a high load portion of the blade root section. 16. The rotor assembly of claim 14, further comprising a retention ring secured around an longitudinal face of the rotor disc, and including at least one portion disposed immediately adjacent a longitudinal bearing face of the at least one blade root portion. 17. The rotor assembly of claim 14, wherein the plurality of blades and the corresponding plurality of radial retention slots are disposed at a broach angle of at least 5° relative to an axial centerline of the rotor assembly. 18. A gas turbine engine comprising a rotor assembly as recited in claim 14, wherein the rotor assembly is disposed in a fan section of the gas turbine engine. 19. A gas turbine engine comprising a plurality of rotor assemblies as recited in claim 14, wherein at least one of the plurality of rotor assemblies is disposed in a turbine section of the gas turbine engine. 20. A method of assembling a turbine rotor assembly, the method comprising: placing a blade root shim having at least one contact relief region over root section of a ceramic matrix composite (CMC) rotor blade, the at least one contact relief region formed into at least an upper portion of the blade root shim;inserting the shim and the rotor blade root section into a rotor disc radial retention slot; andsecuring the shim and the rotor blade root section into the retention slot with the at least one contact relief region aligned with a corresponding at least one location of the blade root section;wherein at least one of a pressure side shim wall and a suction side shim wall includes a lower wall portion curved upwardly and outwardly from the base, and an upper wall portion which is curved upwardly and inwardly from the lower wall portion; andwherein the at least one contact relief region is formed into the upper wall portion of at least one of a leading shim end and a trailing shim end. 21. The method of claim 20, wherein the at least one high load portion of the root section is located proximate an intersection of adjacent root bearing surfaces. 22. The method of claim 20, wherein the blade root section is inserted at a broach angle of at least 5° relative to an axial orientation of the rotor disc.
Garin, Fabrice Marcel Noel; Gendraud, Alain Dominique; Lequitte, Thierry; Lunel, Romain Nicolas, Interface element between a blade root and a blade root housing of a turbine disc, and turbine rotor comprising an interface element.
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