A gas turbine engine includes a central body support that provides an inner annular wall for a core flow path. The central body support includes a first mount feature. A geared architecture interconnects a spool and a fan rotatable about an axis. A flex support interconnects the geared architecture
A gas turbine engine includes a central body support that provides an inner annular wall for a core flow path. The central body support includes a first mount feature. A geared architecture interconnects a spool and a fan rotatable about an axis. A flex support interconnects the geared architecture to the central body support. The flex support includes a second mount feature that cooperates with the first mount feature for transferring torque there between. A method of disassembling a front architecture of a gas turbine engine includes the steps of accessing forward-facing fasteners that secure a central body support to a flex support, wherein the flex support includes a geared architecture supported thereon, removing the fasteners, and decoupling first and second mount features respectively provided on the central body support and the flex support.
대표청구항▼
1. A gas turbine engine comprising: a central body support providing an inner annular wall for a core flow path, the central body support including a first mount feature;a geared architecture interconnecting a spool and a fan rotatable about an axis; anda flex support interconnecting the geared arch
1. A gas turbine engine comprising: a central body support providing an inner annular wall for a core flow path, the central body support including a first mount feature;a geared architecture interconnecting a spool and a fan rotatable about an axis; anda flex support interconnecting the geared architecture to the central body support, the flex support including a second mount feature operatively coupled to the first mount feature and configured to transfer torque there between. 2. The gas turbine engine according to claim 1, wherein the central body support includes circumferentially spaced apart vanes radially extending between and interconnecting the inner annular wall and an outer annular wall. 3. The gas turbine engine according to claim 2, wherein the first mount feature includes tooth groups including multiple teeth, the tooth groups circumferentially spaced apart from one another with untoothed regions arranged between the tooth groups. 4. The gas turbine engine according to claim 3, wherein the vanes are circumferentially aligned with the untoothed regions. 5. The gas turbine engine according to claim 3, wherein the second mount feature includes corresponding tooth groups configured to circumferentially align and mate with the tooth groups of the first mount feature, and corresponding untoothed regions arranged between the tooth groups of the corresponding tooth groups, wherein the untoothed region is provided by a stiffening rail protruding axially inward from a central body section providing the inner annular wall. 6. The gas turbine engine according to claim 3, wherein the central body support includes multiple fastener bosses circumferentially spaced from one another, the fastener bosses aligned with the tooth groups. 7. The gas turbine engine according to claim 3, wherein the untoothed region is provided by a stiffening rail protruding radially inward from a central body section providing the inner annular wall. 8. The gas turbine engine according to claim 7, wherein the central body support includes an annular recess and an annular pocket axially spaced apart from one another to provide first and second lateral sides on the stiffening rail. 9. The gas turbine engine according to claim 7, wherein the tooth groups include internal teeth having roots provided at a first tooth radius and extending radially inward to crests provided at a second tooth radius, the stiffening rail extending radially inward to a rail radius that is less than the first tooth radius. 10. The gas turbine engine according to claim 1, wherein the geared architecture includes an epicyclic gear train having a sun gear, a ring gear, and intermediate gears arranged circumferentially about the sun gear and intermeshing with the sun gear and the ring gear. 11. The gas turbine engine according to claim 10, wherein the intermediate gears are star gears grounded to the flex support against rotation about the axis, the sun gear is supported by the spool, and the ring gear is interconnected to the fan. 12. The gas turbine engine according to claim 1, wherein the central body support includes a first inner face arranged near the first spline, and the flex support includes a first outer face arranged in an interference fit relationship with the first inner face to radially locate the flex support relative to the central body support. 13. The gas turbine engine according to claim 12, wherein the central body support includes a second inner face, and the flex support includes a second outer face arranged in an interference fit relationship with the second inner face, the first inner and outer faces arranged forward of the first mount feature and the second inner and outer faces arranged aft of the first mount feature, the second outer face being positioned radially inward relative to the first outer face. 14. The gas turbine engine according to claim 1, comprising fasteners securing the flex support to the central body support, the fasteners including heads facing forward. 15. The gas turbine engine according to claim 14, wherein the central body support includes circumferentially spaced fastener bosses, and the flex support includes a radially outward extending fastener flange abutting the fastener bosses to axially locate the flex support relative to the central body support. 16. The gas turbine engine according to claim 15, wherein the fastener flange includes apertures arranged circumferentially spaced from one another and receiving the fasteners. 17. The gas turbine engine according to claim 1, wherein the first and second mount features are axially aligned with one another. 18. The gas turbine engine according to claim 17, wherein the first and second mount features are circumferentially adjacent to one another. 19. The gas turbine engine according to claim 17, wherein the first mount feature is arranged radially outward of the second mount feature. 20. A method of disassembling a front architecture of a gas turbine engine, comprising the steps of: accessing forward-facing fasteners that secure a central body support to a flex support, wherein the flex support includes a geared architecture supported thereon;removing the fasteners; anddecoupling first and second mount features respectively provided on the central body support and the flex support. 21. The method according to claim 20, wherein the accessing step includes the step of detaching a fan module from a fan shaft bearing support, with the fan shaft bearing support remaining secured to the central body support. 22. The method according to claim 21, wherein the accessing step includes the step of detaching the fan shaft bearing support from the central support body without removing the geared architecture. 23. The method according to claim 22, wherein the decoupling step includes removing a geared architecture module that includes the geared architecture and the flex support, wherein the decoupling step leaves undisturbed a bearing supporting a front of a spool operatively connectable with the geared architecture. 24. The method according to claim 20, wherein the first and second mount features are axially aligned with one another during the accessing step. 25. The method according to claim 24, wherein the first and second mount features are circumferentially adjacent to one another during the accessing step. 26. The method according to claim 24, wherein the first mount feature is arranged radially outward of the second mount feature during the accessing step.
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이 특허에 인용된 특허 (11)
Amin Mohamed-Samy A. (Mississauga CAX) Matthews Anthony J. (Georgetown CAX), Bearing support housing.
Kervistin Robert (Le Mee Sur Seine FRX) Lardellier Alain M. J. (Melun FRX) Mazeaud Georges (Yerres FRX) Crozet Francois E. G. (Yerres FRX), Means for controlling clearance in an intershaft bearing journal of a multi-spool gas turbine.
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