Vane segment with ribs
There is disclosed a vane segment for a gas turbine engine. The vane segment includes vanes extending radially from inner ends to outer ends. The vanes have leading edges, trailing edges, and chords extending from the leading edges to the trailing edges. A platform circumferentially extends around the central axis. The platform has an inner face facing the central axis and an opposed outer face. The inner face of the platform is connected to the outer ends of the vanes. Ribs protrude away from the outer face and have lengths extending along the outer face.
1. A vane segment for a gas turbine engine, the vane segment comprising:
vanes extending radially relative to a central axis, from inner ends to outer ends relative to the central axis, the vanes having leading edges, trailing edges, and chords extending from the leading edges to the trailing edges, the vanes being non-rotating relative to the central axis;
a platform extending circumferentially relative to the central axis, the platform having a radially inner face and an opposed outer face, the inner face of the platform connected to the outer ends of the vanes; and
ribs protruding away from the outer face and having lengths extending along the outer face, at least one of the ribs intersecting a corresponding one of projections of the chords, the at least one of the ribs extending at least partially axially relative to the central axis, one of two adjacent ones of the projections of the chords intersected by a respective one of the ribs adjacent a leading edge of the one of two adjacent ones of the projections of the chord, the other of the two adjacent ones of the projections of the chords intersected by the respective one of the ribs adjacent a trailing edge of the other of the two adjacent ones of the projections of the chords.
2. The vane segment of claim 1 , wherein the at least one of the ribs perpendicularly intersects the corresponding one of the projections of the chords.
3. The vane segment of claim 1 , wherein each of the ribs intersects a respective one of the projections of the chords.
4. The vane segment of claim 1 , wherein each of the ribs intersects two adjacent ones of the projections of the chords.
5. The vane segment of claim 1 , further comprising stiffeners protruding away from the outer face and having lengths extending along the outer face, the lengths of the stiffeners intersecting the lengths of the ribs.
6. The vane segment of claim 5 , wherein at least one of the lengths of the stiffeners is free of intersection with the projections of the chords.
7. The vane segment of claim 1 , further comprising stiffeners protruding away from the outer face and having lengths extending along the outer face, the stiffeners perpendicularly intersecting the ribs.
8. The vane segment of claim 1 , wherein the platform includes a fore rail and an aft rail, defined axially relative to the central axis, configured to be secured to a casing of the gas turbine engine, the outer face extending between the fore rail and the aft rail, the vane segment further comprising fore axial ribs and aft axial ribs, each of the ribs extending from a respective one of the fore axial ribs to a respective one of the aft axial ribs.
9. A gas turbine engine comprising a turbine section, the turbine section including stators and rotors disposed in alternation along a central axis, at least one of the stators having vane segments circumferentially distributed around the central axis, the vane segments having vanes extending radially from inner ends to outer ends relative to the central axis, the vanes having leading edges, trailing edges, and chords extending from the leading edges to the trailing edges, a platform circumferentially extending around the central axis and being secured to a casing, the platform having an inner face facing the central axis and an opposed outer face, the vanes protruding radially inwardly from the inner face of the platform, and ribs protruding away from the outer face and having lengths extending along the outer face, at least one of the lengths intersecting a corresponding one of projections of the chords, the at least one of the ribs extending at least partially axially relative to the central axis, stiffeners protruding away from the outer face and having lengths extending along the outer face, the lengths of the stiffeners being oriented parallel to the projection of the chords, the lengths of the stiffeners free of intersection with the projections of the chords.
10. The gas turbine engine of claim 9 , wherein the at least one of the lengths perpendicularly intersects the corresponding one of the projections of the chords.
11. The gas turbine engine of claim 9 , wherein each of the lengths of the ribs intersects a respective one of the projections of the chords.
12. The gas turbine engine of claim 9 , wherein each of the lengths of the ribs intersects two adjacent ones of the projections of the chords.
13. The gas turbine engine of claim 9 , wherein one of two adjacent ones of the projections of the chords is intersected by a respective one of the lengths adjacent a leading edge of the one of the two adjacent ones of the projections of the chords, the other of the two adjacent ones of the projections of the chords is intersected by the respective one of the lengths adjacent a trailing edge of the other of the two adjacent ones of the projections of the chords.
14. The gas turbine engine of claim 9 , wherein the stiffeners perpendicularly intersect the ribs.
15. The gas turbine engine of claim 9 , wherein the platform includes a fore rail and an aft rail secured to the casing of the gas turbine engine, the outer face extending between the fore rail and the aft rail, the vane segment further comprising fore axial ribs and aft axial ribs, each of the ribs extending from a respective one of the fore axial ribs to a respective one of the aft axial ribs.
16. A vane segment for a gas turbine engine, the vane segment comprising:
vanes extending radially relative to a central axis, from inner ends to outer ends, the vanes having leading edges, trailing edges, and chords extending from the leading edges to the trailing edges;
a platform extending circumferentially relative to the central axis, the platform having a radially inner face and an opposed outer face, the inner face of the platform connected to the outer ends of the vanes, the platform including a fore rail and an aft rail, defined axially relative to the central axis, securable to a casing of the gas turbine engine, the outer face extending between the fore rail and the aft rail; and
ribs having a thickness protruding away from the outer face and lengths extending along the outer face, at least one of the ribs being transverse to a corresponding one of projections of the chords, the at least one of the ribs extending at least partially axially relative to the central axis, the vane segment having fore axial ribs and aft axial ribs, each of the ribs extending from a respective one of the fore axial ribs to a respective one of the aft axial ribs.
17. The vane segment of claim 16 , wherein the at least one of the ribs perpendicularly intersects the corresponding one of the projections of the chords.
18. The vane segment of claim 16 , further comprising stiffeners protruding away from the outer face and having lengths extending along the outer face, the lengths of the stiffeners intersecting the lengths of the ribs.
19. The vane segment of claim 18 , wherein at least one of the lengths of the stiffeners is free of intersection with the projections of the chords.
20. The vane segment of claim 16 , wherein one of two adjacent ones of the projections of the chords is intersected by a respective one of the ribs adjacent a leading edge of the one of the two adjacent ones of the projections of the chords, the other of the two adjacent ones of the projections of the chords intersected by the respective one of the ribs adjacent a trailing edge of the other of the two adjacent ones of the projections of the chords.