Wall of turbo machine and turbo machine
The invention relates to wall of a turbo machine having a cascade of blades. The wall includes: a first platform facing a first passage between blades in the cascade of blades; and a second platform facing a second passage between adjacent cascade of blades on an upstream side and cascade of blades on a downstream side, and having a circumferential outline having a distribution of radial positions. According to the invention, loss due to disturbance of flow through the gap of axially adjacent walls can be reduced.
1. A wall of a turbo machine having a cascade of blades comprising:
a first platform facing a first passage between blades in the cascade of blades; and
a second platform facing a second passage between another adjacent cascade of blades on an upstream side and said cascade of blades on a downstream side, and having a circumferential outline having a distribution of radial positions, wherein
the circumferential outline of said second platform has a minimum radius position near the circumferential center between said blades,
said minimum radius position is on a front surface side or a rear surface side of said blades with respect to the circumferential center between said blades, and
the circumferential outline has a curvature that is defined using one of a sine curve in the circumferential direction and a cosine curve in the circumferential direction.
2. A wall of a turbo machine according to claim 1 , wherein the circumferential outline of said second platform includes a convex portion adjacent to a front surface of said blades, and a convex portion adjacent to a rear surface of said blades.
3. A wall of a turbo machine having a cascade of blades comprising:
a first platform having a first radial face arranged between a leading edge and a trailing edge of the blades in the cascade of blades; and
a second platform having a second radial face arranged between said blades of said cascade of blades and blades of another adjacent cascade of blades on an upstream side, and that cooperates with said first radial face of said first platform, and in which a circumferential shape of said second radial face has a distribution of radial positions, wherein
the circumferential shape of said second radial face has a minimum radius position near the circumferential center between said blades,
said minimum radius position is on a front surface side or a rear surface side of said blades with respect to the circumferential center between said blades, and
the circumferential outline has a curvature that is defined using one of a sine curve in the circumferential direction and a cosine curve in the circumferential direction.
4. A wall of a turbo machine according to claim 3 , wherein said second platform further has an outside face that cooperates with said second radial face, and faces in the axial direction.
5. A turbo machine comprising:
a stator blade,
a rotor blade,
a wall on a root side of said stator blade,
a wall on a tip side of said stator blade,
a wall on a root side of said rotor blade,
a wall on a tip side of said rotor blade,
and at least one of said walls has a wall according to claim 1 .
6. A turbo machine comprising:
a stator blade,
a rotor blade,
a first wall on a tip side of said stator blade,
a second wall on a tip side of said rotor blade,
a third wall on a root side of said stator blade,
a fourth wall on a root side of said rotor blade,
an extension provided on said second wall, extending from a leading edge of said rotor blade towards a second clearance space between adjacent third wall and second wall, and having a radial depression, wherein
a circumferential center of the depression is to the rear surface side of the blades or the front surface side of the blades with respect to the circumferential center between blades, and
a circumferential outline of the extension has a curvature that is defined using one of a sine curve in the circumferential direction and a cosine curve in the circumferential direction.
7. A turbo machine comprising:
a stator blade,
a rotor blade,
a first wall on a tip side of said stator blade,
a second wall on a tip side of said rotor blade,
a third wall on a root side of said stator blade,
a fourth wall on a root side of said rotor blade,
an extension provided on said fourth wall, extending from a leading edge of said rotor blade towards a first clearance space between adjacent first wall and fourth wall, and having a radial depression, wherein
a circumferential center of the depression is to the rear surface side of the blades or the front surface side of the blades with respect to the circumferential center between blades, and
a circumferential outline of the extension has a curvature that is defined using one of a sine curve in the circumferential direction and a cosine curve in the circumferential direction.
8. A turbo machine according to claim 6 , wherein the radial depression has one depression component for each blade pitch.
9. A turbo machine according to claim 8 , wherein part of said depression component faces a first clearance space or said second clearance space.
10. A turbo machine comprising:
a stator blade,
a rotor blade,
a first wall on a tip side of said stator blade,
a second wall on a tip side of said rotor blade,
a third wall on a root side of said stator blade,
a fourth wall on a root side of said rotor blade;
an extension provided on said second wall, extending from a leading edge of said rotor blade towards a second clearance space between adjacent third wall and second wall, and having a depression that suppresses loss of flow between said second clearance space and a passage between blades, wherein
a circumferential center of the depression is to the rear surface side of the blades or the front surface side of the blades with respect to the circumferential center between blades, and
a circumferential outline of the extension has a curvature that is defined using one of a sine curve in the circumferential direction and a cosine curve in the circumferential direction.
11. A turbo machine comprising:
a stator blade,
a rotor blade,
a first wall on a tip side of said stator blade,
a second wall on a tip side of said rotor blade,
a third wall on a root side of said stator blade,
a fourth wall on a root side of said rotor blade;
an extension provided on said fourth wall, extending from a leading edge of said rotor blade towards a first clearance space between adjacent first wall and fourth wall, and having a depression that suppresses loss of flow between said first clearance space and a passage between blades, wherein
a circumferential center of the depression is to the rear surface side of the blades or the front surface side of the blades with respect to the circumferential center between blades, and
a circumferential outline of the extension has a curvature that is defined using one of a sine curve in the circumferential direction and a cosine curve in the circumferential direction.
12. A wall of a turbo machine according to claim 1 , wherein said distribution of radial positions has periodicity, with one period corresponding to one pitch of said blades.
13. A wall of a turbo machine according to claim 1 , wherein a depression corresponding to said circumferential outline, and extending along at least the axial direction of said cascade of blades is provided in said second platform.
14. A wall of turbo machine according to claim 13 , wherein said depression reaches to the axial outer edge in said second platform.
15. The turbo machine according to claim 7 , wherein the radial depression has one depression component for each blade pitch.