Turbine arrangement with improved sealing effect at a seal
View Patent ↗A turbine arrangement and a gas turbine engine including a rim seal is configured with two cavities. The main fluid path, the two cavities, and a disc space are furthermore separated from another, but still in fluid communication with another, via three annular seal passages. The turbine arrangement also includes a plurality of cooling fluid injectors arranged underneath a radially inner vane platform. The rim seal is configured for an upstream guide vane and a downstream rotor blade.
1. A turbine arrangement comprising:
a rotor that rotates about a rotor axis (x) and comprises a plurality of rotor blade segments extending radially outward, each rotor blade segment comprises an aerofoil and a radially inner blade platform;
a stator surrounding the rotor so as to form an annular flow path for a pressurised working fluid, the stator comprises a plurality of guide vane segments disposed adjacent the plurality of rotor blades, the plurality of guide vane segments extending radially inward, each guide vane segment comprising an aerofoil and a radially inner vane platform,
the stator further comprising a cylindrical stator wall coaxially aligned to the rotor axis (x) and an annular stator wall arranged on a mid section of an outer surface of the cylindrical stator wall;
a seal arrangement comprising a trailing edge of the inner vane platform, a leading edge of the inner blade platform and a first annular cavity and a second annular cavity, wherein
the first annular cavity is defined at least by the trailing edge of the inner vane platform, a first part of the cylindrical stator wall and the annular stator wall,
the second annular cavity is defined at least by the leading edge of the inner blade platform, a second part of the cylindrical stator wall and the annular stator wall,
the first annular cavity is in fluid communication with the annular flow path via a first annular seal passage,
the first annular cavity is separated from the second annular cavity via the annular stator wall,
the first annular cavity is in fluid communication with the second annular cavity via a second annular seal passage between a rim of the annular stator wall and the leading edge of the inner blade platform,
the second annular cavity is in fluid communication with a hollow space for providing sealing fluid via a third annular seal passage;
wherein the second annular cavity is defined furthermore by a substantially radially oriented ring surface of the rotor being substantially parallel to the annular stator wall; and
wherein the second annular cavity further comprises a substantially axially oriented flange of the rotor, wherein the third annular seal passage is formed by an axial edge of the cylindrical stator wall and the flange; and
wherein the flange of the rotor having a radial distance (D 1 ) to the rotor axis (x) greater than a radial distance (D 2 ) of the cylindrical stator wall to the rotor axis (x).
2. The turbine arrangement according to claim 1 ,
wherein the leading edge of the inner blade platform comprises a cylindrical rotor wall at its leading end.
3. The turbine arrangement according to claim 2 ,
wherein the cylindrical rotor wall has a substantially unmodified radial width over its axial length.
4. The turbine arrangement according to claim 2 ,
wherein the second annular seal passage is formed by a most leading end of the cylindrical rotor wall and the rim of the annular stator wall.
5. The turbine arrangement according to claim 1 ,
wherein the leading edge of the inner blade platform comprises a continuous convex curvature surface facing the flow path downstream of the cylindrical rotor wall.
6. The turbine arrangement according to claim 1 ,
wherein the annular stator wall is arranged perpendicularly to the cylindrical stator wall.
7. The turbine arrangement according to claim 1 ,
wherein the annular stator wall comprises a first section and a second section, wherein the first section is arranged perpendicularly to the cylindrical stator wall and the second section is inclined or curved in respect to the first section.
8. The turbine arrangement according to claim 1 ,
wherein the flange of the rotor comprises a radial distance (D 3 ) to the rotor axis (x) less than the radial distance (D 2 ) of the cylindrical stator wall to the rotor axis (x).
9. The turbine arrangement according to claim 1 ,
wherein the third annular seal passage comprises an axially oriented annular axial passage and a second radially oriented radial passage, the axial passage delimited by a shell surface of the cylindrical stator wall and a radially facing surface of a substantially axially oriented flange of the rotor or a first flange of the rotor, the radial passage delimited by a ring surface of the cylindrical stator wall and an axially facing surface of the rotor.
10. The turbine arrangement according to claim 2 ,
wherein the cylindrical rotor wall has a radially outwards facing concave surface with a width at its lip end greater than a width at another axial location of the cylindrical rotor wall.
11. The turbine arrangement according to claim 7 ,
wherein the second section is inclined or curved in direction of the first annular cavity.
12. A turbine arrangement comprising:
a rotor that rotates about a rotor axis (x) and comprises a plurality of rotor blade segments extending radially outward, each rotor blade segment comprises an aerofoil and a radially inner blade platform;
a stator surrounding the rotor so as to form an annular flow path for a pressurized working fluid, the stator comprises a plurality of guide vane segments disposed adjacent the plurality of rotor blades, the plurality of guide vane segments extending radially inward, each guide vane segment comprising an aerofoil and a radially inner vane platform,
the stator further comprising a cylindrical stator wall coaxially aligned to the rotor axis (x) and an annular stator wall arranged on a mid section of an outer surface of the cylindrical stator wall;
a seal arrangement comprising a trailing edge of the inner vane platform, a leading edge of the inner blade platform and a first annular cavity and a second annular cavity, wherein
the first annular cavity is defined at least by the trailing edge of the inner vane platform, a first part of the cylindrical stator wall and the annular stator wall,
the second annular cavity is defined at least by the leading edge of the inner blade platform, a second part of the cylindrical stator wall and the annular stator wall,
the first annular cavity is in fluid communication with the annular flow path via a first annular seal passage,
the first annular cavity is separated from the second annular cavity via the annular stator wall,
the first annular cavity is in fluid communication with the second annular cavity via a second annular seal passage between a rim of the annular stator wall and the leading edge of the inner blade platform,
the second annular cavity is in fluid communication with a hollow space for providing sealing fluid via a third annular seal passage; and
wherein the second annular cavity is defined furthermore by a substantially radially oriented ring surface of the rotor being substantially parallel to the annular stator wall; and
wherein the second annular cavity comprises a substantially axially oriented first flange of the rotor, the rotor further comprising a substantially axially oriented second flange, wherein
the first flange of the rotor comprises a radial distance (D 1 ) to the rotor axis (x) greater than a radial distance (D 2 ) of the cylindrical stator wall to the rotor axis (x),
the second flange of the rotor comprising a radial distance (D 3 ) to the rotor axis (x) less than the radial distance (D 2 ) of the cylindrical stator wall to the rotor axis (x),
the third annular seal passage is formed by an axial edge of the cylindrical stator wall penetrating into a space between the first flange and the second flange.