Blade assembly in a combustion turbo-machine providing reduced concentration of mechanical stress and a seal between adjacent assemblies
View Patent ↗A blade assembly 100 (FIG. 5 ) configuration that includes a means for distributing mechanical stress (e.g., a stress dissipater 54 ) is provided. The stress dissipater is configured to reduce the concentration of a peak mechanical stress without compromising the effectiveness of a seal between adjacent rotating blade assemblies.
1. A blade assembly in a turbo-machine, the assembly comprising:
a blade comprising a platform with a surface;
a groove formed in said surface, the groove configured to linearly extend along a groove axis in a direction generally along an axis of rotation of the turbo-machine, the groove positioned to extend between adjacent blade assemblies of a common row of blades of the turbo-machine, the groove adapted to receive a cylindrical seal pin having a circular cross-section along the groove axis, the seal pin further having at least one end proximate a corresponding end of the groove, the seal pin operable to make sealing contact with a corresponding surface of an adjacent blade assembly to avoid leakage of a fluid through a gap there between, wherein the end of the groove comprises a first portion comprising a blocking surface generally normal to the axis of rotation, the blocking surface adjacent to the end of the seal pin, and the end of the groove further comprises a second portion comprising a lengthwise extension of the groove beyond the blocking surface; and
a dam disposed between the groove end and the lengthwise extension of the groove, the dam configured to radially extend from a bottom location at the end of the groove, the dam positioned substantially normal relative to the groove axis into a portion of the lengthwise extension of the groove, the dam constructed as an integral structure of the blade platform.
2. The blade assembly of claim 1 , wherein said first portion of the end of the groove comprises a radially inner portion with respect to a rotor axis, and said second portion of the end of the groove comprises a radially outer portion with respect to the first portion.
3. The blade assembly of claim 1 , wherein said lengthwise extension of the groove comprises a fillet configured to extend over a segment encompassing at least half a width of the groove.
4. A blade in a turbo-machine comprising:
a groove formed in a platform section of the blade, the groove configured to linearly extend along a groove axis in a direction generally along an axis of rotation of the turbo-machine, the groove positioned to extend between adjacent blade assemblies of a common row of blades of the turbo-machine, the groove adapted to receive a cylindrical seal pin having a circular cross-section along the groove axis, the seal pin operable to make a sealing contact with an adjacent blade platform to avoid leakage of a fluid through a gap there between, wherein at least one end of the groove comprises a first portion comprising a mechanical stress dissipater having a surface configured to distribute mechanical stresses there through, and wherein the end of the groove further comprises a second portion comprising a blocking structure having a fluid-deflecting surface positioned to impede a flow of fluid around the end of the seal pin, wherein the fluid-deflecting surface is positioned generally normal to the axis of rotation of the turbo-machine, and wherein the surface for distributing mechanical stress is arranged to provide a transition from a surface disposed in the direction generally along the axis of rotation of the turbo-machine to a surface generally normal to the axis of rotation of the turbo-machine.
5. The blade assembly of claim 4 , wherein said first portion of the end of the groove comprises a radially inner portion with respect to a rotor axis, and said second portion of the end of the groove comprises a radially outer portion with respect to the first portion.
6. The blade assembly of claim 4 wherein the surface for distributing mechanical stress comprises an elliptically-shaped structure.
7. The blade assembly of claim 4 wherein the surface for distributing mechanical stress is configured to extend over a segment encompassing at least half a width of the groove.
8. A blade group in a turbo-machine comprising:
a first blade comprising a first platform with a first surface;
a second blade comprising a second platform with a second surface located adjacent said first surface and forming a gap there between;
a groove formed in said first surface, the groove comprising a length and width in a plane of the first surface, the groove configured to linearly extend along a groove axis in a direction generally along an axis of rotation of the turbo-machine;
a cylindrical seal pin disposed in the groove, said seal pin having a circular cross-section along the groove axis, the seal pin having a first end proximate a first end of the groove and a second end proximate a second end of the groove, said seal pin operable to make sealing contact with the second surface to avoid leakage of a fluid through the gap, wherein each end of the groove comprises a first portion comprising a blocking surface generally normal to the groove axis, the blocking surface adjacent to each respective end of the seal pin, and each end of the groove further comprises a second portion comprising a lengthwise extension of the groove beyond the blocking surface; and
a dam disposed between the groove and the lengthwise extension of the groove, the dam configured to radially extend from a bottom location at the end of the groove, the dam positioned substantially normal relative to the groove axis into a portion of the lengthwise extension of the groove, the dam constructed as an integral structure of the blade platform.
9. The blade group of claim 8 , wherein said first portion of the end of the groove comprises a radially inner portion with respect to a rotor axis, and said second portion of the end of the groove comprises a radially outer portion with respect to the first portion.
10. The blade group of claim 8 , wherein said lengthwise extension of the groove comprises a fillet configured to extend over a segment encompassing at least half a width of the groove.
11. A blade assembly in a turbo-machine comprising:
a blade having a platform section; and
at least one groove formed in a surface of said platform section, the groove configured to linearly extend along a groove axis in a direction generally along an axis of rotation of the turbo-machine, the groove positioned to extend between adjacent blade assemblies in a common row of blades of the turbo-machine, the groove adapted to receive a cylindrical seal pin having a circular cross-section along the groove axis, the seal pin having at least one end proximate a corresponding end of the groove, said seal pin operable to make sealing contact with an adjacent platform section to avoid leakage of a fluid through a gap there between, wherein a first portion of said end of the groove comprises a mechanical stress dissipater comprising a curved surface for dissipating a peak mechanical stress there through by a pre-determined factor wherein a second portion of said at least one end of the groove comprises a fluid-deflecting surface positioned to impede the flow of fluid around the end of the seal pin, wherein the fluid-deflecting surface is positioned generally normal to the axis of rotation of turbo-machine, and wherein the curved surface is arranged to provide a transition from a surface disposed in the direction generally along the axis of rotation of the turbo-machine to a surface generally normal to the axis of rotation of the turbo-machine.
12. The blade assembly of claim 11 wherein the predetermined factor ranges from about 0.4 to about 0.8.