Gas turbine or compressor blade
View Patent ↗A gas turbine or compressor blade, includes a convex outer surface or suction side and a concave inner surface or pressure side, these sides being joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for the gases and terminating on a platform, one part of which includes a downstream fairing that includes at least one through-notch that extends substantially between a transverse line passing through the trailing edge and the downstream end of the fairing.
1. A gas turbine or compressor rotor blade, comprising a convex outer surface or suction side and a concave inner surface or pressure side, said suction and pressure sides being joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for gases and terminating on a platform, said platform being substantially rectangular and comprising an upstream fairing extending upstream from the leading edge and defining an upstream edge of the platform, and a downstream fairing extending downstream from the trailing edge and defining a downstream edge of the platform, said upstream and downstream edges of the platform being joined at their ends by two lateral edges of the platform, wherein said downstream fairing includes at least one through-notch that extends right through its thickness or dimension along the longitudinal axis of the blade, from the downstream edge of the platform towards a transverse line passing through the trailing edge, wherein the at least one notch is configured to divide the downstream fairing into two lateral portions.
2. A rotor blade according to claim 1 , wherein the at least one notch extends from the downstream edge of the platform as far as the transverse line passing through the trailing edge.
3. A rotor blade according to claim 1 , wherein the at least one notch has a substantially straight shape.
4. A rotor blade according to claim 1 , wherein said downstream fairing includes a plurality of through-notches and the notches diverge from one another towards the downstream edge of the platform.
5. A rotor blade according to claim 1 , wherein a notch closest to the trailing edge is approximately parallel to the downstream end of the suction side.
6. A rotor blade according to claim 1 , wherein the at least one notch is approximately parallel to the direction of gas flow in line with the notch.
7. A rotor blade according to claim 1 , wherein said downstream fairing includes a plurality of through-notches and the upstream end of each notch includes a cylindrical through-hole having a diameter greater than the width of said each notch.
8. A rotor blade according to claim 7 , wherein said holes are produced by machining.
9. A rotor blade according to claim 1 , wherein said downstream fairing includes a plurality of through-notches and the notches are produced by machining.
10. A turbomachine turbine comprising a plurality of blades according to claim 1 .
11. A turbomachine compressor comprising a plurality of blades according to claim 1 .
12. A turbomachine comprising a plurality of blades according to claim 1 .
13. A rotor blade according to claim 1 , wherein said downstream fairing includes a plurality of through-notches formed in the downstream edges of the platform.
14. A gas turbine or compressor blade, comprising a convex outer surface or suction side and a concave inner surface or pressure side, said suction and pressure sides being joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for gases and terminating on a platform, one part of which includes a fairing that extends towards the downstream end from the trailing edge, wherein said fairing includes at least one through-notch that extends right through its thickness or dimension along the longitudinal axis of the blade, the at last one notch extending from the downstream end of the fairing as far as a transverse line passing through the trailing edge.
15. A gas turbine or compressor blade, comprising a convex outer surface or suction side and a concave inner surface or pressure side, said suction and pressure sides being joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for gases and terminating on a platform, one part of which includes a fairing that extends towards the downstream end from the trailing edge, wherein said fairing includes a plurality of through-notches that extends right through its thickness or dimension along the longitudinal axis of the blade, from the downstream end of the fairing towards a transverse line passing through the trailing edge, and wherein the notches diverge from one another towards the downstream end.
16. A gas turbine or compressor blade, comprising a convex outer surface or suction side and a concave inner surface or pressure side, said suction and pressure sides being joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for gases and terminating on a platform, one part of which includes a fairing that extends towards the downstream end from the trailing edge, wherein said fairing includes at least one through-notch that extends right through its thickness or dimension along the longitudinal axis of the blade, from the downstream end of the fairing towards a transverse line passing through the trailing edge, and wherein a notch closest to the trailing edge is approximately parallel to the downstream end of the suction side.