Gas turbine or compressor blade
AssigneeSnecma
InventorsEric Stephen Bil, Nicolas Hervy, Thomas Schlesinger
Life of this patent
Estimating the term…
Abstract
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.
Claims16
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.
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.
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.
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.
Dependencies are inferred from the claim text.