A method of post processing a laser peened component to remove a laser remelt layer is proposed. The post processing includes a series of steps including grit blasting, chemical etching and mechanical finishing the component. This will ensure that the mechanical property (i.e., damage tolerance) benefit of laser peening is restored to the surface of the component.

The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mould in order to produce a blank (3); and b) machining the blank in order to produce the parts,
characterized in that the blank obtained by casting is a solid polyhedron with two generally trapezoidal opposing sides (30a, 30b), and the parts are machined in the blank.

The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mould in order to produce a blank (3); and b) machining the blank in order to produce the parts,
characterized in that the blank obtained by casting is a solid polyhedron with two generally trapezoidal opposing sides (30a, 30b), and the parts are machined in the blank.

The present invention relates to a method for machine finishing the shape of a blank casting for a multi-vane, in particular bi-vane, nozzle of a turbine engine, comprising a first vane and a second vane extending substantially in a radial direction between two walls that are radially inner and radially outer, respectively, the suction face of the first vane defining, together with the pressure face of the trailing edge of the second vane, a cross section of flow (SP), the method comprising measuring, by means of probing, the position of predefined points on said respectively radially inner and radially outer walls on the surface of the vanes and calculating the machining allowances (Δ1 and Δ2 respectively) on the first and second vanes with respect to the theoretical profile at said points, wherein the method comprises calculating said cross section of flow (SP) from the height of the duct between said radially inner and radially outer walls, and values of the machining allowances (Δ1 and Δ2), a correction of the machining allowance (Δ2) on one of the vanes being applied when the calculated value of the cross section of flow (SP) is outside predefined tolerances.

The present invention relates to a method for machine finishing the shape of a blank casting for a multi-vane, in particular bi-vane, nozzle of a turbine engine, comprising a first vane and a second vane extending substantially in a radial direction between two walls that are radially inner and radially outer, respectively, the suction face of the first vane defining, together with the pressure face of the trailing edge of the second vane, a cross section of flow (SP), the method comprising measuring, by means of probing, the position of predefined points on said respectively radially inner and radially outer walls on the surface of the vanes and calculating the machining allowances (Δ1 and Δ2 respectively) on the first and second vanes with respect to the theoretical profile at said points, wherein the method comprises calculating said cross section of flow (SP) from the height of the duct between said radially inner and radially outer walls, and values of the machining allowances (Δ1 and Δ2), a correction of the machining allowance (Δ2) on one of the vanes being applied when the calculated value of the cross section of flow (SP) is outside predefined tolerances.

A method of making a light weight component is provided. The method including the steps of: forming a metallic foam core into a desired configuration; inserting a pre-machined component into an opening in the metallic foam core; applying an external metallic shell to an exterior surface of the metallic foam core after it has been formed into the desired configuration and after the pre-machined component has been inserted into the metallic foam core; introducing an acid into an internal cavity defined by the external metallic shell; dissolving the metallic foam core; and removing the dissolved metallic foam core from the internal cavity, wherein the component and the external metallic shell are resistant to the acid.

A method of making a light weight component is provided. The method including the steps of: forming a metallic foam core into a desired configuration; inserting a pre-machined component into an opening in the metallic foam core; applying an external metallic shell to an exterior surface of the metallic foam core after it has been formed into the desired configuration and after the pre-machined component has been inserted into the metallic foam core; introducing an acid into an internal cavity defined by the external metallic shell; dissolving the metallic foam core; and removing the dissolved metallic foam core from the internal cavity, wherein the component and the external metallic shell are resistant to the acid.

Flutter-resistant transonic turbomachinery blades and methods for reducing transonic turbomachinery blade flutter are provided. The flutter-resistant transonic turbomachinery blade comprises a transonic turbomachinery blade that includes opposite pressure and suction surfaces extending longitudinally in span from a root to an opposite tip, and extending axially in chord between opposite leading and trailing edges. The flutter-resistant transonic turbomachinery blade includes a local positive camber in or proximate a predicted local region of supersonic flow over the transonic turbomachinery blade. The method comprises predicting a local region of supersonic flow over the transonic turbomachinery blade and inducing the local positive camber to the transonic turbomachinery blade in or proximate the predicted region of supersonic flow.

Flutter-resistant transonic turbomachinery blades and methods for reducing transonic turbomachinery blade flutter are provided. The flutter-resistant transonic turbomachinery blade comprises a transonic turbomachinery blade that includes opposite pressure and suction surfaces extending longitudinally in span from a root to an opposite tip, and extending axially in chord between opposite leading and trailing edges. The flutter-resistant transonic turbomachinery blade includes a local positive camber in or proximate a predicted local region of supersonic flow over the transonic turbomachinery blade. The method comprises predicting a local region of supersonic flow over the transonic turbomachinery blade and inducing the local positive camber to the transonic turbomachinery blade in or proximate the predicted region of supersonic flow.

A method of retrofitting vortex generators on a wind turbine blade is disclosed, the wind turbine blade being mounted on a wind turbine hub and extending in a longitudinal direction and having a tip end and a root end, the wind turbine blade further comprising a profiled contour including a pressure side and a suction side, as well as a leading edge and a trailing edge with a chord having a chord length extending there between, the profiled contour, when being impacted by an incident airflow, generating a lift. The method comprises identifying a separation line on the suction side of the wind turbine blade, and mounting one or more vortex panels including a first vortex panel comprising at least one vortex generator on the suction side of the wind turbine blade between the separation line and the leading edge of the wind turbine blade.