The present method for machining a part includes wire electro-discharge machining the part to create a recast layer, and then removing a zinc content of the recast layer without substantially altering the remainder of the initial composition make-up of the recast layer. The final composition make-up of the recast layer is substantially identical to the initial composition make-up except for the removed zinc content.

A blade for a wind turbine comprising a blade root portion is described. The blade root portion defines a mounting surface for coupling to a hub or extender of the wind turbine and comprises a plurality of first holes provided with an insert, the blade root portion further comprises a mounting flange arranged in the periphery of the mounting surface and provided with second holes, wherein the inserts comprise a first end embedded in the blade root portion and a second end opposite to the first end, the second end protruding beyond the mounting surface of the blade root portion, and wherein the second ends are fitted in the second holes of the mounting flange and the mounting flange is attached to the blade by means of the inserts. Furthermore, a wind turbine rotor comprising such a blade is described. Methods of manufacturing half a wind turbine blade and a whole wind turbine blade are also described.

Described is a gas turbine engine component (100), comprising a shell having an internal cavity for receiving a multi-part insert; a multi-part insert located within the cavity, wherein the multi-part insert comprises multiple separate parts assembled in an abutting relation with one another within the cavity to provide the multi-part insert; wherein the assembled insert includes at least one retention part, the retention part engaging with a wall of the cavity and at least one other insert part so as to retain the assembled insert within the cavity.

An array of flow-directing elements for a compressor of a gas turbine including at least one first flow-directing element and at least one second flow-directing element different from the first flow-directing element; the flow-directing elements each having a leading edge facing the gas turbine inlet, a trailing edge, a pressure side connecting them and located ahead in the direction of rotation, a suction side located opposite thereof, as well as successive chords along a stacking axis; the flow-directing elements each extending between an airfoil root proximate to the rotor and an airfoil tip remote from the rotor. The trailing edge of the first flow-directing element is, at least in a portion thereof, axially offset from the trailing edge of the second flow-directing element in a direction toward the leading edge at least in a half proximate to the airfoil tip.

Provided is a method of manufacturing an impeller assembly, the method including providing an impeller including: a rotary shaft; a base portion radially extending outward from the rotary shaft; and a plurality of blades extending radially outward from the rotary shaft and disposed on the base portion, each of the plurality of blades provided apart from one another in a circumferential direction around the rotary shaft; providing a mold in an area between the plurality of blades; and forming a shroud covering upper portions of the plurality of blades and an upper portion of the mold, wherein the forming the shroud comprises applying a melted metal on the upper portions of the plurality of blades and the upper portion of the mold.

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.

A wind turbine blade includes a blade body whose chord length increases from a blade tip toward a blade root. The blade body includes a blade tip region located near the blade tip and whose chord length increases gradually toward the blade root, the blade tip region having a substantially constant first design lift coefficient, a maximum-chord-length position located near the blade root and having a maximum chord length, the maximum-chord-length position having a second design lift coefficient higher than the first design lift coefficient, and a transition region located between the blade tip region and the maximum-chord-length position. The transition region has a design lift coefficient increasing gradually from the first design lift coefficient to the second design lift coefficient in a direction from the blade tip toward the blade root.

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.

An axial impeller has blades formed from sheet metal blanks that are configured from taking a desired impeller blade and mathematically “unwinding” the blade to its flat counterpart. Preferably, the impeller blade is formed from a single rolling operation. The result of a thin, elongate blade, preferably having a trailing edge that defines a helix with rearwardly skewed, forwardly raked blades, provides an efficient impeller having good anti-ragging properties.

A hybrid turbine blade having a box beam assembly structure and method of designing such a hybrid turbine blade are disclosed. The box beam assembly provides the primary structure for supporting loads on the blade, and comprises oppositely positioned spar caps joined by oppositely positioned shear webs. For a portion of the blade, the box beam assembly further comprises a root buildup. In one embodiment, the shear webs comprise foam core sandwiched between two biaxial fiber-reinforced plastic laminates (FRP), the spar caps comprise uniaxial FRP laminates, and the root buildup comprises triaxial FRP laminates. The blades are designed using a novel inside-out method, wherein the box beam is first designed to support expected loads, and an aerodynamic surface is then designed to be supported by the box beam. The blade may be constructed in segments that are joined with connectors that engage the box beam structure.