The disclosed subject matter provides a system and method for facilitating bonding of various turbine blade components, including trailing edge inserts, or flatbacks, to the trailing edge of a wind turbine blade. The system disclosed herein ensures a consistent force is applied from root to top thereby preventing defects, e.g. paste voids, from forming. Additionally, a consistent bonding gap can be achieved due to the consistent application of force from the root to tip of the blade.

The disclosed subject matter provides a system and method for facilitating bonding of various turbine blade components, including trailing edge inserts, or flatbacks, to the trailing edge of a wind turbine blade. The system disclosed herein ensures a consistent force is applied from root to top thereby preventing defects, e.g. paste voids, from forming. Additionally, a consistent bonding gap can be achieved due to the consistent application of force from the root to tip of the blade.

A turbine blade includes an airfoil that extends radially between a root end and a tip end, a platform coupled to the root end, and a shank that extends radially inwardly from the platform. The shank includes a cover plate. The cover plate includes an outer surface, an opposite inner surface, and a contoured face that at least partially defines a damper pin slot. The contoured face extends from the outer surface to a first blend edge. The cover plate also includes a blended surface that extends from the first blend edge to a second blend edge. The second blend edge intersects with the inner surface.

A turbine blade includes an airfoil that extends radially between a root end and a tip end, a platform coupled to the root end, and a shank that extends radially inwardly from the platform. The shank includes a cover plate. The cover plate includes an outer surface, an opposite inner surface, and a contoured face that at least partially defines a damper pin slot. The contoured face extends from the outer surface to a first blend edge. The cover plate also includes a blended surface that extends from the first blend edge to a second blend edge. The second blend edge intersects with the inner surface.

The invention relates to a method for producing a turbomachine compressor blade, comprising the following steps:installing primary pins (26) comprising a material other than a titanium-based alloy in primary bores (20) of a core, the primary bores forming at least one polygon, and installing a secondary pin made of titanium-based alloy in a secondary bore of the core; producing a stack (2) of a suction-face sheet (4), a core (14) and a pressure-face sheet (6); compacting the stack; removing the primary pins (26) from the primary bores (20); removing the secondary pin from the secondary bore; andtaking the core (14) away from the stack.

The invention relates to a method for producing a turbomachine compressor blade, comprising the following steps:installing primary pins (26) comprising a material other than a titanium-based alloy in primary bores (20) of a core, the primary bores forming at least one polygon, and installing a secondary pin made of titanium-based alloy in a secondary bore of the core; producing a stack (2) of a suction-face sheet (4), a core (14) and a pressure-face sheet (6); compacting the stack; removing the primary pins (26) from the primary bores (20); removing the secondary pin from the secondary bore; andtaking the core (14) away from the stack.

A process of forming an aerofoil is provided. The process includes: providing a layered, planar pre-form; inflating and hot creep forming the pre-form to form an intermediate structure having aerofoil pressure and suction surfaces, and a front, edge-receiving portion joining front edges of the pressure and suction surfaces; providing a leading edge piece; and bonding the leading edge piece to the front, edge-receiving portion of the intermediate structure to form an aerofoil in which the leading edge piece forms an aerofoil leading edge.

A method for accurately producing the drilled hole in a wall of a component fabricated by investment casting process, such as for use in a blade or steam turbine includes the following steps. The 3D data of actual component is obtained from the measurements or from the numerical simulation. The actual model and the ideal model are aligned and compared, a series of cutting planes are given to establish a series of 2D cross-sections of the actual and ideal models after registration. Each cross-section is dispersed into discrete points, the distance between each corresponding points are calculated and formed into 2D displacement. The accurate parametric model consisting of the depth, hole center, and the nominal vector is obtained on the basis of considering the deviations in geometrical and positional values. The drilled hole is then produced according to the corrected parametric drilled-hole geometrical and positional value.

A method for accurately producing the drilled hole in a wall of a component fabricated by investment casting process, such as for use in a blade or steam turbine includes the following steps. The 3D data of actual component is obtained from the measurements or from the numerical simulation. The actual model and the ideal model are aligned and compared, a series of cutting planes are given to establish a series of 2D cross-sections of the actual and ideal models after registration. Each cross-section is dispersed into discrete points, the distance between each corresponding points are calculated and formed into 2D displacement. The accurate parametric model consisting of the depth, hole center, and the nominal vector is obtained on the basis of considering the deviations in geometrical and positional values. The drilled hole is then produced according to the corrected parametric drilled-hole geometrical and positional value.

A method of manufacturing a hollow aerofoil component 100 for a gas turbine engine 10 comprises joining a first panel 200 to a second panel 300 using bonding, and hot forming the panels into shape. The bonding step and the hot forming step are performed in the same rig, thereby optimizing process time and component quality.