A system is for bonding a cover sheet to a core to form or repair a dual wall structure. The system includes a cover sheet probe and an inner pedestal probe. A three dimensional contoured tip of the cover sheet probe abuts against a three dimensional contoured outer surface of the cover sheet opposite a pedestal of the core. The pedestal abuts the inner surface of the cover sheet. The inner pedestal probe may be coupled to the core to create a conductive electrical path from the cover sheet probe through at least part of the structure. A flow of electric power is controlled and supplied to the cover sheet probe to heat a junction between the area of the cover sheet abutting the pedestal and the pedestal. A heated area is created in the junction and fixedly couples the coversheet and the pedestal.

Disclosed is a method for producing a blade for a turbomachine, in particular for an aero engine. The method comprises providing at least one blade airfoil with a first platform region and at least one blade root with a second platform region and joining the blade airfoil and the blade root at the respective platform regions by a friction welding method at a common joint region of the platform regions, the blade airfoil and the blade root being made of materials which are different from each other. Also disclosed is a blade which is and/or can be obtained by such a method.

Disclosed is a method for producing a blade for a turbomachine, which method comprises: providing a blade root, having a first platform region, from a first material; providing on the first platform region at least one capsule that is filled with a metallic and/or ceramic powder that comprises at least one second material which is different from the first material, for producing a blade airfoil having a second platform region; producing and shaping a blade airfoil from the capsule that is filled with the powder by at least one thermal input method, thereby connecting the blade root to the blade airfoil in respective platform regions.

Also disclosed is a blade which is obtainable and/or obtained by this method.

An improved gas turbine cover plate assembly is disclosed for use in connection with segmented cover plates in turbine configurations where it is not possible to stagger the blades to create assembly clearance. The improved turbine assembly also avoids cover plate loading slots in the disc which can cause high stress features. The improved system also includes a method to axially retain segmented cover plates in relation to a turbine disc using a segmented retainer ring.

An improved gas turbine cover plate assembly is disclosed for use in connection with segmented cover plates in turbine configurations where it is not possible to stagger the blades to create assembly clearance. The improved turbine assembly also avoids cover plate loading slots in the disc which can cause high stress features. The improved system also includes a method to axially retain segmented cover plates in relation to a turbine disc using a segmented retainer ring.

One aspect of the present disclosure includes a turbine vane assembly comprising a vane made from ceramic matrix composite material having an outer wall extending between a leading edge and a trailing edge and between a first end and an opposing second end; an endwall made at least partially from a ceramic matrix composite material configured to engage the first end of the vane; and a retaining region including corresponding bi-cast grooves formed adjacent the first end of the vane and a receiving aperture formed in the endwall; wherein a bond is formed in the retaining region to join the vane and endwall together.

An article, a component, and a method of making a component are provided. The article includes a pre-sintered preform having a contoured proximal face and a contoured distal face. The contoured proximal face is arranged and disposed to substantially mirror a contour of an end wall of a component and the contoured distal face is arranged and disposed to form an exterior surface including a modified surface characteristic. The component includes a first end wall, a second end wall, and an article secured to at least one of the first end wall and the second end wall, the article including a pre-sintered preform having a contoured proximal face and a contoured distal face. The contoured proximal face substantially mirrors a contour of at least one of the first end wall and the second end wall, and the contoured distal face is arranged and disposed to form an exterior surface thereover.

A method of defining a rib structure within an iso-grid composite component according to an exemplary aspect of the present disclosure includes, among other things, defining a first rib at least partially with a uni-tape ply bundle at a first level, the uni-tape ply bundle including uni-tape plies and a first spacer ply, and defining a second rib transverse to the first rib at least partially with a spacer at the first level, the spacer including a second, different spacer ply, the spacer transverse to the uni-tape ply bundle such that the spacer is interrupted by the uni-tape ply bundle.

A method of defining a rib structure within an iso-grid composite component according to an exemplary aspect of the present disclosure includes, among other things, defining a first rib at least partially with a uni-tape ply bundle at a first level, the uni-tape ply bundle including uni-tape plies and a first spacer ply, and defining a second rib transverse to the first rib at least partially with a spacer at the first level, the spacer including a second, different spacer ply, the spacer transverse to the uni-tape ply bundle such that the spacer is interrupted by the uni-tape ply bundle.

There is proposed a method of forming an inflated aerofoil (1), the method comprising the steps of: forming a layered, planar pre-form (30); providing at least one stress-relieving opening (44, 45, 46, 47) through the pre-form; hot creep forming and inflating the pre-form (30) to form an intermediate aerofoil; and subsequently removing material from the intermediate aerofoil, including at least a region containing the or each stress-relieving opening (44, 45, 46, 47), to form a finished aerofoil.