A blade (1) for a turbomachine, including an impact chamber (2), a single impulse body (3) being situated in the impact chamber, a clearance (S1+S2) between the impulse body and the impact chamber being at least 10 μm and/or at most 1.5 mm in at least one direction.

A bulkhead (22) of a wind turbine (10) to be arranged on a rotor blade connection of a rotor blade (14), especially on a rotor hub (9). The bulkhead (22) has a core body (30). A layer (31, 32) of fiberglass-reinforced plastic (31, 32) is arranged on the core body (30) on both sides respectively and a metal layer body (33) is arranged on one side of the layer of fiberglass-reinforced plastic (31). A method for producing a bulkhead (22) of a wind turbine (9), which is arranged on a rotor blade connection of a rotor blade (14) and a use of a bulkhead (22) of a wind turbine (10).

There is provided a wind power installation rotor blade having a rotor blade root, a rotor blade tip, a rotor blade leading edge, a rotor blade trailing edge, a pressure side and a suction side. The rotor blade further has a rotor blade outer casing with at least one opening in the pressure and/or suction side for receiving handling means for fitting or removing the rotor blade. The rotor blade also has at least one fixing unit for fixing the handling means which are introduced through the at least one opening. The fixing unit is arranged in the interior of the rotor blade outer casing between the pressure side and the suction side.

A metal part is hot formed by placing a metal part blank on a forming tool and installing a fabric cover over the forming tool, overlying the metal part blank. The fabric is at least partially wrapped around the metal part blank. The metal part blank is heated to a temperature sufficient to allow forming of the metal part blank. Forming pressure is applied to the metal part blank that conforms the metal part blank to the forming tool by tensioning the fabric.

A method of balancing a gas turbine engine rotor comprises the step of obtaining a rotor disc with a circumferential array of balance tabs projecting from a peripheral rim of the disc. Stress shielding scallops are defined in the rotor disc between the tabs. The balancing is achieved by removing material from at least one of the tabs.

Apparatus for storing, tapering, cutting and dispensing preform layers of material includes a device for storing coiled lengths of the preform layers of material and a mechanism for receiving coiled lengths of the preform layers of material. The mechanism includes a grinding mechanism to grind portions of the preform layers of material and a cutter to cut the grinded portions of material. A programmable controller is configured to control the operations of at least one of the device and mechanism.

A method of bonding a blade cuff to a rotor blade includes installing the blade cuff to a root end of the rotor blade. The method includes mounting the rotor blade within a plurality of supports. The method includes coupling the blade cuff to a first fixture. The method includes installing a second fixture about the blade cuff. The method further includes applying localized and constant heat and pressure to the blade cuff via the second fixture.

A first rotor configured to rotate adjacent to a second rotor is disclosed. The second rotor includes a circular main body with a first axis of rotation and a vane extending radially from the main body. The first rotor includes a first curved surface that corresponds to a curve swept at a constant radius about a second axis of rotation, a second curved surface that corresponds to a curve swept by a leading edge of the vane when the second rotor is simultaneously rotated about the first axis of rotation and the second axis of rotation, a third curved surface that corresponds to a curve swept by a trailing edge of the vane when the second rotor is simultaneously rotated about the first axis of rotation and the second axis of rotation, and a vane-receiving groove disposed between the second curved surface and the third curved surface.

A blade for mounting on a rotor disc of a gas turbine engine includes platform segments between a airfoil and blade root and extending laterally from the blade, the platform segment having a curved profile defining a platform recess on a root side of the platform segment, the recess configured to cooperate with recesses of adjacent blades to define a blade pocket. A recessed region is defined in a rear surface of the blade root, and is configured to receive a complementary projection of the rotor disc upon mounting the blade on the rotor disc. The recessed region has a surface configured to abut a corresponding surface on the projection of the rotor disc to form a face seal. Methods of manufacturing such a rotor disc and of sealing a circumferential joint between such blades and the rotor disc are also disclosed.

A method of forming an airfoil includes the steps of depositing material to form an airfoil in a first layer, and then depositing material in a second layer on the first layer. The first and second layers have distinct densities. An airfoil is also disclosed. The method provides powerful design advantages.