A variable pitch blade holder for use with a gas turbine engine. The variable pitch blade holder is configured to retain a blade and to rotate about a center axis with the blade during operation of the gas turbine engine. The blade holder is adapted to rotate about a pitch change axis to vary a pitch of the blade.

The invention relates to a method for producing a rotor of a flow engine, namely an integrally bladed rotor with an integral outer shroud, comprising at least the following steps: a rotor blank comprising the integral rotor blades and the integral outer shroud is first produced by means of a generative production method; the rotor blank is then subjected to a separating surface treatment at flow-guiding sections and is subjected, separately therefrom, to a machining surface treatment at non-flow-guiding sections.

A cover plate for maintaining axial alignment between a blade assembly and a rotor disk and transferring centrifugal loading directly to the rotor disk. The cover plate comprises a plate key extending axially from an elongate member, the plate key configured to engage a keyway of the rotor disk assembly and/or a notch of the blade key.

A wheel assembly for a gas turbine engine includes a disk, a blade-attachment system, and a plurality of blades. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blade-attachment system is configured to couple the plurality of blades with the disk for rotation therewith.

A vibration absorber damper and method of dissipating vibration energy in a rotatable structure which is nominally cyclic symmetric. The nominally cyclic symmetric structure includes a hub portion having a rotational axis and a plurality of radial members radially extending from the hub portion. The hub portions having a groove extending circumferentially about the rotational axis. The vibrational absorber having a ring member having a plurality of repetitive cellular structures each defining a hollow interior section and a plurality of deformable members each extending from the ring member and disposed in a corresponding one of the repetitive cellular structures. Each of the deformable members is configured to interact with the cyclic symmetric structure to damp vibration thereof.

A double-sided impeller with a dual intake fluid housing apparatus is designed to suction an extraneous fluid through both a first intake and a second intake, where gases trapped in the fluid housing may escape and mitigate cavitation. The apparatus includes a fluid impeller, a fluid housing, an output volute, and a shaft. The fluid impeller is double-sided with a first plurality of blades and a second plurality of blades respectively adjacent to the first intake and the second intake. The fluid housing surrounds the fluid impeller and in fluid communication with the extraneous fluid. The shaft is rotationally coupled with the fluid impeller such that torque applied to the shaft applies torque to the fluid impeller. The output volute is in fluid communication with the fluid housing and tangentially positioned such that the motion of the extraneous fluid in the fluid housing is directed toward the output volute.

A sealing structure for a gas turbine includes a turbine rotor disk, a turbine blade coupled the turbine rotor disk, and an interstage disk interposed between adjacent turbine rotor disks. The turbine blade includes a blade circumferential surface protruding axially and extending in a circumferential direction of the turbine rotor disk and mutually engaging with a disk circumferential surface formed circumferentially on the turbine rotor disk. The interstage disk includes a rim portion and a groove formed in the rim portion. A plurality of static ring seals are mounted in the groove, each static ring seal facing toward the blade circumferential surface and the disk circumferential surface. The static ring are configured such that an outer circumferential surface of all the static ring seals contact the blade circumferential surface and the outer circumferential surface of at least one of the static ring seals does not contact the disk circumferential surface.

A blower (100) includes a blower attachment housing (112), a power head housing (122) having a handle (130) operably coupled thereto, a motor (140) disposed in the power head housing (122), a fan (160) disposed in the blower attachment housing (112), a battery (150), and an intake chamber (174) disposed between the motor (140) and the fan (160) to enable the air to enter the blower (100) between the motor (140) and the fan (160).

A compact and unobtrusive rotor control mechanism is presented that provides collective and cyclic pitch change to both rotors of a coaxial rotor system as well as a differential collective pitch change to one or both rotors simultaneously.

A rotor drum for an aircraft turbomachine includes an annular wall extending around a longitudinal axis (A), the annular wall carrying rotor blades and having at least one bleed device configured to allow at least one liquid to pass through the annular wall. The bleed device includes a series of three adjacent circular orifices, the three orifices being aligned along a line and having a central orifice of larger diameter D1 and two lateral orifices of smaller diameter D2 diametrically opposed with respect to the central orifice.