A blade for a turbomachine includes a blade root portion for securing the blade to a rotatable annular outer drum rotor. The blade root portion includes one or more radial retention features for radially retaining each of the blade root portions within the rotatable annular outer drum rotor. Further, at least one of the radial retention feature(s) includes at least one sealing member integrated therewith.

A damper seal for a turbomachine includes an annular body having an inner circumferential surface and an outer circumferential surface separated by a thickness. As such, the inner circumferential surface may define a plurality of cavities arranged into a plurality of circumferential rows and at least one partition positioned between at least two of the plurality of cavities. In addition, the inner circumferential surface may further define at least one plenum arranged between two of the plurality of circumferential rows.

Flow control system systems and techniques are described. A flow control system, such as a thruster, includes an annular rotor within an annular housing. The annular rotor rotates about a central axis relative to the annular housing. The flow control system includes rotor blades with respective bases that are coupled to the annular rotor, and with respective tips directed toward the central axis. The flow control system includes a first actuator that rotates the annular rotor about the central axis relative to the annular housing, thus also rotating the rotor blades about the central axis relative to the annular housing. The flow control system includes a second actuator that rotates the rotor blades relative to the annular rotor. Actuation of the second actuator rotates a rotor blade about a rotor blade axis that extends from a base of the rotor blade toward the central axis.

Flow control system systems and techniques are described. A flow control system, such as a thruster, includes an annular rotor within an annular housing. The annular rotor rotates about a central axis relative to the annular housing. The flow control system includes rotor blades with respective bases that are coupled to the annular rotor, and with respective tips directed toward the central axis. The flow control system includes a first actuator that rotates the annular rotor about the central axis relative to the annular housing, thus also rotating the rotor blades about the central axis relative to the annular housing. The flow control system includes a second actuator that rotates the rotor blades relative to the annular rotor. Actuation of the second actuator rotates a rotor blade about a rotor blade axis that extends from a base of the rotor blade toward the central axis.

A turbomachine having an engine centerline and a first rotor. The first rotor having a first annular drum and being connected to a first plurality of blades. At least one blade of the first plurality of blades having a blade root, a blade tip, a first arm, a second arm and a first seal. The first arm extending from the blade root and having a radial retention hook. The second arm extending from the blade tip.

An axial impeller has a tubular housing mounted on bearings for rotation. The housing is capable of engaging a motor or generator directly or through a drive belt. Interior turbine blades are mounted on the housing wall. The blades may be hinged so they can rotate between a retracted position adjacent to the wall and an extended radial position. Rods penetrate the wall to position the blades between retracted and extended positions. When extended, the blades may be rotated to propel a fluid through the housing; and when retracted natural fluid flow is less restricted.

An axial impeller has a tubular housing mounted on bearings for rotation. The housing is capable of engaging a motor or generator directly or through a drive belt. Interior turbine blades are mounted on the housing wall. The blades may be hinged so they can rotate between a retracted position adjacent to the wall and an extended radial position. Rods penetrate the wall to position the blades between retracted and extended positions. When extended, the blades may be rotated to propel a fluid through the housing; and when retracted natural fluid flow is less restricted.

The present disclosure is directed to a gas turbine engine including a first turbine frame defining one or more first struts extended along a radial direction and a turbine rotor assembly. The turbine rotor assembly defines a rotatable drum surrounding a reduction speed reduction assembly and coupled thereto. The turbine rotor assembly includes a first turbine rotor and a second turbine rotor each disposed on one or more bearing assemblies. The first turbine frame defines a first supply conduit through the first strut providing a flow of fluid to the speed reduction assembly and one or more of the bearing assemblies. The first turbine frame further defines a first scavenge conduit providing an egress of at least a portion of the flow of fluid from one or more of the bearing assemblies.

The present disclosure is directed to a gas turbine engine including a first turbine frame defining one or more first struts extended along a radial direction and a turbine rotor assembly. The turbine rotor assembly defines a rotatable drum surrounding a reduction speed reduction assembly and coupled thereto. The turbine rotor assembly includes a first turbine rotor and a second turbine rotor each disposed on one or more bearing assemblies. The first turbine frame defines a first supply conduit through the first strut providing a flow of fluid to the speed reduction assembly and one or more of the bearing assemblies. The first turbine frame further defines a first scavenge conduit providing an egress of at least a portion of the flow of fluid from one or more of the bearing assemblies.

A gas turbine engine having an interdigitated turbine assembly including a first turbine rotor and a second turbine rotor, wherein a total number of stages at the interdigitated turbine assembly is between 3 and 8, and an average stage pressure ratio at the interdigitated turbine assembly is between 1.3 and 1.9. A gear assembly is configured to receive power from the interdigitated turbine assembly, and a fan assembly is configured to receive power from the gear assembly. The interdigitated turbine assembly and the gear assembly are together configured to allow the second turbine rotor to rotate at a second rotational speed greater than a first rotational speed at the first turbine rotor. The fan assembly and the gear assembly are together configured to allow the fan assembly to rotate at a third rotational speed less than the first rotational speed and the second rotational speed. The interdigitated turbine assembly, the gear assembly, and the fan assembly together have a maximum AN.sup.2 at the second turbine rotor between 30 and 90.