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 turbomachine engine includes a fan assembly and a core engine comprising a turbine and an input shaft rotatable with the turbine is provided. A single-stage epicyclic gear assembly receives the input shaft at a first speed and drives an output shaft coupled to the fan assembly at a second speed. A sun gear rotates about a longitudinal centerline of the gear assembly and has a sun gear-mesh region along the longitudinal centerline of the gear assembly where the sun gear is configured to contact a plurality of planet gears. A ring gear-mesh region is provided along the longitudinal centerline of the gear assembly where a ring gear is configured to contact the plurality of planet gears. The sun gear-mesh region is axially offset from the ring gear-mesh region along the longitudinal centerline.

Described is a rotor disk (40) for a compressor (29, 32) of a gas turbine, in particular an aircraft gas turbine (10), the rotor disk having a main body (42), at least one rotor arm (44) projecting from the main body (42) in the axial direction (AR), the rotor arm (44) having, in a sectional view taken in a sectional plane defined by the axial direction (AR) and the radial direction (RR) a beginning portion (44a) merging into the main body (42); an end (44e) portion remote from the main body (42) and forming a kind of free end in the axial direction (AR), the beginning portion (44a) and the end portion (44e) being interconnected by an intermediate portion (44z), characterized in that the intermediate portion (44z) is curved with at least one radius of curvature (Ri, Ra).

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.

A dual entry turbine of a compression device includes a housing having a first inlet and a second inlet, and a first outlet and a second outlet. A turbine impeller is arranged within the housing. The turbine impeller has a first gas path and a second gas path. A first flow path extends from the first inlet to the first outlet via the first gas path and a second flow path extends from the second inlet to the second outlet via the second gas path. The first flow path and the second flow path being fluidly separate from one another.

A turbomachine engine includes a fan assembly and a core engine comprising a turbine and an input shaft rotatable with the turbine is provided. A single-stage epicyclic gear assembly receives the input shaft at a first speed and drives an output shaft coupled to the fan assembly at a second speed. A sun gear rotates about a longitudinal centerline of the gear assembly and has a sun gear-mesh region along the longitudinal centerline of the gear assembly where the sun gear is configured to contact a plurality of planet gears. A ring gear-mesh region is provided along the longitudinal centerline of the gear assembly where a ring gear is configured to contact the plurality of planet gears. The sun gear-mesh region is axially offset from the ring gear-mesh region along the longitudinal centerline.

A compressor rotor for turbomachinery, such as a compressor, is provided. Disclosed embodiments can benefit from seal elements that may be arranged to inhibit passage onto respective hirth couplings of process fluid being processed by the compressor. A seal element may be affixed to adjacent rotor components (e.g., adjacent impeller bodies) by way of a slip or interference fit connection to one of the adjacent components and may be affixed to the other adjacent rotor component by way of a elastically flexible frustoconical inner surface of the seal element that permits the seal element to be placed in a spring-loaded condition, which generates a biasing force to circumferentially clamp onto a frustoconical outer surface of the other adjacent rotor component. This arrangement is conducive to user-friendly assembly/disassembly of the seal elements with respect to the adjacent rotor components.

The rotor assembly can have a first disc having a first body extending circumferentially and radially around the axis, a first set of circumferentially distributed blades protruding radially from the first disc, and a male spline extending axially relative the first body, the male spline extending around and along the axis, and a second disc having a second body extending circumferentially and radially around the axis, a second set of circumferentially distributed blades protruding radially from the second disc, and a female spline extending around and along the axis, the female spline receiving the male spline in a spline engagement.

A turbofan assembly that includes a primary turbine section and an aft fan section positioned downstream from the primary turbine section. The primary turbine section includes a bypass duct configured to channel a stream of bypass air therethrough, and a main flow duct configured to discharge a stream of exhaust gas therefrom. The bypass duct and the main flow duct each include a discharge end positioned such that a mixed stream of bypass air and exhaust gas is discharged from the primary turbine section. The aft fan section includes at least one turbine and fan stage including a turbine portion and a fan portion coupled to the turbine portion. The turbine portion is positioned to receive the mixed stream of bypass air and exhaust gas, and the fan portion is positioned radially outward from the turbine portion.

A blade row group arrangeable in a main flow path of a fluid-flow machine includes N adjacent member blade rows firmly arranged relative to each other in both a meridional direction (m) and a circumferential direction (u). A relative secondary passage length (v′) and a relative secondary passage width (w′) each increase at least in one part of the area between the mean meridional flow line (SLM) and at least one of the main flow path boundaries (HB) towards the main flow path boundary (HB).