An electronic control system (30) for a turbopropeller engine (12) having a gas turbine (20) and a propeller assembly (13) coupled to the gas turbine (20), controls propeller operation based on a pilot input request, via generation of a driving quantity (Ip) for an actuation assembly (29) designed to adjust a pitch angle (β) of propeller blades (2) of the propeller assembly (13). The control system (30) envisages: a propeller speed regulator (39), receiving at its input a propeller speed error (ep), indicative of a difference between a propeller speed measure (Nr) and a propeller speed demand (Nrref), and generating at its output, based on the propeller speed error (ep), a first control quantity (Outi); a propeller pitch regulator (42), receiving at its input a propeller pitch error (ep), indicative of a difference between a propeller pitch demand ( ) and a pitch position measure (β), and generating at its output, based on the propeller pitch error (ep), a first control quantity (Out2); and a priority selection stage (45), configured to implement a priority selection between the first and the second control quantities, for providing at the output the driving quantity (IP), based on the priority selection between the first and the second control quantities.

Apparatuses and systems are provided herein for unducted propulsion systems. The system includes a forward housing for high efficiency for high subsonic sustained flight. A plurality of blades are affixed to the forward housing, wherein the forward housing defines a flowpath curve extending from the forward-most end of the forward housing through the axial extent of a forward blade root. The flowpath curve is described by an axial direction parallel to an axis of rotation and a radius from the axis of rotation. The flowpath curve includes a first point having a first radius where the radius reaches a maximum forward of the forward blade root and a second point aft of the first point having a second radius where the radius stops decreasing. The ratio of the first radius to the second radius is greater than or equal to 1.029.

A gas turbine is provided, the gas turbine engine including a turbomachine having an inlet splitter defining in part an inlet to a working gas flowpath and a fan duct splitter defining in part an inlet to a fan duct flowpath. The gas turbine engine also includes a primary fan driven by the turbomachine defining a primary fan tip radius R1, a primary fan hub radius R2, and a primary fan specific thrust rating TP; and a secondary fan downstream of the primary fan and driven by the turbomachine, the secondary fan defining a secondary fan tip radius R3, a secondary fan hub radius R4, and a secondary fan specific thrust rating TS; wherein the gas turbine engine defines an Effective Bypass Area, and wherein a ratio of R1 to R3 equals

[00001]$\frac{R_1}{R_3}=\sqrt{\left(EFP\right)\frac{\left(1-{\mathrm{RqR}}_{\mathrm{Sec}.-\mathrm{Fan}}^2\right)}{\left(1-{\mathrm{RqR}}_{\mathrm{Prim}.-\mathrm{Fan}}^2\right)}\left(\frac{T_P}{T_S}\right)\left(EBA\right)}.$

An airfoil assembly comprising a central spar extending along the radial direction; a blade skin positioned around the central spar to define an airfoil that has a pressure side and a suction side extending in the axial direction between a leading edge and a trailing edge, wherein at least one cavity is defined between the blade skin and the central spar; and a support structure positioned at least partially within the at least one cavity. The support structure comprises: a foam; and a foam reinforcement structure embedded within the foam.

A variable pitch bladed disc including a plurality of blades, each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each shaft having a root and a tip, the root of each blade being mounted on the tip of a corresponding rotor connecting shaft via a pivot so as to allow each blade to be rotated about the blade axis of rotation, the first blade having a first rotation axis inclination such that the rotation axis thereof is inclined in a fixed manner with respect to a radial axis passing through the root of the corresponding shaft, and the second blade has a second rotation axis inclination different from the first rotation axis inclination.

The invention relates to a module of a turbomachine of longitudinal axis X, the module comprising: ⋅—a rotary casing (31) that rotates about the longitudinal axis and bears a propeller (2; 20, 21, 22) which is provided with a plurality of blades (32); ⋅—a fixed casing (48) comprising a cylindrical wall (49) extending between an inner wall (40) and an outer wall (41) of the rotary casing (31); and, ⋅—a system (30) for changing the pitch of the blades of the propeller, mounted around the fixed casing and comprising: a control means (55) comprising a movable body (57) that is able to move axially on said fixed casing, at least one load transfer bearing (56) comprising an inner ring (65) that is connected to the movable body (57), and an outer ring (66); and a connection mechanism (61) for connecting the outer ring (66) to the blades of the propeller. According to the invention, the module further comprises a feathering device (70) for feathering the blades of the propeller, this device (70) comprising an annular row of springs (71) that are arranged around said fixed casing and extend axially, the springs (71) comprising first axial ends (72) that bear against a ferrule (51) of the fixed casing, and opposite second axial ends (73) that bear against said inner ring (65).

Apparatuses and systems are provided herein for unducted propulsion systems. The system includes a forward housing for high efficiency for high subsonic sustained flight. A plurality of blades are affixed to the forward housing, wherein the forward housing defines a flowpath curve extending from the forward-most end of the forward housing through the axial extent of a forward blade root. The flowpath curve is described by an axial direction parallel to an axis of rotation and a radius from the axis of rotation. The flowpath curve includes a first point having a first radius where the radius reaches a maximum forward of the forward blade root and a second point aft of the first point having a second radius where the radius stops decreasing. The ratio of the first radius to the second radius is greater than or equal to 1.029.

A turbine engine module of longitudinal axis X, including an unducted propeller intended to be rotated around the longitudinal axis X by a power shaft which is connected at least to a rotor member, at least one flow straightener including a plurality of stator vanes (28)-extending along a radial axis Z, at least one first casing mounted upstream, along the longitudinal axis, of the rotor member and a second casing mounted downstream, along the longitudinal axis, of the rotor member. The stator vanes each include a root housed in a sleeve which is connected to the first casing and to the second casing

The invention relates to an assembly for a turbine engine blade, the assembly comprising a fastener (9) defining a well (10) for receiving a blade root (7), and a clamping device (32) for clamping the blade root (7) against the fastener (9) when the blade root (7) is received in the well (10), wherein the clamping device (32) comprises: at least one clamping member (34; 36) suitable for bearing simultaneously on the blade root (7) and on the fastener (9) in the well (10) so as to exert a clamping force on the blade root (7), the clamping member (34; 36) defining a threaded hole, and a resilient layer (44) arranged to bear in the well on the blade root, a rod (38) comprising a thread engaging with the threaded hole so that a rotation of the rod (38) with respect to the clamping member causes a variation in the clamping force exerted by the clamping member on the root.

The invention relates to a module of a turbomachine of longitudinal axis X, the module comprising: ⋅—a rotary casing (31) that rotates about the longitudinal axis and bears a propeller (2; 20, 21, 22) which is provided with a plurality of blades (32); ⋅—a fixed casing (48) comprising a cylindrical wall (49) extending between an inner wall (40) and an outer wall (41) of the rotary casing (31); and, ⋅—a system (30) for changing the pitch of the blades of the propeller, mounted around the fixed casing and comprising: a control means (55) comprising a movable body (57) that is able to move axially on said fixed casing, at least one load transfer bearing (56) comprising an inner ring (65) that is connected to the movable body (57), and an outer ring (66); and a connection mechanism (61) for connecting the outer ring (66) to the blades of the propeller. According to the invention, the module further comprises a feathering device (70) for feathering the blades of the propeller, this device (70) comprising an annular row of springs (71) that are arranged around said fixed casing and extend axially, the springs (71) comprising first axial ends (72) that bear against a ferrule (51) of the fixed casing, and opposite second axial ends (73) that bear against said inner ring (65).