# US 11,993,365 B2 · Aircraft turbine engine comprising variable-pitch propeller blades > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,993,365 B2 - Document ID: US11993365B2 - Status: Granted - Kind: B2 - Application number: 18/006,344 - Filed: 2021-07-15 - Published: 2023-09-14 - Granted: 2024-05-28 - Earliest claimed: 2020-07-24 - Assignees: Safran Aircraft Engines - Applicants: Safran Aircraft Engines - Inventors: Clement Cottet; Vivien Mickael Courtier; Vincent Joudon; Regis Eugene Henri Servant; Laurent Jablonski - Web page: https://patentgrep.com/patent/US11993365B2 ## CPC - B64C 27/78: in association with pitch adjustment of blades of anti-torque rotor - F04D 29/323: {adjustable} - B64C 11/06: for variable-pitch blades - F01D 7/00: Rotors with blades adjustable in operation; Control thereof (for reversing F01D1/30) - F04D 29/644: {especially adapted for elastic fluid pumps} - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - B64C: AEROPLANES; HELICOPTERS - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An assembly comprising a propeller blade and its system for angularly adjusting the pitch of the blade including a bowl which is radially delimited by an annular wall extending about an axis for adjusting the pitch of the blade, the bowl having a bottom wall, a free lower end of the root being fitted axially into a complementary housing of the bottom wall in order to rotatably connect the bowl and the blade about the pitch-adjustment axis. The root of the blade comprises a first limiting face that engages with a first abutment face of the bowl to limit the rotation of the blade in the event of breakage of the lower end of the root. ## Claims ### Claim 1 An assembly comprising a propeller vane and a system for setting the pitch of the vane about a pitch setting axis, for an aircraft turbine engine, the vane having a root extending from an upper end connected to a blade of the vane to a free lower end, the system for setting the pitch of the vane comprising a cup which is radially delimited by an annular wall extending around the pitch setting axis, the cup comprising a bottom wall and an upper opening through which the root is intended to be inserted axially into the cup, the free lower end of the root being nested axially into a housing of the bottom wall having a cross-section complementary to that of the free lower end of the root in order to connect the cup and the vane in rotation about the pitch setting axis, wherein the root of the vane comprises at least one radial limiting face which is intended to cooperate with at least one associated radial stop face of the cup in order to limit the rotation of the vane in an orientation about the pitch setting axis with respect to the cup in the event of failure of the lower end of the root. ### Claim 2 (depends on 1) The assembly according to claim 1, wherein the root of the vane comprises: at least one first radial limiting face of the at least one radial limiting face for cooperating with at least one first radial stop face of the at least one associated radial stop face in order to limit the rotation of the vane in a first orientation about the pitch setting axis with respect to the cup in the event of failure of the lower end of the root; and at least one second radial limiting face which is intended to cooperate with at least one associated second radial stop face of the cup in order to limit the rotation of the vane in a second orientation about the pitch setting axis with respect to the cup in the event of failure of the lower end of the root. ### Claim 3 (depends on 2) The assembly according to claim 2, wherein the root comprises a body housed in an annular barrel prior to its insertion into the cup, each at least one radial limiting face being formed in one part with the barrel. ### Claim 4 (depends on 2) The assembly according to claim 2, wherein the at least one first radial limiting face and the at least one second radial limiting face are arranged on a common limiting finger which projects radially outwards relative to the root. ### Claim 5 (depends on 4) The assembly according to claim 4, wherein the limiting finger is received in an associated stop notch of the cup which is circumferentially delimited by the at least one first radial stop face and by the at least one second radial stop face. ### Claim 6 (depends on 4) The assembly according to claim 4, wherein a radial space is reserved between the limiting finger and an internal face of the annular wall of the cup. ### Claim 7 (depends on 2) The assembly according to claim 2, wherein the at least one first radial stop face and the at least one second radial stop face are arranged in opposition on a common stop finger which projects radially inwards relative to the annular wall of the cup. ### Claim 8 (depends on 7) The assembly according to claim 7, wherein the stop finger is received in an associated limiting notch of the root which is circumferentially delimited by the at least one first radial limiting face and by the at least one second radial limiting face. ### Claim 9 (depends on 8) The assembly according to claim 8, wherein a radial space is reserved between the stop finger and the root. ### Claim 10 (depends on 1) The assembly according to claim 1, wherein an angular space is reserved between each at least one radial limiting face and its at least one associated radial stop face when the vane is connected in rotation to the cup by means of its free lower end. ### Claim 11 (depends on 10) The assembly according to claim 10, wherein the angular space is between 2° and 10° around the pitch setting axis. ### Claim 12 (depends on 10) The assembly according to claim 10, wherein the angular space around the pitch setting axis is equal to 5°. ### Claim 13 (depends on 1) The assembly according to claim 1, wherein the assembly comprises retention means for axially attaching the root in the cup. ### Claim 14 (depends on 13) The assembly according to claim 13, wherein the root has a bulged stretch, referred to as “bulb”, which is arranged axially between the blade and the free lower end, the pitch setting system comprising an annular immobilization ring which is configured to be mounted inside the cup and to cooperate respectively with the bulb and the annular wall of the cup in order to secure the root axially to the cup. ### Claim 15 (depends on 14) The assembly according to claim 14, wherein the root of the vane comprises: at least one first radial limiting face of the at least one radial limiting face for cooperating with at least one first radial stop face of the at least one associated radial stop face in order to limit the rotation of the vane in a first orientation about the pitch setting axis with respect to the cup in the event of failure of the lower end of the root; and at least one second radial limiting face which is intended to cooperate with at least one associated second radial stop face of the cup in order to limit the rotation of the vane in a second orientation about the pitch setting axis with respect to the cup in the event of failure of the lower end of the root, wherein the at least one radial stop faces and the at least one radial limiting face are arranged axially below the immobilization ring. ### Claim 16 (depends on 15) The assembly according to claim 15, wherein a portion of the at least one radial limiting face is arranged substantially at the level at which the bulb has maximum radial dimensions.