# US 12,000,298 B2 · Device for pressurizing turbomachine downstream enclosure, and corresponding turbomachine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,000,298 B2 - Document ID: US12000298B2 - Status: Granted - Kind: B2 - Application number: 18/250,346 - Filed: 2021-10-22 - Published: 2023-12-14 - Granted: 2024-06-04 - Earliest claimed: 2020-10-27 - Assignees: Safran Aircraft Engines - Applicants: Safran Aircraft Engines - Inventors: Maeva Daphne Gros-Borot; Clementine Charlotte Marie Mouton - Web page: https://patentgrep.com/patent/US12000298B2 ## CPC - F01D 25/16: Arrangement of bearings; Supporting or mounting bearings in casings (bearings per se F16C) - F02C 7/06: Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) - F01D 5/026: {Shaft to shaft connections} - F01D 5/06: Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections {(F01D5/022, F01D5/023 take precedence)} - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2240/50: Bearings - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A device for pressurizing a turbomachine downstream enclosure, the device being fed by means of a pressurizing air flow and including: a first shaft portion, a second shaft portion coupled to the first shaft portion via internal splines and external splines and extending, at a distance, inside the first shaft portion. The device includes at least a first passage made through the splines, and at least one orifice passing right through the second shaft portion, the orifice being arranged upstream of the first passage, in fluidic communication with the first passage, and opening out inside the second shaft portion so as to allow the pressurizing air flow to circulate from the first passage, between the first and second shaft portions, towards the downstream enclosure. ## Claims ### Claim 1 A device for pressurising a downstream enclosure of a turbomachine with a longitudinal axis X, the device being supplied by means of a pressurisation air flow (FP) collected upstream of the turbomachine along the longitudinal axis, the device comprising: a first shaft segment extending along the longitudinal axis X, a second shaft segment coupled to the first shaft segment via longitudinal internal splines carried by the first shaft segment and longitudinal external splines carried by the second shaft segment, the second shaft segment extending at least partly inside the first shaft segment with a radial distance along a radial axis Z perpendicular to the longitudinal axis X, the internal and external splines comprising faces respectively, wherein it comprises at least one first passage made through the internal and external splines, and at least one orifice passing through the second shaft segment on either side along the radial axis, the orifice being arranged upstream of the first passage and, on the one hand, being in fluidic communication with the first passage and, on the other hand, opening out inside the second shaft segment so as to allow the circulation of the pressurisation air flow (FP) from the first passage between the first shaft segment and the second shaft segment, then through the orifice towards the downstream enclosure of the turbomachine and in that the internal and external splines are configured so as to create pairs of internal and external splines adjacently along a circumferential direction, with faces in contact with each other, and empty inter-spline spaces forming first passages. ### Claim 2 (depends on 1) The pressurising device according to claim 1, wherein the first passages occupy an angular range (a), measured between a lateral flank of an internal or external spline and another lateral flank of an internal or external spline which are spaced apart, and which is between 35° and 55°. ### Claim 3 (depends on 1) The pressurising device according to claim 1, wherein the first shaft segment or the second shaft segment comprises a series of teeth which are arranged downstream of the internal and external splines and configured so as to carry out a function of centring the first shaft segment with respect to the second shaft segment. ### Claim 4 (depends on 3) The pressurising device according to claim 3, wherein at least one second passage is made through the teeth. ### Claim 5 (depends on 4) The pressurising device according to claim 4, wherein the first passages and the second passages are evenly distributed around the longitudinal axis. ### Claim 6 (depends on 4) The pressurising device according to claim 4, wherein the first shaft segment comprises at least one opening passing through its wall on either side, the opening being located downstream of the second passage and being intended to open out inside the first shaft segment. ### Claim 7 (depends on 3) The pressurising device according to claim 3, wherein the teeth are spaced apart from each other in a circumferential direction so as to create empty inter-tooth spaces forming second passages. ### Claim 8 (depends on 3) The pressurising device according to claim 3, wherein the internal and external splines have a similar cross-sectional shape and dimensions and the teeth each have a similar cross-sectional shape and dimensions. ### Claim 9 (depends on 1) The pressurising device claim 1, wherein it comprises a first shaft comprising the first shaft segment and the second shaft segment, and a second shaft within which the first shaft extends at least partly, the second shaft comprising at least one hole passing through its wall on either side, the hole being intended to be arranged in the vicinity of the downstream enclosure in such a way that the pressurisation air flow leaving the orifice or orifices penetrates inside the downstream enclosure. ### Claim 10 (depends on 1) An aircraft turbomachine comprising a propeller rotating about a longitudinal axis X, a gas generator for driving the propeller in rotation, and a device for pressurising a downstream enclosure according to claim 1.