# US 10,767,505 B2 · Turbomachine shaft > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,767,505 B2 - Document ID: US10767505B2 - Status: Granted - Kind: B2 - Application number: 15/320,303 - Filed: 2015-08-28 - Published: 2017-09-07 - Granted: 2020-09-08 - Earliest claimed: 2014-09-05 - Assignees: Safran Aircraft Engines - Applicants: Safran Aircraft Engines - Inventors: Youki Olivier Ito-Lardeau; Pierrick Raphael Americo Bauduin; Stephane Pierre Guillaume Blanchard; Bertrand Guillaume Robin Pellaton - Web page: https://patentgrep.com/patent/US10767505B2 ## CPC - F01D 17/02: Arrangement of sensing elements - F01D 5/026: {Shaft to shaft connections} - F02C 7/36: Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) - F16C 3/023: {made of several parts, e.g. by welding} - F16D 1/02: for connecting two abutting shafts or the like - F16D 1/10: Quick-acting couplings in which the parts are connected by simply bringing them together axially - F05D 2240/61: Hollow - F16D 2001/103: {the torque is transmitted via splined connections} - F16D 2300/18: Sensors; Details or arrangements thereof - Y10T 403/7026: Longitudinally splined or fluted rod - 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) - F16C: SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS - F16D: COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract A tubular shaft (8) of a turbomachine, including at the inner periphery of same, a bath (11), substantially perpendicular to splines (9), the bath (11) includes cavities (17) distributed over a circumference centred on an axis of rotation (LL) of the shaft (8). ## Claims ### Claim 1 A tubular turbine engine shaft, having at its inner periphery a trough, wherein said trough has at least one recess which is made in a surface centered on the axis of rotation of the tubular engine shaft and is for trapping oil entering in said trough. ### Claim 2 (depends on 1) The turbine engine shaft according to claim 1, wherein said trough has a part in which said at least one recess is made on a surface generated by the rotation about the axis of rotation of a curve defined in a meridian plane. ### Claim 3 (depends on 1) The turbine engine shaft according to claim 1, comprising at least two recesses distributed on a circumference about the axis of rotation of the tubular engine shaft. ### Claim 4 (depends on 3) The turbine engine shaft according to claim 3, wherein the recesses are distributed regularly about said axis of rotation. ### Claim 5 (depends on 4) The turbine engine shaft according to claim 4, wherein the recesses are symmetrical in relation to said axis of rotation or in relation to a plane passing through said axis of rotation. ### Claim 6 (depends on 1) The turbine engine shaft according to claim 1, wherein the recess or recesses are obtained by milling or by electrical discharge machining in an internal wall of the tubular engine shaft. ### Claim 7 (depends on 1) The turbine engine shaft according to claim 1, wherein the recess or recesses are formed by parts forming partitions and extending substantially radially from an internal wall of the shaft. ### Claim 8 (depends on 7) The turbine engine shaft according to claim 7, wherein the parts forming partitions are fixed by brazing or welding. ### Claim 9 (depends on 1) The tubular turbine engine shaft according to claim 1, having connection means disposed at its outer periphery and configured so as to transmit a torque to another shaft. ### Claim 10 (depends on 9) The tubular turbine engine shaft according to claim 9, wherein the trough is situated substantially in line with said connection means. ### Claim 11 (depends on 9) The turbine engine shaft according to claim 9, wherein the connection means are splines. ### Claim 12 (depends on 1) The turbine engine shaft according to claim 1 wherein the trough forms a hollow inside the inner periphery. ### Claim 13 (depends on 1) The turbine engine shaft according to claim 1 wherein the trough has a surface having a part closer to the axis of rotation generated by the rotation of a curve in a meridian plane. ### Claim 14 (depends on 1) The turbine engines shaft according to claim 1 wherein the at least one recess comprises a bottom surface linked to a surface of the trough. ### Claim 15 (depends on 1) The turbine engines shaft according to claim 1 wherein the recess has a closed surface which is linked to a surface of the trough. ### Claim 16 (depends on 1) A method for detecting the presence of oil inside a tubular turbine engine shaft according to claim 1, at the trough in the inner periphery of the tubular turbine engine shaft, the method comprising: a step of measuring a value of an unbalance of the tubular turbine engine shaft synchronous with a rotation speed of the tubular turbine engine shaft, and a step of issuing an alert when the difference between said unbalance value and an unbalance value of the tubular turbine engine shaft alone is above a predetermined threshold, said predetermined threshold corresponding to the likely presence of oil trapped in one recess at least and producing an unbalance synchronous with the speed of the tubular turbine engine shaft.