# US 2019/0169990 A1 · Turbine engine assembly comprising a nose cone and a front shroud > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2019/0169990 A1 - Document ID: US20190169990A1 - Status: Published application - Kind: A1 - Application number: 16/321,263 - Filed: 2017-07-27 - Published: 2019-06-06 - Earliest claimed: 2016-07-29 - Assignees: Safran Aircraft Engines - Applicants: Safran Aircraft Engines - Inventors: Alexis Thomas CHABOUD; Alexandre Michel Henri HASQUENOPH; Guillaume Maurice René PATIN - Web page: https://patentgrep.com/patent/US20190169990A1 ## CPC - F01D 5/066: {Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps} - F01D 25/243: {Flange connections; Bolting arrangements (F01D25/265 takes precedence)} - F02C 7/04: Air intakes for gas-turbine plants or jet-propulsion plants - F05D 2220/36: specially adapted for the fan of turbofan engines - F05D 2250/232: conical - F05D 2260/31: Retaining bolts or nuts - F05D 2260/36: by a form fit connection, e.g. by interlocking - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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 - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract The invention relates to an assembly for a turbine engine extending about a longitudinal axis, comprising: a nose cone (20) comprising a conical body (22) extending about the longitudinal axis and a flange (23) comprising a first contact surface (24) forming an extension of an inner surface (25) of the conical body (22); a front shroud (21) comprising an overall annular body (26) extending about the longitudinal axis and a flange (27) comprising a first contact surface (28) forming an extension of an outer surface (29) of the annular body (26), the first contact surface (24) of the nose cone (20) being in contact with the first contact surface (28) of the front shroud (21), the first contact surfaces (24, 28) of the nose cone (20) and the front shroud (21) being tilted in the downstream direction towards the longitudinal axis, so that the flange (23) of the nose cone (20) is secured to the flange (27) of the front shroud (21); and attachment elements (30) configured to clamp the first contact surface (24) of the flange (23) of the nose cone (20) against the first contact surface (28) of the flange (27) of the front shroud (21). ## Claims ### Claim 1 An assembly for a turbine engine extending about a longitudinal axis (11), comprising: a nose cone (20) comprising a conical body (22) extending about the longitudinal axis (11) or an axis parallel to said longitudinal axis (11) and a flange (23) arranged downstream of the conical body (22), in the gas flow direction, said flange (23) comprising a first contact surface (24) extending into the extension of an inner surface (25) of the conical body (22), a front shroud (21) comprising a generally annular body (26) extending about the longitudinal axis (11) or the axis parallel to said longitudinal axis (11) and a flange (27) arranged upstream of the annular body (26), in the gas flow direction, said flange (27) comprising a first contact surface (28) extending into the extension of an outer surface (29) of the annular body (26), the first contact surface (24) of the nose cone (20) being in contact with the first contact surface (28) of the front shroud (21), fasteners (30) configured to clamp the first contact surface (24) of the nose cone (20) flange (23) against the first contact surface (28) of the front shroud (21) flange (27), said assembly being characterized in that the first contact surface (24) of the nose cone (20) and the first contact surface (28) of the front shroud (21) are inclined from upstream to downstream, in the gas flow direction, towards the longitudinal axis (11), so that the flange (23) of the nose cone (20) grips the flange (27) of the front shroud (21). ### Claim 2 (depends on 1) The assembly according to claim 1, wherein the first contact surfaces (24, 28) of the nose cone (20) flange (23) and of the front shroud (21) flange (27) are inclined with respect to the longitudinal axis (11) by an angle (α) comprised between 5 and 25°. ### Claim 3 (depends on 1) The assembly according to claim 1, wherein the flange (23) of the nose cone (20) comprises over its entire circumference, a succession of protrusions (33) extending radially inwards, with respect to the longitudinal axis (11), from said flange (23) and accommodating the first contact surface (24) of the nose cone (20) flange (23), and wherein the flange (27) of the front shroud (21) comprises over its entire circumference, a plurality of tabs (35) extending from said flange (27) in the direction of the conical body (22) of the nose cone (20) and accommodating the first contact surface (28) of the front shroud (21) flange (27). ### Claim 4 (depends on 1) The assembly according to claim 1, wherein the flange (23) of the nose cone (20) comprises a second contact surface (31) extending generally perpendicularly with respect to the longitudinal axis (11) into the extension of the first contact surface (24), and wherein the flange (27) of the front shroud (21) comprises a second contact surface (32) extending generally perpendicularly with respect to the longitudinal axis (11) into the extension of the outer surface (29) of the annular body (26) and into the extension of which the first contact surface (28) extends, the second contact surface (31) of the nose cone (20) being in contact with the second contact surface (32) the front shroud (21). ### Claim 5 (depends on 4) The assembly according to claim 4, wherein the second contact surfaces (31, 32) of the nose cone (20) flange (23) and of the front shroud (21) flange (27) are continuous over the entire circumference of their respective flange (23, 27). ### Claim 6 (depends on 4) The assembly according to claim 4, further comprising an annular sealing element (38) arranged between the second contact surface (31) of the nose cone (20) flange (23) and the second contact surface (32) of the front shroud (21) flange (27). ### Claim 7 (depends on 6) The assembly according to claim 6, wherein an annular groove (39, 40) is arranged in the second contact surface (31) of the nose cone (20) flange (23) and/or in the second contact surface (32) of the front shroud (21) flange (27), said annular groove(s) (39, 40) accommodating the sealing element (38). ### Claim 8 (depends on 1) A nose cone (20) for a turbine engine assembly according to claim 1. ### Claim 9 (depends on 1) A front shroud (21) for a turbine engine assembly according to claim 1. ### Claim 10 (depends on 1) A turbine engine (10) comprising a turbine engine assembly according to claim 1. ### Claim 11 (depends on 1) A method for mounting a nose cone (20) on a front shroud (21) of an assembly according to claim 1, wherein the nose cone (20) is advanced along the longitudinal axis (11) so that the protrusions (33) are each positioned in a recess arranged between two adjacent tabs (35), and this until the second contact surface (31) of the nose cone (20) flange (23) is in contact with the second contact surface (32) of the front shroud (21) flange (27), then the nose cone (20) is pivoted about the longitudinal axis (11) to put into contact the first inclined contact surfaces (24, 28) of the nose cone (20) and front shroud (21) flanges, the fasteners (30) are then placed.