# US 10,309,250 B2 · Splitter nose with plasma de-icing for axial turbine engine compressor > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,309,250 B2 - Document ID: US10309250B2 - Status: Granted - Kind: B2 - Application number: 14/918,041 - Filed: 2015-10-20 - Published: 2016-04-21 - Granted: 2019-06-04 - Earliest claimed: 2014-10-21 - Assignees: Safran Aero Boosters SA - Applicants: Techspace Aero S.A. - Inventors: Ghislain Herbaut; David Bouillon - Web page: https://patentgrep.com/patent/US10309250B2 ## CPC - F01D 25/02: De-icing means for engines having icing phenomena - B64D 15/12: by electric heating (heating arrangements specially adapted for transparent or reflecting areas H05B3/84) - B64D 15/163: {using electro-impulsive devices} - B64D 33/02: of combustion air intakes - F01D 5/225: {by shrouding} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 25/24: Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) - F02C 7/047: Heating to prevent icing - H05H 1/2406: {using dielectric barrier discharges, i.e. with a dielectric interposed between the electrodes} - B64D 2033/0226: {comprising boundary layer control means} - B64D 2033/0233: {comprising de-icing means} - F05D 2220/30: in turbines - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2270/172: by a plasma generator, e.g. control of ignition - F05D 2300/40: Organic materials - F05D 2300/603: Composites; e.g. fibre-reinforced - H05H 1/2425: {the electrodes being flush with the dielectric} - 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) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - 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) - H05H: PLASMA TECHNIQUE (apparatus or processes specially adapted for producing X-rays H05G2/00); PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS - 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 deals with a splitter nose delimiting the inlet of a low-pressure compressor of an axial turbine engine. The splitter nose comprises a separation surface with an upstream circular edge suitable for separating a flow entering into the turbine engine into a primary flow and a secondary flow, and a plasma de-icing device. The device comprises two annular layers of dielectric material (42; 44) partially forming the separation surface, an electrode forming the upstream edge, an electrode forming an outer wall of the splitter nose, an electrode forming an outer shroud which supports blades, an electrode delimiting the primary flow. The device generates plasmas (46; 48; 50) opposing the presence of ice on the partitions of the splitter nose. The invention also deals with a turbine engine with a splitter nose that is provided with a de-icing system downstream of the fan. ## Claims ### Claim 1 An axial turbine engine compressor, said compressor comprising a splitter nose, the splitter nose comprising: a separation surface with an upstream circular edge, intended to split a flow entering into the turbine engine into a primary annular flow and a secondary annular flow wherein the separation surface comprises an inner annular portion intended to delimit the primary flow, an outer annular portion intended to delimit the secondary flow and the upstream circular edge linking the inner annular portion to the outer annular portion; a first layer of dielectric material partially forming the separation surface; a first electrode which partially forms the separation surface and which is adapted to form a plasma in combination with the first dielectric layer in order to de-ice the separation surface, the first electrode being arranged on the upstream circular edge, a second layer of dielectric material, distinct from the first layer of dielectric material, the second layer of dielectric material having a tubular portion; and a second electrode separated from the first electrode by the first layer of dielectric material, the second electrode being configured to be able to form a plasma on the separation surface in combination with the second layer of dielectric material, wherein the first and second dielectric layers are separated axially by an annular groove forming an axial circular gap, which can allow for a relative movement between the first electrode and the second electrode. ### Claim 2 (depends on 1) The axial turbine engine compressor in accordance with claim 1, wherein the compressor comprises; an outer wall on which the first layer of dielectric material is arranged; and an outer shroud and an annular row of stator blades extending radially inwards from the outer shroud, wherein the second layer of dielectric material is arranged on the outer shroud. ### Claim 3 (depends on 2) The axial turbine engine compressor in accordance with claim 2, wherein the outer wall is inwardly in contact with the second layer of dielectric material. ### Claim 4 (depends on 1) The axial turbine engine compressor in accordance with claim 1, wherein the first and second layers of dielectric material are formed by a respective organic matrix of a composite material. ### Claim 5 (depends on 1) The axial turbine engine compressor in accordance with claim 1, wherein the layers of dielectric material each have a form of revolution with a profile of revolution about the axis of rotation, the first layer of dielectric material being upstream the second layer of dielectric material and the first layer of dielectric material having a profile of revolution radially higher than the profile of revolution of the second layer of dielectric material. ### Claim 6 (depends on 1) The axial turbine engine compressor in accordance with claim 1, wherein the nose comprises at least four electrodes distributed in two sets of electrodes configured to be able to generate at least two circular plasmas to de-ice the separation surface, each set of electrodes being separated by a respective layer amongst the first and second layers of dielectric material. ### Claim 7 (depends on 1) The axial turbine engine compressor in accordance with claim 1, wherein the first and second layers of dielectric material are U-shaped and cover upstreamingly an outer wall and an outer shroud respectively. ### Claim 8 (depends on 7) The axial turbine engine compressor in accordance with claim 7, wherein the outer wall is inwardly in contact with the second layer of dielectric material. ### Claim 9 (depends on 1) The axial turbine engine compressor in accordance with claim 1, wherein the first electrode is configured to generate a plasma which flows radially outwardly and inwardly from the first electrode, and the second electrode is configured to form a plasma which flows axially downstream from the second electrode. ### Claim 10 (depends on 1) The axial turbine engine compressor in accordance with claim 1 wherein the compressor comprises: an outer wall on which the first layer of dielectric material is arranged, the first layer of dielectric material being arranged between the first electrode and the outer wall, such that the first electrode and the outer wall form a first set of electrodes generating plasma. ### Claim 11 (depends on 1) The axial turbine engine compressor in accordance with claim 1 wherein the compressor comprises: an outer shroud and an annular row of stator blades extending radially inwards from the outer shroud, wherein the second layer of dielectric material is arranged between the outer shroud and the second electrode, such that the second electrode and the outer shroud form a second set of electrodes generating plasma.