# US 10,502,143 B2 · Compressor of axial turbine engine with contra-rotating rotor > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,502,143 B2 - Document ID: US10502143B2 - Status: Granted - Kind: B2 - Application number: 14/865,202 - Filed: 2015-09-25 - Published: 2016-04-14 - Granted: 2019-12-10 - Earliest claimed: 2014-10-09 - Assignees: Safran Aero Boosters SA - Applicants: Techspace Aero S.A. - Inventors: Stéphane Hiernaux - Web page: https://patentgrep.com/patent/US10502143B2 ## CPC - 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) - F02C 3/067: having counter-rotating rotors (F02C3/073 takes precedence) - F02C 3/107: with two or more rotors connected by power transmission - F02K 3/06: with front fan - F04D 19/024: {with contrarotating parts} - F05D 2220/32: in gas turbines - F05D 2260/40: Transmission of power - F05D 2260/40311: of the epicyclical, planetary or differential type - Y02T 50/60: Efficient propulsion technologies, e.g. for 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) - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - 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 present application relates to an axial turbine engine with a turbine, a low-pressure compressor, and a fan. The turbine drives the compressor and the fan via a plurality of epicyclic reducing gears. The rotor of the compressor includes upstream a disc with a row of vanes and downstream a drum with a plurality of rows of vanes. The disc and the drum are connected to different parts of the epicyclic reducing gears, so as to be counter-rotating. The turbine engine includes a row of stator vanes arranged between two rows of rotor blades of the drum of the compressor, so as to straighten the flow and improve the efficiency. The turbine engine includes at least two epicyclic reducing gears, so that the vane rows of the drum turn faster than that downstream, which itself turns faster than the fan. ## Claims ### Claim 1 An axial turbine engine, comprising: a stator; a fan; a transmission driving the fan, the transmission comprising an upstream epicyclic reducing gear, a downstream epicyclic reducing gear, and a transmission shaft, the upstream epicyclic reducing gear comprising: an upstream outer planet wheel fixed to the fan; an upstream inner planet wheel fixed to the transmission shaft; an upstream satellite carrier fixed to an upstream side of the stator; and one or more upstream satellites which engage with the upstream outer planet wheel and with the upstream inner planet wheel; the downstream epicyclic reducing gear comprising: a downstream outer planet wheel; a downstream inner planet wheel fixed to the transmission shaft; a downstream satellite carrier fixed to a downstream side of the stator; and one or more downstream satellites which engage with the a downstream outer planet wheel and with the downstream inner planet wheel; and a compressor exhibiting successively two annular counter-rotating blade rows and an annular row of stator vanes downstream of the two annular counter-rotating blade rows, wherein the two annular counter-rotating blade rows comprise: a first row of rotor blades arranged on a disc driven by the downstream outer planet wheel of the downstream epicyclic reducing gear; and a second row of rotor blades arranged on a drum fixed to the transmission shaft. ### Claim 2 (depends on 1) The axial turbine engine in accordance with claim 1, wherein each rotor blade of the first row of rotor blades is connected to the disc via an inner end and each rotor blade of the second row of rotor blades is connected to the drum via an inner end, and wherein the compressor further comprises: additional row of stator vanes arranged upstream of the two annular counter-rotating blade rows. ### Claim 3 (depends on 1) The axial turbine engine in accordance with claim 1, wherein the downstream satellite carrier comprises an upstream portion fixed to the stator of the turbine engine, the downstream epicyclic reducing gear lying inside the annular row of stator vanes. ### Claim 4 (depends on 1) The axial turbine engine in accordance with claim 1, wherein the first row of rotor blades has blades which are higher radially than those of the second row of rotor blades. ### Claim 5 (depends on 1) The axial turbine engine in accordance with claim 1, wherein the downstream epicyclic reducing gear is configured such that the first row of rotor blades turns more slowly than the second row of rotor blades. ### Claim 6 (depends on 1) The axial turbine engine in accordance with claim 1, wherein the first row of rotor blades are arranged axially closest to the fan, said first row of rotor blades turns at an intermediate speed relative to the rotation speed of the fan and the rotation speed of the second row of rotor blades of the two annular counter-rotating blade rows. ### Claim 7 (depends on 1) The axial turbine engine in accordance with claim 1, wherein the disc is arranged upstream of the drum. ### Claim 8 (depends on 1) The axial turbine engine in accordance with claim 1, wherein the compressor comprises: a plurality of rows of stator vanes, wherein an upstream row and a downstream row at opposing ends of the compressor define the plurality of rows of stator vanes; wherein the compressor is a low-pressure compressor. ### Claim 9 (depends on 1) The axial turbine engine in accordance with claim 1, wherein the compressor comprises: a third row of rotor blades fixed to the second row of rotor blades. ### Claim 10 (depends on 1) The axial turbine engine in accordance with claim 1, the stator including a fixing housing for the fan with at least one or more rows of housing arms passing through a primary air flow path of the axial turbine engine, the compressor being arranged downstream of one of the at least one or more rows of housing arms. ### Claim 11 (depends on 2) The axial turbine engine in accordance with claim 2, wherein the additional row of stator vanes, the two annular counter-rotating blade rows and the annular row of stator vanes downstream of the two annular counter-rotating blade rows form a succession of four successive rows. ### Claim 12 An axial turbine engine, comprising: a fan; a compressor fitted with a rotor with at least three annular rows of rotor blades, of which two annular rows are counter-rotating; a transmission shaft; a reducing gear connecting the fan to the transmission shaft; an epicyclic reducing gear comprising: an outer planet wheel; an inner planet wheel fixed to the transmission shaft; a satellite carrier fixed to a stator; and one or more satellites which engage with the outer planet wheel and with the inner planet wheel; and an annular row of cambered stator vanes; wherein the at least three annular rows of rotor blades comprise: a first row of rotor blades arranged on a disc driven by the outer planet wheel of the epicyclic reducing gear; and a second row of rotor blades and a third row of rotor blades, both being arranged on a drum fixed to the transmission shaft; and wherein the annular row of cambered stator vanes is arranged between the second row of rotor blades and the third row of rotor blades, the cambered stator vanes being arranged so as to straighten axially the flow between the second row of rotor blades and the third row of rotor blades.