AIRCRAFT TURBINE ENGINE WITH EPICYCLIC REDUCTION GEAR HAVING A VARIABLE REDUCTION RATIO

• Main Authors: FULLERINGER BENJAMIN, CAZAUX YANNICK, LECOUVREUR DAMIEN
• Format: Patent
• Language: Chinese; English
• Published: 15.01.2019
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; BLASTING; COMBUSTION ENGINES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; ENGINEERING ELEMENTS AND UNITS; GAS-TURBINE PLANTS; GEARING; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; LIGHTING; MECHANICAL ENGINEERING; THERMAL INSULATION IN GENERAL; WEAPONS

The invention relates to an aircraft turbine engine, including at least one rotary body comprising a compressor rotor and a turbine rotor connected to one another by a rotor shaft, the turbine enginebeing configured to drive a member by said shaft via an epicyclic reduction gear (32), said reduction gear including at least one first element (50) configured to be rotatably secured to said shaft, at least one second element (56) rotatably secured to said member, and at least one third element (52) which is configured to be selectively secured to a stator of the turbine engine and separated fromsaid stator, characterised in that it comprises means (82, 84) for rotating said third element which are configured to drive said third element at a predetermined speed when it is separated from saidstator. 本发明涉及种飞机涡轮发动机，包括至少个旋转体，该旋转体包括彼此通过转子轴连接的压缩机转子和涡轮转子，该涡轮发动机被配置为经由行星减速齿轮(32)通过所述轴驱动构件，所述减速齿轮包括：至少个第元件(50)，被配置为可旋转地固定到所述轴上；至少个第二元件(56)，可旋转地固定到所述构件上；和至少个第三元件(52)，被配置为选择性地固定到涡轮发动机的定子上以及与所述定子脱离，其特征在于，涡轮发动机包括用于旋转地驱动所述第三元件的装置(82