AIRCRAFT TURBINE ENGINE WITH EPICYCLIC REDUCTION GEAR HAVING A VARIABLE REDUCTION RATIO
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...
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Main Authors | , , |
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Format | Patent |
Language | Chinese English |
Published |
15.01.2019
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Subjects | |
Online Access | Get full text |
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