A gas turbine engine includes a low speed spool mechanically interconnecting a low pressure turbine and at least one of a fan and a prop, a high speed spool mechanically interconnecting a high pressure turbine and a high pressure compressor, and an epicyclic gear system mechanically coupled to the high speed spool. The gas turbine engine also includes a low pressure compressor mechanically coupled to the high speed spool via the epicyclic gear system. The low pressure compressor may be mechanically independent of the low speed spool. The gas turbine engine may include a plurality of motor-generators for transferring power between the high speed spool and the low pressure compressor.
LOW PRESSURE COMPRESSOR CONTROL FOR A GAS TURBINE ENGINE
2020-06-11
Patent
Electronic Resource
English
Low pressure compressor control for a gas turbine engine
European Patent Office | 2023
|LOW PRESSURE COMPRESSOR CONTROL FOR A GAS TURBINE ENGINE
European Patent Office | 2023
|