SPLIT AXIAL-CENTRIFUGAL COMPRESSOR

摘要

A gas turbine engine including a compressor, a turbine, and a variable-ratio unit is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The variable-ratio unit is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor.

主权项

1. A gas turbine engine comprising
a compressor including an axial compression stage and a centrifugal compression stage arranged aft of the axial compression stage along an engine axis, a turbine arranged aft of the centrifugal compression stage and coupled to the compressor to drive rotation of the axial compression stage and the centrifugal compression stage about the engine axis, and a variable-ratio unit coupled to the turbine and the compressor, the variable-ratio unit configured to transmit rotational power generated by the turbine about the engine axis to at least one of the axial compression stage and the centrifugal compression stage to drive rotation of the at least one of the axial compression stage and the centrifugal compression stage at various speeds offset from a turbine speed, wherein the axial compression stage has an outlet radius and the centrifugal compression stage has an inlet radius that is about equal to the outlet radius of the axial compression stage to facilitate a smooth transition of air from the axial compression stage to the centrifugal compression stage.