Patent ID: 11859538
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 5:
6. A turbine engine comprising:
a three-stage first compression section disposed aft of a geared architecture, the three-stage first compression section including a first rotating compressor blade with a leading edge and a last rotating compressor blade with a trailing edge, wherein a radial distance from an engine longitudinal axis to a tip of the trailing edge of the last rotating compressor blade is greater than 67% of a radial distance from the engine longitudinal axis to a tip of the first rotating compressor blade at the leading edge; and
an eight stage second compression section including a last rotating compressor blade with a trailing edge tip that includes a radial length that is greater than 57% of a radial length of the first rotating compressor blade at the leading edge of the eight-stage first compression section.