公开(公告)号：US20200291782A1

公开(公告)日：2020-09-17

申请号：US16444341

申请日：2019-06-18

Applicant: ROLLS-ROYCE PLC ,  ITP NEXT GENERATION TURBINES SLU

Inventor： Roderick M TOWNES ,  Diego TORRE RUIZ

IPC: F01D5/08 ,  F01D5/04

Abstract: A gas turbine engine for an aircraft includes an engine core with a turbine, a compressor, and a core shaft connecting them. The engine includes a fan, with a plurality of fan blades, located upstream of the core and a gearbox receiving an input from the core shaft and outputting drive so the fan is at a lower rotational speed than the core shaft. The turbine includes a plurality of stages of axially spaced rotor blades mounted on a rotor, which are surrounded by a turbine casing. The turbine has an inlet defined at an upstream end of a first stage of blades and an outlet defined at a downstream end of a last stage of blades and a ratio of the area of the outlet to the inlet is at between 2.5 and 3.5. This increases the pressure ratio of and power extracted from the turbine and the engine.