Nova Patents
EP1632672A3

Fan for an aircraft engine

Abstract

The invention relates to a fan for an aircraft engine, in particular a gas turbine aircraft engine, wherein the fan has a fan rotor (13) with fan blades (14) extending radially outward from a hub to an outer channel wall (16) of a fan flow channel an auxiliary rotor (18) positioned upstream of the fan rotor (13) and having attachment blades (19) extending radially outward from a hub and terminating at a distance from the outer passage wall (16) of the fan flow passage. According to the attachment rotor (18) and the fan rotor (13) are designed as separate rotors, wherein the attachment rotor (18) can be driven at a higher speed as the fan rotor (13).

EP1632672A3, drawing sheet 1
Sheet 1 of 1

Term

Term ended

Projected expiry passed 26 August 2025, 1.1 years ago.

  1. Priority
  2. Filed
  3. Published
  4. Projected expiry
  5. Today

1 sheet

  1. Sheet 1