Patent ID: 9077221
Filing Date: 2015-07-07
Classification: F01D,F02K,F05D,H02K

Abstract:
1. A gas turbine engine, comprising: a cold section stage being at least one of including a fan blade stage and a compressor blade stage, wherein the fan blade stage includes a wheel and a plurality of blades and a shroud circumferentially surrounding the plurality of blades; a combustor in fluid communication with the at least one of the fan blade stage and the compressor blade stage; a turbine in fluid communication with the combustor; and an electrical machine located between the fan blade stage and the compressor blade stage, the electrical machine being configured to generate electrical power, wherein the electrical machine includes a stator and a rotor; wherein the stator is positioned adjacent to or within the shroud; and wherein the rotor extends from the wheel of the fan blade stage.