Patent ID: 7574867

Claim:
A gas turbine engine for generating electricity, comprising: an engine body; a first rotor spool with an axis of rotation within said engine body, said first rotor spool having a first bladed compressor rotor with an air inlet and exit, a first compressor rotor shaft and a first bladed turbine rotor with a gas inlet and exit; a second rotor spool with an axis of rotation perpendicular to the first rotor spool axis of rotation within said engine body, said second rotor spool having an integral alternator rotor with retained permanent magnets, a second bladed compressor rotor having an air inlet and exit and a second bladed turbine rotor having a gas inlet and exit; an electrical stator within said engine body having electrical wire, laminates of magnetically attracted material, said stator is coaxial with and in close proximity to said alternator rotor where relative rotation to said stator inner diameter causes flux change and subsequent electricity generation within said wires; a combustion system within said engine body receives compressor discharge air from said second bladed compressor rotor exit for combusting supplied fuel and delivering combusted gas energy to the second bladed turbine rotor; an air intake in said engine body with communication to said first compressor inlet; the first turbine having a gas discharge duct within said engine body having fluid communication with said first turbine rotor exit; a first ducting means to deliver said first compressor rotor exit pressurized air flow to the inlet of said second compressor rotor inlet; a second ducting means to deliver said second turbine rotor exiting gas energy to said first turbine rotor inlet; wherein said first ducting means induces a preswirl to the second compressor rotor inlet by one of a scroll volute shaped duct or by providing an air flow control plate inside the duct.