Patent ID: 8820092
Filing Date: 2014-09-02
Classification: F01D,F02C,F05D,Y02T

Abstract:
1. A method of operating a gas turbine engine, comprising: a. supplying at least a first portion of fuel to a rotatable portion of the gas turbine engine, wherein said rotatable portion comprises a rotor and at least one blade operatively coupled to or a part of said rotor; b. cooling at least one of said rotor or at least one said at least one blade with said first portion of said fuel supplied to said rotatable portion, wherein said at least one said blade is closed at its tip and lateral surfaces with respect to a combustion chamber of said gas turbine engine relative to said fuel supplied to said at least one said blade, and the operation of cooling provides for transforming said first portion of said fuel to a vapor or gaseous state; and c. discharging said first portion of said fuel from an orifice of and rotating with said rotatable portion directly into said combustion chamber of said gas turbine engine, wherein when discharged from said orifice of and rotating with said rotatable portion directly into said combustion chamber of said gas turbine engine, said first portion of said fuel is in said vapor or gaseous state.