Patent ID: 9103280
Filing Date: 2015-08-11
Classification: F01D,F02C,F02K,F05D,Y02T

Abstract:
1. A method of propelling an aircraft having an integrated turbine and a plurality of high Mach aircraft engines disposed about the integrated turbine, the integrated turbine defining a center shaft and a generally circular turbine intake face, the method comprising: positioning a translatable cylindrical air duct upstream of the turbine and high Mach aircraft engines, the cylindrical air duct being axially translatable with respect to the center shaft and positioned upstream of the turbine intake face; and axially translating the cylindrical air duct from a first position wherein the aft end of the cylindrical duct is positioned forward of the plurality of high Mach engines, such that airflow through the cylindrical air duct is communicated to both the turbine and the plurality of high Mach aircraft engines to generate a thrust on the aircraft in a first propulsion mode, to a second position wherein the aft end of the cylindrical air duct substantially abuts the outer circumference of the turbine intake face such that air flow through the cylindrical air duct is communicated only to the turbine to generate a thrust on the aircraft in a second propulsion mode.