Patent ID: 6351940
Filing Date: 2002-03-05
Classification: F02C,F02K,F04D,F05D,Y02T

Abstract:
A ducting system for use on a gas turbine engine having two fans connected to a common shaft, said ducting system comprising:a primary inlet duct and a plurality of primary discharge ducts, each of said primary discharge ducts is integral with said primary duct, said primary inlet duct having a circular primary inlet port located at one end thereof distant from said primary discharge ducts, and each of said primary discharge ducts having a primary discharge port located at one end thereof distant from said primary inlet duct; a plurality of secondary inlet ducts and a single secondary discharge duct, each of said secondary inlet ducts is integral with said secondary discharge duct, each of said secondary inlet ducts having a secondary inlet port located at one end thereof distant from said secondary discharge duct, and said secondary discharge duct having a circular secondary discharge port located at one end thereof distant from said secondary inlet ducts; a reference axis; wherein the center of the circular primary inlet port and the center of the circular secondary discharge port are both located on said reference axis, said secondary inlet ports are located radially outward of said circular primary inlet port relative to said reference axis, and said primary discharge ports are located radially outward of said circular secondary discharge port relative to said reference axis; and wherein the flow are of the primary inlet duct is constant along the length thereof, the flow area of each of the primary discharge ducts is constant along the length thereof, and the flow area of each of the primary discharge ports is equal to one-fourth of the flow area of the circular primary inlet port.