Patent ID: 9163562
Filing Date: 2015-10-20
Classification: F01D,F02C,F02K,Y02T

Abstract:
1. A gas turbine engine comprising: a fan configured to produce propulsive thrust from a fan discharge air stream, a bypass duct located between a cowl and an engine core, said bypass duct fluidly coupled to said fan; an impeller pump positioned on said engine core, said impeller pump having an intake manifold fluidly coupled to said bypass duct and configured to intake a portion of said fan discharge air stream, said impeller pump having an outlet coupled to an outlet duct fluidly coupled to an environmental control system, wherein said impeller pump is configured to raise pressure of said portion of said fan discharge air stream and pump said portion of said fan discharge air stream into said environmental control system for cooling; an integrated drive pump connected to said impeller pump for driving said impeller pump at a constant speed, said integrated drive pump being positioned on said engine core, said integrated drive pump being connected to a towershaft opposite said impeller pump for driving said integrated drive pump.