Patent ID: 8206088
Filing Date: 2012-06-26
Classification: B64D,F02C,Y02T

Abstract:
1. A method for providing a flow control system for an aircraft by converting an air cycle machine on the aircraft having a heat exchanger with a primary stage and a secondary stage, a compressor connected to the heat exchanger by a compressor ducting section, a turbine connected to the heat exchanger by an upstream turbine duct, and a downstream turbine duct connected to the turbine, the method comprising the steps of: removing the compressor; removing the compressor ducting from a primary stage outlet of the heat exchanger and a secondary stage inlet of the heat exchanger; providing a first connector duct; connecting the primary stage outlet of the heat exchanger to the first connector duct; connecting the secondary stage inlet of the heat exchanger to the connector duct such that air may travel from the primary stage of the heat exchanger directly to the secondary stage inlet of the heat exchanger by way of the first connector duct; removing the turbine; providing a second connector duct; and connecting the upstream turbine duct directly to the downstream turbine duct using the second connector duct.