Patent ID: 6283410
Filing Date: 2001-09-04
Classification: B64D,F05B,Y02T

Abstract:
A secondary power integrated cabin energy system for an aircraft, comprising:an aircraft cabin;a low pressure rotary turbo machine including a rotary load compressor connected by a first shaft to a rotary, low pressure turbine wheel;a high pressure rotary turbo machine including a rotary cycle compressor connected by a second shaft to a rotary high pressure turbine wheel;a combustor connected to an outlet of said cycle compressor and a source of fuel for combusting fuel to generate combustion gases and direct them to said high pressure turbine wheel to cause rotation of the same;an ambient air inlet for said load compressorfirst ducting connecting an outlet of said load compressor to said cabin to provide compressed air to pressurize said cabin;second ducting connecting said cabin to an inlet of said cycle compressor; andthird ducting connecting an outlet of said high pressure turbine wheel to an inlet for said low pressure turbine wheel.