Secondary power integrated cabin energy system for a pressurized aircraft
AssigneeHamilton Sundstrand Corporation
InventorRobert George Thompson
Life of this patent
Estimating the term…
Abstract
Increased efficiency of operation in pressurized aircraft may be obtained by employing pressurized air to be discharged from an aircraft cabin 10 as combustion air by applying it to the inlet 42 of a cycle compressor 40 whereat it is compressed before being fed to a combustor 52. Fuel from a source 64 is combusted within the combustor 52 and drives a high pressure turbine 48 as well as a low pressure turbine 30, either one of which may drive a load 56, 58 to provide electrical power for the aircraft. In addition, a load compressor 20 provides air to an environmental control system including an ECS turbo machine 88 and a bypass 110 for delivering conditioned air to the cabin 10.
Claims17
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 compressor
- first 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;
- and
- third ducting connecting an outlet of said high pressure turbine wheel to an inlet for said low pressure turbine wheel.
A secondary power integrated cabin energy system for an aircraft, comprising:
- 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, said second shaft being concentric about said first shaft;
- 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 compressor
- a first ducting adapted to connect an outlet of said load compressor to an aircraft cabin to provide compressed air to pressurize the cabin;
- second ducting adapted to connect an aircraft cabin to an inlet of said cycle compressor;
- and
- third ducting connecting an outlet of said high pressure turbine wheel to an inlet for said low pressure turbine wheel.
A secondary power integrated cabin energy system for an aircraft, comprising:
- a turbomachine including a rotary compressor connected by a shaft to a rotary turbine wheel and a combustor connected to an outlet of said compressor, to a source of fuel to be combusted to provide gases of combustion and to an inlet to said turbine wheel so that said gases of combustion may drive said turbine wheel to, in turn, drive said compressors;
- an inlet to said compressor;
- ducting adapted to be connected to an aircraft cabin and to said compressor inlet to provide air from said cabin to said compressor to be compressed thereby and delivered to said combustor to combust fuel therein;
- a load to be driven connected to said turbomachine;
- and
- a source of air under pressure adapted to be connected to an aircraft cabin, said source of air under pressure including a second rotary compressor coupled by a second shaft to a second rotary turbine wheel.
Dependencies are inferred from the claim text.