Electro-pneumatic environmental control system air circuit
An engine driven environmental control system (ECS) air circuit includes a gas turbine engine having a compressor section. The compressor section includes a plurality of compressor bleeds. A selection valve selectively connects each of said bleeds to an input of an intercooler. A second valve is configured to selectively connect an output of said intercooler to at least one auxiliary compressor. The output of each of the at least one auxiliary compressors is connected to an ECS air input.
1. An engine driven environmental control system (ECS) air circuit comprising:
a gas turbine engine including a compressor section having a low pressure compressor section and a high pressure compressor section downstream of the low pressure compressor section, the compressor section including a plurality of compressor bleeds, wherein the plurality of compressor bleeds includes a first bleed positioned at a location between the low pressure compressor and the high pressure compressor, a second bleed positioned at a third stage of the high pressure compressor, a third bleed positioned at a sixth stage of the high pressure compressor, and a fourth bleed positioned at an eighth stage of the high pressure compressor;
a selection valve selectively connecting each bleed of said plurality of compressor bleeds to an input of an intercooler; and
a second valve configured to selectively connect an output of said intercooler to at least one auxiliary compressor, the output of every auxiliary compressor of the at least one auxiliary compressors being connected to an ECS air input.
2. The engine driven ECS air circuit of claim 1 , wherein the at least one auxiliary compressor comprises a plurality of auxiliary compressors.
3. The engine driven ECS air circuit of claim 1 , wherein the intercooler is an air to air heat exchanger.
4. The engine driven ECS air circuit of claim 3 , wherein a heat sink of the air to air heat exchanger is fan air.
5. The engine driven ECS air circuit of claim 1 , further comprising an aircraft controller controllably connected to the selection valve and to the second valve such that the aircraft controller controls a state of the selection valve and a state of the second valve.
6. The engine driven ECS air circuit of claim 5 , wherein the aircraft controller includes a memory storing instructions configured to cause the controller to connect a bleed of the plurality of compressor bleeds having a required flowrate for an ECS operating requirement, and wherein the connected bleed of the plurality of compressor bleeds has a pressure requirement below a pressure requirement of the ECS inlet.
7. The engine driven ECS air circuit of claim 5 , wherein the at least one auxiliary compressor comprises a plurality of auxiliary compressors and wherein the aircraft controller includes a memory storing instructions configured to cause the controller to alternate auxiliary compressors operating as a primary compressor such that the primary compressor is alternated between each flight.
8. The engine driven ECS air circuit of claim 1 , wherein at least one of said at least one auxiliary compressors includes an electric motor, and wherein the electric motor is configured to drive rotation of the corresponding auxiliary compressor.
9. The engine driven ECS air circuit of claim 1 , wherein at least one of said at least one auxiliary compressor includes a mechanical motor, and wherein the mechanical motor is configured to drive rotation of the corresponding auxiliary compressor.