Integrated fuel cell aircraft pressurization and cooling system

An integrated fuel cell and environmental control system comprising:

• a first turbo-compressor comprising:
• a rotatable shaft;
• a compressor rotatable with the shaft to generate a flow of compressed air;
• a motor connected to the shaft;
• and
• a turbine connected to the shaft;
• a second turbo-compressor comprising:
• a rotatable shaft;
• a compressor rotatable with the shaft to generate a second flow of compressed air;
• a motor connected to the shaft;
• and
• a turbine connected to the shaft;
• wherein the motor of the second turbo-compressor is connected to the fuel cell by a cable and draws a load of electrical power from the fuel cell;
• a fuel cell connected to the compressor by a first compressed air supply line that supplies a first portion of the flow of compressed air to the fuel cell, wherein the fuel cell is connected to the first turbine by a first fuel cell exhaust line that supplies a flow of fuel cell exhaust to the first turbine and causes the first turbine to rotate, and wherein the fuel cell is connected to the second turbine by a second fuel cell exhaust line;
• an environmental control system connected to the compressor by a second compressed air supply line that supplies a second portion of the flow of compressed air to the environmental control system;
• and
• a third compressed air supply line for transporting a first portion of the second flow of compressed air to the fuel cell.

An integrated fuel cell and environmental control system comprising:

• a first turbo-compressor comprising:
• a rotatable shaft;
• a compressor rotatable with the shaft to generate a flow of compressed air;
• a motor connected to the shaft;
• and
• a turbine connected to the shaft;
• a second turbo-compressor comprising:
• a rotatable shaft;
• a compressor rotatable with the shaft to generate a second flow of compressed air;
• a motor connected to the shaft;
• and
• a turbine connected to the shaft;
• a fuel cell connected to the compressor by a first compressed air supply line that supplies a first portion of the flow of compressed air to the fuel cell, wherein the fuel cell is connected to the first turbine by a first fuel cell exhaust line that supplies a flow of fuel cell exhaust to the first turbine and causes the first turbine to rotate, and wherein the fuel cell is connected to the second turbine by a second fuel cell exhaust line;
• an environmental control system connected to the compressor by a second compressed air supply line that supplies a second portion of the flow of compressed air to the environmental control system;
• and
• a third compressed air supply line for transporting a first portion of the second flow of compressed air to the fuel cell;
• and
• a second environmental control system connected to the compressor of the second turbo-compressor by a fourth compressed air supply line.

A method for powering a system comprising:

• supplying a compressor with a flow of air;
• producing a flow of compressed air in the compressor;
• supplying a first portion of the flow of compressed air to a fuel cell;
• supplying a second portion of the flow of compressed air to an environmental control system;
• pressurizing the second portion of the flow of compressed air in the environmental control system for use in an aircraft cabin and flight deck;
• producing electrical power in the fuel cell;
• and
• supplying a flow of exhaust gas from the fuel cell to a turbine connected to the compressor by a shaft.