Integrated aircraft environmental control and buffer system

A gas turbine engine comprising:

• a fan section delivering air into a main compressor section where the air is compressed and communicated to a combustion section where the air is mixed with fuel and ignited to generate a high energy flow that is expanded through a turbine section that drives the fan and main compressor section;
• and
• an environmental control system including:
• a higher pressure tap to be associated with a higher compression location in the main compressor section, and a lower pressure tap to be associated with a lower pressure location in the main compressor section, said lower pressure location being at a lower pressure than said higher pressure location;
• the lower pressure tap communicating to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor;
• the higher pressure tap leading into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section of the turbocompressor to in turn drive the compressor section of the turbocompressor;
• a turbine outlet receiving airflow exhausted from the turbine section of the turbocompressor;
• a compressor outlet receiving airflow exhausted from the compressor section of the turbocompressor;
• a combined outlet receiving airflow from the turbine outlet and the compressor outlet intermixing airflow and passing the mixed airflow downstream to be delivered to an aircraft;
• and
• a diverter valve controlling airflow from the turbine outlet into the combined outlet for controlling a temperature of airflow in the combined outlet.

An environmental control system for an aircraft comprising:

• a higher pressure tap to be associated with a higher compression location in a main compressor section associated with an aircraft engine, and a lower pressure tap to be associated with a lower pressure location in the main compressor section associated with the aircraft engine, said lower pressure location being at a lower pressure than said higher pressure location;
• the lower pressure tap communicating to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor;
• the higher pressure tap leading into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor;
• a turbine outlet receiving airflow exhausted from the turbine section;
• a compressor outlet receiving airflow exhausted from the compressor section of the turbocompressor;
• a combined outlet receiving airflow from the turbine outlet and the compressor outlet intermixing airflow and passing the mixed airflow downstream to be delivered to an aircraft;
• a diverter valve controlling airflow from the turbine outlet into the combined outlet for controlling a temperature of airflow in the combined outlet;
• a check valve controlling airflow from the lower pressure tap through a bypass passage between the lower pressure tap and the combined outlet;
• a first control valve positioned on the higher pressure tap and is operable to control operation of the turbocompressor, wherein when the first control valve is in an open position, airflow is drawn into the compressor section of the turbocompressor from the lower pressure tap, and when the first control valve is in a closed position, airflow is not drawn through the compressor section of the turbocompressor and passes through the bypass passage;
• and
• a second control valve positioned downstream of a location at which the bypass passage and the combined outlet intermix into a common conduit operable to control airflow through a common conduit to an aircraft system.