Intercooled cooling air with auxiliary compressor control

An intercooling system for a gas turbine engine comprising:

• a heat exchanger for cooling air drawn from a portion of a main compressor section at a first temperature and pressure for cooling the air to a second temperature cooler than the first temperature;
• a cooling compressor compressing air communicated from the heat exchanger to a second pressure greater than the first pressure and communicating the compressed air to a portion of a turbine section;
• and
• said cooling compressor rotating at a speed proportional to a speed of at least one rotor in said turbine section, and said cooling compressor being allowed to rotate at a speed that is not proportional to a speed of said at least one rotor under certain conditions.

A gas turbine engine comprising;

• a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations, a low pressure compressor providing some of said more upstream locations;
• a turbine section having a high pressure turbine;
• and
• a tap tapping air from at least one of said more upstream locations in said compressor section, passing said tapped air through a heat exchanger and then to a cooling compressor, said cooling compressor compressing air downstream of said heat exchanger, and delivering air into said high pressure turbine.