Conditioned low pressure compressor compartment for gas turbine engine

A gas turbine engine, comprising:

• a combustor;
• and
• a compressor to provide a compressed airflow to the combustor, the compressor including:
• a high pressure compressor;
• and
• a low pressure compressor including:
• a low pressure compressor case extending circumferentially around a central axis of the gas turbine engine, including:
• an inner radial wall surrounding a low pressure compressor rotor;
• and
• an outer radial wall at least partially defining a fan bypass passage of the gas turbine engine;
• and
• a low pressure compressor compartment disposed between the inner radial wall and the outer radial wall;
• an electrical component disposed in the low pressure compressor compartment;
• and
• an inlet port at the outer radial wall configured to admit a cooling airflow into the low pressure compressor compartment from the fan bypass passage to cool the electrical component.

A method of operating a gas turbine engine, comprising:

• flowing an airflow through a fan portion of the gas turbine engine and along a fan bypass passage;
• directing a portion of the airflow through an inlet port of a low pressure compressor case and into a low pressure compressor compartment, the low pressure compressor compartment defined by an inner radial wall and an outer radial wall of the low pressure compressor;
• flowing the airflow across an electrical component disposed in the low pressure compressor compartment;
• and
• cooling the electrical component via a thermal energy exchange between the airflow and the electrical component.