Hybrid Electric Power Dependent Active Clearance Control

A system for an aircraft, comprising:

• an active clearance control (ACC) system configured to control a clearance between a tip of a rotating blade and a case structure by controlling thermal growth of the case structure;
• a hybrid electric propulsion (HEP) system that includes a gas turbine engine and an electric motor configured to assist the gas turbine engine by rotating a first shaft of the gas turbine engine;
• and
• a controller configured to:
• receive a throttle command;
• determine, based on an amount of electric power available to the electric motor:
• a power allocation between the gas turbine engine and the electric motor for an acceleration period during which a rotational speed of the first shaft of the gas turbine is accelerated to implement the throttle command, wherein the first shaft is part of a low pressure spool of the gas turbine engine or a high pressure spool of the gas turbine engine;
• and
• a target clearance between a tip of a rotor blade and a case structure for the acceleration period;
• and
• during the acceleration period, implement the power allocation and operate the ACC system to establish the target clearance.

A method for a hybrid electric propulsion (HEP) system, comprising:

• receiving a throttle command for a hybrid electric propulsion (HEP) system, the HEP system includes a gas turbine engine and an electric motor configured to assist the gas turbine engine by rotating a first shaft of the gas turbine engine;
• based on the throttle command and an amount of electric power available to the electric motor, determining a target clearance between a tip of a rotor blade and a case structure;
• and
• implementing the power allocation and operating an active clearance control (ACC) system to establish the target clearance.