System for controlling blade clearances within a gas turbine engine

A system for controlling blade tip clearances within a gas turbine engine, the gas turbine engine defining an axial centerline and a radial direction extending orthogonal to the axial centerline, the system comprising:

• an inner rotor configured to rotate in a first direction;
• an inner rotor blade coupled to the inner rotor;
• an outer rotating drum configured to rotate in a second direction opposite of the first direction;
• an outer rotor blade coupled to the outer rotating drum;
• a heat exchanger configured to receive a first flow of cooling air bled from the gas turbine engine and transfer heat from the received flow of the cooling air to a flow of coolant to generate cooled cooling air;
• a first air valve configured to direct a first portion of the cooled cooling air to the outer rotating drum and a second portion of the cooled cooling air to cool the inner rotor;
• and
• a second air valve configured to direct a first portion of a second flow of the cooling air to the outer rotating drum and a second portion of the second flow of the cooling air to cool the inner rotor,
• wherein the cooled cooling air is supplied to at least one of the outer rotating drum or the inner rotor to adjust a first clearance defined between the inner rotor blade and the outer rotating drum and a second clearance between the outer rotor blade and the inner rotor.