An apparatus and method of cooling a gas turbine engine (10) including a core (44) with a compressor section (22) in which the compressor section (22) includes a closed loop cooling circuit (84) having a pump (86), at least one heat pipe (94) extending from at least one of the stationary vanes (60, 62), a heat exchanger (76) located within the bypass air flow (47), and a coolant conduit (90) passing fluidly coupled to the pump (86) and heat exchanger (76) and passing by the heat pipe (94). The pump (86) pumps coolant (98, 100, 114) through the coolant conduit (90) to draw heat from the heat pipes (94) into the coolant (98, 100, 114) to form heated coolant (100), the heated coolant (100) then passes through the heat exchanger (76), where the heat is rejected from the coolant (98, 100, 114) to the bypass air (47) to cool the coolant (98, 100, 114) to form cooled coolant (98), which is then returned to the heat pipes (94).
