HEAT EXCHANGER MOUNTED AT REAR OF GAS TURBINE ENGINE FOR CHALLENGING TEMPERATURE APPLICATIONS

A gas turbine engine (100) has a fan rotor (87) delivering air into a bypass duct defined between an outer fan case (94) and an outer interior housing. The fan rotor (87) also delivers air into a compressor section (77,79), a combustor (106), a turbine section (108H,108L). A chamber (97) is defined between the outer interior housing and an inner housing (113). The inner housing (113) contains the compressor section (77,79), the combustor (106) and the turbine section (108H,108L). A first conduit (110) taps hot compressed air to be cooled and passes the air to at least one heat exchanger (102). The air is cooled in the heat exchanger (102) and returned to a return conduit (112). The return conduit (112) passes the cooled air to at least one of the turbine section (108H,108L) and the compressor section (77,79). The heat exchanger (102) has a core exhaust plane (86). The turbine section (108H,108L) has at least a first and a downstream second rotor blade row (80,82), with the core exhaust plane (86) located downstream of a center plane (88) of the second blade row (82).