| abstract |
A turbine exhaust case (28) for a gas turbine engine (10) comprises a frame (100), a vane fairing (108), a heat shield (124, 126, 128), and a serpentine cooling path. The frame has an outer ring (102) and an inner ring (104) connected by a hollow strut (106) with a radial service line passage (132). The vane fairing is disposed between the inner ring and the outer ring to define a core airflow path. The heat shield is disposed between the vane fairing and the frame. The serpentine cooling flow path passes through and around the outer ring, the inner ring, and the plurality of struts |