Abstract: A gas turbine engine thermal control apparatus includes at least one annular spray tube having spray holes oriented to impinge thermal control air onto a fillet between an outer casing and a forward thermal control ring and, in a more particular embodiment, into a center of the fillet. The apparatus may include an annular segmented stator shroud attached to the outer casing and circumscribing radial outer blade tips of turbine blades of a turbine rotor. A thermal air distribution manifold encircling a portion of the outer casing includes an annular supply tube connected in fluid supply relationship to plenums of header assemblies. The annular spray tube is connected to at least one of the plenums and may be elongated radially inwardly and axially. Baffles attached to radially outwardly facing surfaces of the panels may be contoured to form exhaust passages having exhaust passage inlets and outlets between the baffles and the panels.

Abstract: An exemplary thermal air exhaust system includes circumferentially extending exhaust passages to exhaust thermal control air from an annular region between an outer casing and a distribution manifold encircling an axially extending portion of the casing after the thermal control air has been sprayed on at least one thermal control ring attached to the outer casing and/or onto the outer casing by spray tubes with spray holes. Baffles attached to base panels of the distribution manifold and contoured to form the exhaust passages between the baffles and base panels. The exhaust passages having exhaust passage inlets formed by radially facing exhaust holes through the baffles and exhaust passage outlets formed by circumferentially facing exhaust passage outlets between the baffles and the base panels. Thermal control air is sprayed on at least one thermal control ring and/or onto the outer casing and then circumferentially exhausted through the exhaust passages.