Abstract: A shroud cooling system configured to cool a shroud adjacent to an airfoil within a gas turbine engine is disclosed. The turbine engine shroud may be formed from shroud segments that include a plurality of cooling air supply channels extending through a forward shroud support for impingement of cooling air onto an outer radial surface of the shroud segment with respect to the inner turbine section of the turbine engine. The channels may extend at various angles to increase cooling efficiency. The backside surface may also include various cooling enhancement components configured to assist in directing, dispersing, concentrating, or distributing cooling air impinged thereon from the channels to provide enhanced cooling at the backside surface. The shroud cooling system may be used to slow down the thermal response by isolating a turbine vane carrier from the cooling fluids while still providing efficient cooling to the shroud.

Abstract: A shroud cooling system (100) configured to cool a shroud (50) adjacent to an airfoil within a gas turbine engine (10) is disclosed. The turbine engine shroud (50) may be formed from shroud segments (34) that include a plurality of cooling air supply channels (40) extending through a forward shroud support (52) for impingement of cooling air onto an outer radial surface of the shroud segment (34) with respect to the inner turbine section of the turbine engine (10). The channels (40) may extend at various angles (42) to increase cooling efficiency. The backside surface (62) may also include various cooling enhancement components configured to assist in directing, dispersing, concentrating, or distributing cooling air impinged thereon from the channels (40) to provide enhanced cooling at the backside surface (62).

Abstract: A gas turbine engine is provided comprising an outer casing and a plurality of circumferentially positioned vane segments. The outer casing is provided with a circumferential casing slot. The plurality of circumferentially positioned vane segments are coupled to the outer casing. Each vane segment comprises at least one vane airfoil, a radially inner shroud coupled to a first end of the airfoil, a radially outer shroud coupled to a second end of the airfoil, and a strongback fixedly coupled to axially spaced-apart portions of the outer shroud such that a gap is provided between the strongback and the outer shroud. The strongback may comprise axially spaced-apart first and second end portions received in the casing slot.

Abstract: A gas turbine engine is provided comprising an outer casing and a plurality of circumferentially positioned vane segments. The outer casing is provided with a circumferential casing slot. The plurality of circumferentially positioned vane segments are coupled to the outer casing. Each vane segment comprises at least one vane airfoil, a radially inner shroud coupled to a first end of the airfoil, a radially outer shroud coupled to a second end of the airfoil, and a strongback fixedly coupled to axially spaced-apart portions of the outer shroud such that a gap is provided between the strongback and the outer shroud. The strongback may comprise axially spaced-apart first and second end portions received in the casing slot.