Abstract: In accordance with an exemplary embodiment, disclosed is an air-cooled turbine blade having an airfoil shape, including a convex suction side wall, a concave pressure side wall, the walls including an interior surface that defines an interior with the blade, a suction side flow circuit formed within the blade interior, a pressure side flow circuit formed within the blade interior; and a trailing edge pin bank positioned aft of the suction side and pressure side flow circuits. The turbine blade includes a wishbone-shaped architecture at a transition point between the suction side flow circuit and the pressure side flow circuit and the trailing edge pin bank.

Abstract: An airfoil is provided for a gas turbine engine. The airfoil includes a pressure side wall; a suction side wall; an internal cavity defined between the pressure side wall and the suction side wall for receiving cooling air; and a cooling arrangement within the internal cavity. The cooling arrangement includes a first land extending to a first downstream end aft of the pressure side trailing edge, a second land extending to a second downstream end aft of the pressure side trailing edge, the first land and second land defining a first slot, a first divider positioned radially in between the first land and the second land to define a first passageway of the first slot and a second passageway of the first slot, a first pin positioned upstream and indexed to the first passageway, and a second pin positioned upstream and indexed to the second passageway.

Abstract: An airfoil is provided for a gas turbine engine. The airfoil includes a pressure side wall; a suction side wall; an internal cavity defined between the pressure side wall and the suction side wall for receiving cooling air; and a cooling arrangement within the internal cavity. The cooling arrangement includes a first land extending to a first downstream end aft of the pressure side trailing edge, a second land extending to a second downstream end aft of the pressure side trailing edge, the first land and second land defining a first slot, a first divider positioned radially in between the first land and the second land to define a first passageway of the first slot and a second passageway of the first slot, a first pin positioned upstream and indexed to the first passageway, and a second pin positioned upstream and indexed to the second passageway.

Abstract: A combustor for a gas turbine engine includes an inner liner and an outer liner circumscribing the inner liner and forming a combustion chamber with the inner liner. The outer liner is a dual walled liner with a first wall and a second wall. The combustor includes a fuel igniter comprising a tip portion configured to ignite an air and fuel mixture in the combustion chamber and an igniter tube positioning the fuel igniter relative to the combustion chamber. The igniter tube includes a plurality of holes configured to direct cooling air toward the tip portion of the fuel igniter.

Abstract: A dual wall structure for a combustor of a gas turbine engine including an inner liner and an outer liner coupled to a combustor dome and defining a combustion chamber there between. Each of the inner liner and the outer liner include an outer wall and an inner wall. Each of the outer walls includes a plurality of impingement holes formed therein for allowing a coolant to flow therethrough. Each of the inner walls is coupled to the outer wall and a combustor dome and includes a plurality of heat shield panels. Each of the plurality of heat shield panels extends a longitudinal length of the combustor chamber and includes a plurality of side rails, an aft rail and a forward flange that when coupled to the outer wall defines a single cavity there between. A plurality of cavities being formed by the plurality of heat shield panels.