Abstract: An improved cooling passage configuration for a gas turbine engine airfoil is disclosed for enhancing convective cooling over that afforded by conventional wall turbulator ribs. An internal cooling passage bounded by pressure and suction side walls and at least one partition has raised turbulator ribs disposed on at least one side wall and the partition. A side wall turbulator rib extends over at least a portion of the side wall and abuts the partition. A turbulator rib disposed on the partition extends from a point spaced from the wall rib to the opposed side wall. The gap formed between the partition rib and wall rib accelerates a coolant flow passing therethrough, locally enhancing convective heat transfer. Partition ribs may be aligned with or offset from the wall ribs in the spanwise direction and may be normal to the primary direction of cooling flow or angled thereto.

Abstract: A pulse-cooled gas turbine engine assembly includes a hollow airfoil and a fluidic oscillator joined thereto. The fluidic oscillator discharges pressurized cooling air inside the airfoil at a predetermined pulsation frequency for cooling the airfoil.

Abstract: A cooling system 24 for an electrochemical cell stack 12 is disclosed. Various construction details which avoid plugging of the cooling system during long term operation with a cooling fluid having dissolved species and suspended particles, such as water, are discussed. The cooling system includes spaced apart cooler assemblies 30. Conduits 32 for supplying cooling fluid to the cooler assemblies include sets of cooling tubes 74 in serial flow communication.