Abstract: A turbine airfoil includes a plurality of cooling circuits embedded within the pressure and suction sidewalls and a first and a second flow passage. The first flow passage feeds the coolant fluid to the cooling circuits that are embedded only within the pressure sidewall and the second flow passage feeds the coolant fluid to the cooling circuits that are embedded only within the suction sidewall. A method embodiment of the present comprises placing the inlets of the cooling circuits embedded within the first sidewall in flow communication with only one of the flow passages and placing the inlets of the cooling circuits embedded within the second sidewall in flow communication with at least one of the other flow passages to minimize the difference in sink pressures of the suction and pressure sidewalls to ensure ingestion of the coolant fluid into the inlets of the respective cooling circuits.

Abstract: An improved cooling design and method for cooling airfoils within a gas turbine engine is provided which includes a plenum longitudinally located within the leading edge of the airfoils. Within the plenum are positioned a plurality of turbulence promoters to provide enhance heat transfer within the leading edge. Also, the cooling design includes a plurality of inlets to receive cooling air from an internal cavity of the airfoil as well as a plurality of outlets located within a trench on the exterior surface of the leading edge through which the cooling air exits to film cool leading edge.

Abstract: An improved cooling design and method for cooling airfoils within a gas turbine engine is provided which includes an embedded microcircuit that traverses a tip between a suction sidewall and a pressure sidewall of the airfoil. The microcircuit includes at least on inlet disposed proximate to the tip and one of the sidewalls for receiving cooling air from an internal cooling cavity of the airfoil and at least outlet disposed proximate to the tip through which the cooling air ejects into a region outside the airfoil.

Abstract: A cooling circuit disposed within a first wall portion and a second wall portion of a wall for use in a gas turbine engine is provided. The cooling circuit includes a plurality of inlet apertures disposed in the first wall portion to provide a flow path of cooling air into the cooling circuit, a first exit slot disposed in the second wall portion to provide a cooling air flow path out of the cooling circuit, a plurality of pedestals arranged in rows extending between the first wall portion and the second wall portion and a first elongated pedestal disposed radially and extending between the first and second wall portions. The first elongated pedestal is positioned between the pedestals and the first exit slot.

Abstract: A turbine blade is provided comprising an internal cavity into which cooling air is flowable, an external wall and a first, second and third cooling circuits embedded with the wall. The cooling circuits include inlets that connect each respective cooling circuit with a cavity to provide a cooling air flow path into the respective cooling circuit. The cooling circuits also include an exit aperture that provides a cooling air flow path out of the respective cooling circuits. The cooling circuits are configured to increase the temperature of the cooling air as it travels from the inlet to the exit aperture. In the exemplary embodiment, the inlets are aligned with the direction of counter-rotating flow circulations experienced by the inner surface of the wall caused by Coriolis flow effects on the cooling air flowing inside the cavity.

Abstract: An annular combustor suitable for use in a gas turbine engine having a plurality of fuel injectors and a plurality of apertures circumferentially arranged within the inner and outer liners of the combustion chamber is disclosed. Further, each of the apertures of the inner liner are disposed on one side of the centerline of each of the fuel injectors and each of the apertures of the outer liner are disposed on the opposing side of the centerline of each of the fuel injectors. In this way, air exhausted from the apertures advantageously opposes the direction of swirl of the fuel and air mixture that is injected from the fuel injectors thereby providing enhanced mixing of the fuel and air within the combustion chamber, increased residence time and the reduction of hot streaks in the inner and outer liners.

Abstract: A turbine airfoil section having an internal cavity and a plurality of indentations on the inner surface of the internal cavity is described. The indentations provide enhanced heat transfer for cooling the internal cavity of an airfoil thereby improving the life of the airfoil and optimizing the efficiency of the engine by minimizing the amount of compressor bleed air required. Advantageously, this cooling scheme also does not restrict the cooling flow within the internal cavity. The indentations may have varying patterns and alternative geometric configurations.

Abstract: The present invention provides a reliable regulating device that permits liquids, such as fuel oils, to be drained into the enclosure while preventing the flow of gases into the enclosure. The device includes a valve housing having a chamber for receiving the liquids and the gases and a drain valve means in open flow communication with the liquids and gases. The drain valve means includes a valve seat and a float member both located within the valve housing. The float member has a specific gravity less than the liquids passing through the device. The float member floats off the valve seat when the liquids flow through the valve housing and engages the valve seat when gases are present in the chamber preventing the gases from entering the enclosure.