Abstract: An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities (16) having an insert (18) contained therein that forms nearwall cooling channels (20) having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels (20) may be controlled via a plurality of cooling fluid flow controllers (22) extending from the outer wall (24) forming the generally hollow elongated airfoil (26). The cooling fluid flow controllers (22) may be collected into spanwise extending rows (28), and the internal cooling system (14) may include one or more bypass flow reducers (30) extending from the insert (18) toward the outer wall (24) to direct the cooling fluids through the channels (20) created by the cooling fluid flow controllers (22), thereby increasing the effectiveness of the internal cooling system (14).

Abstract: An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities (16) having an insert (18) contained therein that forms nearwall cooling channels (20) having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels (20) may be controlled via a plurality of cooling fluid flow controllers (22) extending from the outer wall (24) forming the generally hollow elongated airfoil (26). The cooling fluid flow controllers (22) may be collected into spanwise extending rows (28), and the internal cooling system (14) may include one or more bypass flow reducers (30) extending from the insert (18) toward the outer wall (24) to direct the cooling fluids through the channels (20) created by the cooling fluid flow controllers (22), thereby increasing the effectiveness of the internal cooling system (14).

Abstract: A turbine airfoil (10) usable in a turbine engine and having an internal cooling system (14) with a leading edge impingement channel (16) for enhanced cooling of the leading edge (18) of the turbine airfoil (10) without a leading edge film cooling showerhead array is disclosed. The internal cooling system (14) may include an leading edge cooling supply channel (20) formed from a leading edge wall (22) having a leading edge tip (24) that is advanced closer to an inner surface (26) of the leading edge (18) of the generally elongated, hollow airfoil (28) than other aspects of the leading edge cooling supply channel (20). The leading edge cooling supply channel (20) may include leading edge impingement orifices (30) for directing cooling fluids to impinge on the inner surface (26) of the leading edge (18) of the airfoil (28).

Abstract: A cooling system (10) positioned within a turbine airfoil (12) useable in a turbine engine and having cooling channels (16) positioned within a platform (18) of the turbine airfoil (12) with exhaust outlets (20) at the pressure and suction side edges (22, 24) to prevent hot gas ingestion under the platform (18) is disclosed. The cooling channels (16) may be formed from main channels (26) extending from cooling fluid supply channels (64) aligned with the airfoil (12) and branch channels (30) extending between the main channels (26) and the pressure or suction side edges (22, 24). The cooling system (10) reduces the cooling surface area adjacent to the airfoil fillet (32) at the intersection (34) of the platform (18) and airfoil (12) and increases cooling surface area adjacent to the pressure side and suction side mate faces (22, 24) as compared with conventional designs.

Abstract: An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, and a cooling system. The outer wall has a leading edge, a trailing edge, a pressure side, a suction side, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall, extends generally radially between the inner and outer ends of the outer wall, and receives cooling fluid for cooling the outer wall. The cooling system receives cooling fluid from the cooling fluid cavity for cooling the trailing edge portion of the outer wall and includes a cooling fluid chamber defined by opposing first and second sidewalls that include respective alternating angled sections that provide the cooling fluid chamber with a zigzag shape.

Abstract: An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, and a cooling system. The outer wall has a leading edge, a trailing edge, a pressure side, a suction side, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall, extends generally radially between the inner and outer ends of the outer wall, and receives cooling fluid for cooling the outer wall. The cooling system receives cooling fluid from the cooling fluid cavity for cooling the trailing edge portion of the outer wall and includes a cooling fluid chamber defined by opposing first and second sidewalls that include respective alternating angled sections that provide the cooling fluid chamber with a zigzag shape.

Abstract: A method and system for determining organic matter in an aqueous solution including an oxidizing agent are disclosed. The method includes contacting the solution with a semiconductor which is capable of photocatalytically oxidizing the organic matter, illuminating the semiconductor with light of a wavelength or having a spectrum whereby the semiconductor photocatalytically oxidizes the organic matter in the solution to form a photocatalytic by-product(s), and detecting the by-product(s).

Abstract: A Technetium-99m generator has a matrix having a compound of molybdenum-99 bound into or forming the matrix, the compound of the molybdenum-99 being substantially insoluble in an eluant which can be used in a radiopharmaceutical and the molybdenum compound permitting diffusion of technetium-99m therethrough and elution therefrom. The molybdenum compound can be a monomolybdate, an isopolymolybdate or a heteropolymolybdate and zirconium molybdate is preferred although other cation molybdates may be used. Methods of preparation of the generator include dissolving irradiated molybdenum trioxide in alkaline solution and precipitating the molybdate at a selected pH and packing the precipitate in finely divided form into a column. Alternatively the generator may be formed from a non-radioactive, molybdenum compound and activated later when desired by passing a solution of a compound of molybdenum-99 through the column.

Abstract: A generator for liquid containing .sup.99m Tc has an adsorbant bed of alumina, zirconia or the like and has associated therewith a quantity of an electron scavenging compound of a rare earth, silver or gold so as to maintain elution efficiency during the working life of the generator. The compound may be a rare earth oxide such as ceric oxide typically present as a coating on alumina particles in an amount of about 0.1% by weight or a compound such as silver chloride present in quantities typically of about 5%. The eluant may be sodium or potassium perchlorate in water.

Abstract: An hydraulic system comprising a displacement-type hydraulic element in communication with a sealed reservoir tank for receiving hydraulic fluid from and returning hydraulic fluid to the reservoir, and a stabilizer for preventing excessive vacuum and pressure from forming within the reservoir as fluid is moved into and out of the same. The stabilizer is carried within the reservoir tank and has a bellows construction for compensating for change of volume in the reservoir as fluid changes take place therein, and the stabilizer is vented to the atmosphere through a breather system constructed to minimize entrance of dirt and the like within the stabilizer.