Abstract: A split volute for a centrifugal pump is disclosed that provides a manufacturing advantage by improving the yield of high-chrome iron casting, providing for full surface coating capability using line-of-sight spray coating systems. Performance improvements include improved pump efficiency, abrasion resistance, and volute lifetime. Additional operational cost savings are enabled through reduced time required for common volute maintenance procedures and an increased replacement interval for the volute. Taken together, these advantages reduce the total cost of ownership of the split volute pump system.

Abstract: A split volute for a centrifugal pump is disclosed that provides a manufacturing advantage by improving the yield of high-chrome iron casting, providing for full surface coating capability using line-of-sight spray coating systems. Performance improvements include improved pump efficiency, abrasion resistance, and volute lifetime. Additional operational cost savings are enabled through reduced time required for common volute maintenance procedures and an increased replacement interval for the volute. Taken together, these advantages reduce the total cost of ownership of the split volute pump system.

Abstract: A split volute for a centrifugal pump is disclosed that provides a manufacturing advantage by improving the yield of high-chrome iron casting, providing for full surface coating capability using line-of-sight spray coating systems. Performance improvements include improved pump efficiency, abrasion resistance, and volute lifetime. Additional operational cost savings are enabled through reduced time required for common volute maintenance procedures and an increased replacement interval for the volute. Taken together, these advantages reduce the total cost of ownership of the split volute pump system.

Abstract: An aircraft air system includes a gas turbine engine, a bleed air duct directing compressed air bled from a compressor to an inner compartment within the aircraft, and an air contamination detector located downstream of the gas turbine engine compressor. The air contamination detector includes a visual indicator which detects the presence of a fluid contaminant within the bleed air.

Abstract: An aircraft air system includes a gas turbine engine, a bleed air duct directing compressed air bled from a compressor to an inner compartment within the aircraft, and an air contamination detector located downstream of the gas turbine engine compressor. The air contamination detector includes a visual indicator which detects the presence of a fluid contaminant within the bleed air.

Abstract: A tangential on board injector with auxiliary supply of further cooled compressed air, from an external heat exchanger or air cooled bearing gallery for example, serves to reduce the volume of cooling air directed tangentially toward a cooled rotor of a gas turbine engine. The tangential on board injector has an array of injector blades between two injector walls defining circumferential main flow nozzles for directing a main compressed air flow tangentially. Each blade has an interior chamber in flow communication with a source of auxiliary compressed air with at least one bore extending between the chamber and an exterior surface of the blade. The bores eject further cooled air from the heat exchanger and merge with the primary compressed air flowing through the injector nozzles. The bores may also produce a cooling film of air that reduces drag over the injector blades.

Abstract: A tangential on board injector with auxiliary supply of further cooled compressed air, from an external heat exchanger or air cooled bearing gallery for example, serves to reduce the volume of cooling air directed tangentially toward a cooled rotor of a gas turbine engine. The tangential on board injector has an array of injector blades between two injector walls defining circumferential main flow nozzles for directing a main compressed air flow tangentially. Each blade has an interior chamber in flow communication with a source of auxiliary compressed air with at least one bore extending between the chamber and an exterior surface of the blade. The bores eject further cooled air from the heat exchanger and merge with the primary compressed air flowing through the injector nozzles. The bores may also produce a cooling film of air that reduces drag over the injector blades.

Abstract: A turbine engine having interior cavity sealed by a thermally controlled valve is disclosed. The cavity is defined by at least one cylindrical wall portion. The valve comprises an opening in the cylindrical wall portion and a cylindrical band, coaxial and interior to the wall portion. The cylindrical band is made of material having a higher thermal coefficient of expansion than the wall portion. As the temperature of the engine increases, the band expands at a higher rate than the wall, thereby sealing the valve. As the temperature decreases, the band contracts thereby opening the valve. The valve may be used to permit a cavity to be pressurized at low temperatures. The pressure in the cavity may exert a forward load on a thrust bearing, suspending the engine shaft.