SBIR/STTR Award attributes
Engine systems in advanced aircraft are increasingly being designed to operate at higher power densities, and support higher inlet temperatures and more demanding flight profiles, subjecting ancillary equipment to more extreme environmental conditions. In particular, a critical need has emerged for a lubricant pump that is capable of handling fluid temperatures of 500ºF/260ºC, while operating reliably to both scavenge engine oil and re circulate through the oil cooler back to the main engine shaft bearings. To address this need, we propose a compact, high-speed screw pump supported by hydrodynamic forces. The theory and practice are well established for similar pump flow elements; however, layout, design features, and materials proposed for the present application are a novel embodiment to allow high-temperature operation for applications relevant to aircraft engines. In Phase I, we will complete detailed design of the rotor including hydrodynamic bearings and drive system, carry out a demonstration of a sub scale screw pump to demonstrate efficacy of the concept, then complete a preliminary integrated design of the overall integrated pump. In Phase II, we will build the prototype pump, carry out performance tests, and deliver it to the Air Force for further performance characterization.
