High Temperature Airfoil Preforming for Small Turbine Engine Components

As a part of the Integrated High Performance Turbine Engine Technology (IHPTET) program, the Joint Turbine Advanced Gas Generator (JTAGG) program aims to revolutionize aircraft propulsion performance and operational capability by decreasing specific fuel consumption by 40%. and increase power-to-weight by 120%. In order to accomplish these goals, higher operating temperatures must be achieved through the incorporation of ceramic matrix composites (CMC's) into turbine components. Foster-Miller has previously proven the ability to braid net shape airfoils with ceramic fibers, for low pressure turbine components for jet aircraft engines. Foster-Miller proposes to further develop this technology by addressing the miniaturization issues which will be encountered to fabricate a turbine nozzle guide vane for the JTAGG engine, while optimizing the airfoil-to-platform strength for the integrally braided preforms. In cooperation with our Phase I partner, GE Aircraft Engines, Foster-Miller has developed a technology development plan for all related CMC turbine components. Successful development of this technology will result in low cost, high performance parts which can be incorporated into future generation engines. This technology will not only benefit the JTAGG engine program, but will also provide essential data and technology to feed into related engine programs for the Navy, Air Force, NASA, and Army. BENEFITS: Advancing and miniaturizing the technology to braid high temperature materials with complex geometry will be developed to meet the needs of the IHPTET program and GE Aircraft Engines, a leading manufacturer of the future generation engines. The nozzle guide vanes in gas turbine engines have been identified as the ideal first implementation location. The preforming technology will be applicable to all future turbine applications. These preforming technologies are critical to the incorporation of high temperature materials into complex, highly loaded geometries.