Assessment of Cooling Techniques for 2-D & 3-D Ceramic Matrix Composite (CMC) Turbine Engine Comps.

Triton proposes teaming with an aircraft engine original equipment manufacturer (OEM) to assess the performance of laser drilled film cooling holes in both three-dimensional (3-D) randomly dispersed fiber CMC material and two-dimensional (2-D) layered woven fiber CMC material for fabrication of hot section turbine engine components. 2-D and 3-D cooled (drilled) and uncooled (undrilled) coupons representative of turbine component configurations of interest to the Army will be rig tested to assess their performance in high temperature environments. Triton will produce the 3-D CMC test specimens in-house and will procure 2-D CMC test specimens from an established CMC supplier. Triton will validate the laser drilling work from its Phase I work for the Phase II materials and will fabricate test component from designs provided by the OEM. 2-D and 3-D test components with cooling schemes will be compared to 2-D and 3-D test components without cooling. The OEM will support Triton in all aspects of design, modeling and analysis relating to the the test components and rig test requirements. After rig testing, the OEM will support Triton in the assessment of the effectiveness of the different cooling schemes and the performance of the two materials under adverse high temperature gradient conditions.