Abstract:
Articulating the pitch angle of a turbine blade can improve performance by maintaining optimum design incidence and thus reduce the probability of flow separation and thermal stresses developed due to aerothermal loads for variable speed gas turbine engine applications. Potential benefits to Army Aviation are highly efficient (aerodynamically) turbine blades, possible reduction of the need for active blade cooling and thermal barrier coatings, increased fuel efficiency, power density, and the ability to fly faster and longer. The goal of this effort is to assess the benefit and feasibility of an adaptable variable pitch turbine blade for maintaining attached flow and optimal thermal design for a gas turbine engine. A technology concept study has been conducted to enable a viable adaptable turbine rotor blade that can enhance the performance and efficiency of future aircraft gas turbine engines. A typical aircraft t turbine blade is used for this technology concept study. An adaptable turbine rotor blade, if made feasible, can lead to a leap ahead technology innovation in improving part-load efficiency of gas turbine engines.