A Low Pressure Compressor (LPC) is unique in its requirements for wide operating range during a flight mission. As a result, the aerodynamic design involves a trade-off between performance and stall margin. The requirement to reduce engine development cost and schedule has resulted in developing LPCs during the engine validation program. With engine validation and certification schedules being compressed continuously, getting the initial design right has become critical. Multistage CFD analysis is used in the current design process to optimize the airfoils and stage matching. Three-dimensional airfoil features, such as bow, that improve secondary flow features and can be optimized using CFD. The PW6000 LPC engine test data has validated the analytical results and demonstrated surge margin and efficiency levels above the requirements. The LPC also achieved all other design objectives in its first build, representing a significant cost saving for a new centerline engine development program.
The performance of a compressor stator airfoil with end-wall injection was studied experimentally and computationally. The geometry was a high-speed, subsonic, linear cascade. The independent variables studied were airfoil incidence angle and mass flow rate of end-wall injection upstream of the stator. The end-wall injection was intended to simulate upstream “leakage” through hardware gaps in the end-walls of gas-turbine engines. The exit of the cascade was interrogated experimentally by a five-hole-probe and a total pressure Kiel probe to provide total pressure measurements, which were used to calculate total pressure loss coefficients at the exit of the test section. Computational studies were completed to examine the end-wall flow physics and entropy generating mechanisms through the stator section. The experimental results showed a distinct decrease in the downstream total pressure field with end-wall injection flow, and the impact of the upstream injection on the stator loss coefficient was not a function of the incidence angle. The computational investigation found that the majority of the end-wall injection’s effect on the downstream total pressure field was observed as an increase in the size of the secondary flows on the suction-side of the stator near the upper end-wall.
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