Experimental Investigation of High-Pressure Steam-Induced Surge in a Transonic Compressor Stage; Master's thesis

摘要

Operational experience indicates that steam escaping from carrier catapults has the potential to induce stall or surge in the compressors of jet aircraft during takeoff. As the carrier fleet ages and the Navy transitions to the single engine F-35C variant of the Joint Strike Fighter, further investigation of steaminduced surge phenomena is necessary to avert undue risks to pilots and to obviate stall related damage to Navy aircraft. This study investigated the effects of both throttle-induced surge and steam-induced surge in a transonic compressor stage at 70%, 80%, 90%, 95%, and 100% of the compressor design speed. The primary goals of this research were to quantify changes in the compressor stall margin as a result of steam ingestion and to develop pressure contour maps to analyze the transformation of shock structures in the blade passages as they relate to inlet throttle settings. The results of this experiment confirmed that the introduction of high-pressure steam consistently reduced the observed compressor stall margin over the entire operating range of the transonic stage and produced reliable representations of the shock structure present along the compressor casing.