Numerical research on the safety and performance of transonic compressor with bleed air at multiple operation state

Some provisions in CCAR 33 are directly and indirectly related with the air system of aircraft engines. To certificate the characteristics of air system is an important work for engine airworthiness. Requirements and instructions of air system are issued under the above provisions in CCAR 33. Air system is essential to the safe and reliable operation of the aircraft engines. The bleed air is drawn out from the compressors. The Sec. 33.66 in CCAR 33, which is referred to as "Bleed air system", presents requirements and instructions for the bleed air. Bleed air from the high pressure compressor has taken up 3-5% in the air system, which keeping on growing during recent decades. Therefore, in view of the importance of air system and the bleed location, a new bleeding method with more efficient use of the bleed air is very much needed. In this paper, air system bleed is used for flow control to explore the feasibility of improving compressor performance through removing stator corner separation by bleed air. The transonic single-stage axial compressor Stage35 of NASA is taken as the research object to study the impact of stator bleed rates on the performance of compressor at different rotation speeds. The numerical research shows that bleeding on the stator casing corner can effectively enhance the performance of compressor at different rotation speeds and improve stator flow field.