LecturePg. 39-48A two casing (three-stage) high-pressure injection compressor train driven by a gas turbine via a gearbox was full load and full speed performance tested to demonstrate satisfactory aerothermal and rotordynamic performance. During the PTC 10 (1997) Type I testing, rotor instability was observed on the back-to-back (first and second stage) compressor casing. The third stage final compressor casing exhibited anomalous rotor centerline positions in the bearings and rotating stall. This paper discusses the technical analysis, resolution, and retesting to resolve the rotor instability, rotor equilibrium/synchronous response, and rotating stall issues experienced during the testing. It also shows the need for additional joint industry research to better understand and analyze the use of honeycomb seals in hydrocarbon-gas centrifugal compressors
