Abstract:

A new method of acceleration control law design for turbojet and turbofan is proposed. Based on the steadystate performance computing model, an extra power extraction of spool is induced so that the steady-state operating points (line) are approached to the surge limit. Taking the fuel-rich flameout limit of combustor, total temperature limit of turbine inlet and surge margin limit of compressor into account, and using appropriate form to describe the acceleration control law and combining with the experiences of research and development of turbine engine, the acceleration control law for turbojet and turbofan is designed fast and accurately.The computing results of improved design of acceleration control law of some turbojet engine indicate that the new method is accurate and effective.

Key words: turbine , engine,  , acceleration , characteristic,  , acceleration , control , law , design,  , power , extraction , model,  , surge , margin,  , turbine , inlet , total , temperature