Accession Number : ADA190110

Title :   Linear State Space Modeling of a Turbofan Engine.

Descriptive Note : Final rept. May 86-Dec 87,

Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s) : Thelen, Gregory L

PDF Url : ADA190110

Report Date : Dec 1987

Pagination or Media Count : 84

Abstract : The F101 turbofan engine, used on the B-1B bomber, will be used as the example with the linear state space models being derived from the non-linear F101 engine computer simulation model. The internal convergence logic of the F101 engine simulation will be used to derive the individual elements making up the linear state space models. The linear state space models will consist of both high speed and low speed rotor dynamics and turbine inlet temperature heat soak dynamics. State space inputs considered will be fuel flow and engine exit nozzle area. Also disussed in this paper will be linear analytic equations in state space format and their comparative accuracies to the models derived using the F101 non-linear computer simulation model. Based on the linear state space models developed in this paper, control systems will be designed and implemented into the F101 engine computer model. Transient performance will be compared between current engine control design and the control design based on the linear state space models. Final results will confirm the validity of the state space models derived by showing improvement over current engine transient performance.

Descriptors :   *CONTROL SYSTEMS, *TURBOFAN ENGINES, ACCURACY, CONTROL, CONVERGENCE, DYNAMICS, EQUATIONS, EXITS, FLOW, FORMATS, JET ENGINE FUELS, INTERNAL, LINEARITY, LOGIC, LOW VELOCITY, MATHEMATICAL MODELS, NOZZLES, PERFORMANCE(ENGINEERING), GAS TURBINE ROTORS, TRANSIENTS, COMPUTERIZED SIMULATION, JET ENGINE INLETS, THERMODYNAMICS, FEEDBACK, BALANCE, TURBINE COMPONENTS, LINEAR DIFFERENTIAL EQUATIONS, EXHAUST NOZZLES, THESES

Subject Categories : Jet and Gas Turbine Engines
      Numerical Mathematics

Distribution Statement : APPROVED FOR PUBLIC RELEASE