Performance Simulation of a Turboprop Engine for Basic Trainer

• Published in: Journal of mechanical science and technology 2002-06, Vol.16 (6), p.839-850
• Main Authors: Kong, Changduk, Ki, Jayoung, Chung, Sukchoo
• Format: Article
• Language: English
• Subjects: Applied sciences; Compressors; Energy; Energy consumption; Energy. Thermal use of fuels; Engine components; Engines; Engines and turbines; Equipments for energy generation and conversion: thermal, electrical, mechanical energy, etc; Exact sciences and technology; Flight simulators; Fuel consumption; Fuels; Gas generators; Gas turbines; Inlet temperature; Jet engines; Mass flow rate; Monitoring systems; Performance evaluation; Performance prediction; Power plants; Pressure ratio; Scaling laws; Simulation; Studies; Transient analysis; Transient performance; Turbines; Turboprop engines; Variable pitch propellers
• ISSN: 1738-494X; 1226-4865; 1976-3824
• DOI: 10.1007/BF02939343

A performance simulation program for the turboprop engine (PT6A-62), which is the power plant of the first Korean indigenous basic trainer KT-1, was developed for performance prediction, development of an EHMS (Engine Health Monitoring System) and the flight simulator. Characteristics of components including compressors, turbines, power turbines and the constant speed propeller were required for the steady state and transient performance analysis with on and off design point analysis. In most cases, these were substituted for what scaled from similar engine components' characteristics with the scaling law. The developed program was evaluated with the performance data provided by the engine manufacturer and with analysis results of GASTURB program, which is well known for the performance simulation of gas turbines. Performance parameters such as mass flow rate, compressor pressure ratio, fuel flow rate, specific fuel consumption and turbine inlet temperature were discussed to evaluate validity of the developed program at various cases. The first case was the sea level static standard condition and other cases were considered with various altitudes, flight velocities and part loads with the range between idle and 105% rotational speed of the gas generator. In the transient analysis, the Continuity of Mass Flow Method was utilized under the condition that mass stored between components is ignored and the flow compatibility is satisfied, and the Modified Euler Method was used for integration of the surplus torque. The transient performance analysis for various fuel schedules was performed. When the fuel step increase was considered, the overshoot of the turbine inlet temperature occurred. However, in case of ramp increase of the fuel longer than step increase of the fuel, the overshoot of the turbine inlet temperature was effectively reduced.[PUBLICATION ABSTRACT]