0
Research Papers: Gas Turbines: Cycle Innovations

Steady-State and Transient Performance Modeling of Smart UAV Propulsion System Using SIMULINK

[+] Author and Article Information
Jayoung Ki

 Easy Gas Turbine R&D Co., Ltd., 1112-Ho, Cention Building, 1 412 Dunsan-dong, Seo-gu, Daejeon 301-120, Republic of Koreayoung@ezgtc.com

Changduk Kong

Department of Aerospace Engineering, Chosun University, 375 Seosuk-dong, Dong-gu, Gwangju 501-759, Republic of Koreacdgong@chosun.ac.kr

Seonghee Kho

Department of Aerospace Engineering, Chosun University, 375 Seosuk-dong, Dong-gu, Gwangju 501-759, Republic of Koreahabari@paran.com

Changho Lee

Smart UAV Development Center, Korea Aerospace Research Institute, 45 Eoeun-dong, Yuseong-gu, Daejeon 305-333, Republic of Korealeech@kari.re.kr

J. Eng. Gas Turbines Power 131(3), 031702 (Feb 10, 2009) (8 pages) doi:10.1115/1.2982141 History: Received March 31, 2008; Revised April 09, 2008; Published February 10, 2009

Because an aircraft gas turbine operates under various flight conditions that change with altitude, flight velocity, and ambient temperature, the performance estimation that considers the flight conditions must be known before developing or operating the gas turbine. More so, for the unmanned aerial vehicle (UAV) where the engine is activated by an onboard engine controller in emergencies, the precise performance model including the estimated steady-state and transient performance data should be provided to the engine control system and the engine health monitoring system. In this study, a graphic user interface (GUI) type steady-state and transient performance simulation model of the PW206C turboshaft engine that was adopted for use in the Smart UAV was developed using SIMULINK for the performance analysis. For the simulation model, first the component maps including the compressor, gas generator turbine, and power turbine were inversely generated from the manufacturer’s limited performance deck data by the hybrid method. For the work and mass flow matching between components of the steady-state simulation, the state-flow library of SIMULINK was applied. The proposed steady-state performance model can simulate off-design point performance at various flight conditions and part loads, and in order to evaluate the steady-state performance model their simulation results were compared with the manufacturer’s performance deck data. According to comparison results, it was confirmed that the steady-state model agreed well with the deck data within 3% in all flight envelopes. In the transient performance simulation model, the continuity of mass flow (CMF) method was used, and the rotational speed change was calculated by integrating the excess torque due to the transient fuel flow change using the Runge–Kutta method. In this transient performance simulation, the turbine overshoot was predicted.

FIGURES IN THIS ARTICLE
<>
Copyright © 2009 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Figure 1

Engine schematic of the PW206C turboshaft engine

Grahic Jump Location
Figure 2

Generated compressor map by the hybrid intelligent method

Grahic Jump Location
Figure 3

Generated compressor turbine map by the hybrid intelligent method

Grahic Jump Location
Figure 4

Generated power turbine map by the hybrid intelligent method

Grahic Jump Location
Figure 5

Steady-state performance model using SIMULINK ®

Grahic Jump Location
Figure 6

Flowchart for the steady-state performance simulation

Grahic Jump Location
Figure 7

Results of the steady-state performance analysis

Grahic Jump Location
Figure 8

Transient performance model using SIMULINK ®

Grahic Jump Location
Figure 9

Flowchart for the transient performance simulation

Grahic Jump Location
Figure 10

Results of the transient performance simulation

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In