International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
권호 표지
DOI QR코드

DOI QR Code

Development of Block type Inlet Distortion Simulating Device for Gas Turbine Engine Inlet Distortion Test

  • Lee, Kyung-Jae (Advanced Propulsion System Department Korea Aerospace Research Institute) ;
  • Lee, Bo-Hwa (Advanced Propulsion System Department Korea Aerospace Research Institute) ;
  • Kang, Sang-Hun (Advanced Propulsion System Department Korea Aerospace Research Institute) ;
  • Jung, Jae-Hong (Advanced Propulsion System Department Korea Aerospace Research Institute) ;
  • Yang, Soo-Seok (Advanced Propulsion System Department Korea Aerospace Research Institute) ;
  • Lee, Dae-Sung (Advanced Propulsion System Department Korea Aerospace Research Institute) ;
  • Kwak, Jae-Su (School of Aerospace and Mechanical Engineering Korea Aerospace University)
  • Published : 2007.11.01
Download PDF
⟨ Previous Next ⟩

Abstract

In late 1960's, engineers of the engine manufacturer experienced that the distortion of inlet flow of turbofan and turbojet engine could cause the surge in compressor and affect overall engine operational performance, which result in the deterioration of stability of the engine. In this study, block type of inlet distortion simulating device has been developed in order to investigate the effect of inlet distortion on the deterioration of overall engine operational performance. The inlet distortion simulating device was installed in front of engine inlet in order to simulate distortion of inlet flow. The degree of inlet distortion was measured by rakes installed upstream the inlet distortion simulating device and between the engine inlet and inlet distortion simulating device. Before applying the inlet distortion simulating device to real engine, preliminary tests were performed with a simulated engine in order to verify the degree of inlet distortion by the device. Preliminary inlet distortion tests were performed in Altitude Engine Test Facility(AETF) of Korea Aerospace Research Institute(KARI) and results showed that the inlet distortion simulating device could be used in simulating various inlet distortion cases.

Keywords

References

  1. Milt Davis, Alan Hale, Dave Beale, 2001, 'An Argument for Enhancement of the Current Inlet Distortion Ground Test Practice for Aircraft Gas Turbine Engines', ASME TURBO EXPO 2001, 2001-GT-0507
  2. P. P. Walsh and P. Fletcher, 2004, 'Gas Turbine Performance', 2nd edition, Blackwell Science and ASME Press
  3. J. Seddon, E. L. Goldsmith, 1989, 'Intake Aerodynamics', AIAA EDUCATION SERIES, Blackwell Scientific Publications Ltd
  4. Jin-Kun Lee, Kyung-Jae Lee, Sung-Hee Kho, Jae-Su Kwak, 2007, 'Inlet Distortion Test of Gas Turbine Engine', Journal of Aerospace System Engineering, Vol. 1, No. 1, pp. 53-59
  5. Myung-Ho Kim, 2007, 'Design and Numerical Analysis of Swirl Generator in Internal Duct using Delta Wing with Vortex Flap', KSAS, Vol 35, No. 9, pp. 761-770 https://doi.org/10.5139/JKSAS.2007.35.9.761
  6. Subba Reddy, C., 1981, 'Effect of Leading Edge Vortex Flaps on Aerodynamic Performance of Delta Wings', AIAA Journal, Vol. 18, No. 9, pp. 227-238 https://doi.org/10.2514/3.50753
  7. Genbler, H. P., Meyer, W., and Fottner, L., 1986, 'Development of Intake Swirl Generators for Turbo Jet Engine Testing', AGARD CP-400
  8. Marchman III, J. E., 1981, 'Effectiveness of Leading-Edge Vortex Flaps on 60 and 75 Degree Delta Wings', AIAA Journal, Vol. 18, No. 4, pp. 280-286

Cited by

  1. Performance of a Low Speed Axial Compressor Rotor Blade Row under Different Inlet Distortions vol.8, pp.1, 2017, https://doi.org/10.5194/ms-8-127-2017