Advertisement

Performance Evaluation of a Rake Used for Measuring Total Pressure and Total Temperature Inside an Engine Inlet Duct

  • Bohwa LeeEmail author
  • Chuntaek Kim
  • Inyoung Yang
  • Kyungjae Lee
  • Yangji Lee
Original Paper

Abstract

The Korea Aerospace Research Institute runs the ground-based Altitude Engine Test Facility (AETF) for simulating high-altitude environments. This facility is widely used to test the performance of gas turbine engines at ground level to high altitudes. When engine performance is tested in the AETF, total pressure and total temperature of airflow can be measured using rakes in a duct directly connected to the engine inlet. The total pressure and total temperature of airflow into an engine are the main factors affecting the thrust and specific fuel consumption rate of the engine. Furthermore, the total pressure and total temperature at the engine inlet are used as the main reference values when operating test equipment to determine the airflow rate and temperature corresponding to the performance test conditions of the engine. The performance evaluation of the rake used to measure this is crucial. Accordingly, in this study, to improve the accuracy of the total pressure and total temperature values measured using rakes, their total pressure coefficient and total temperature recovery factor are measured, and the measurement uncertainty of the total temperature recovery factor is evaluated.

Keywords

Altitude engine test facility Engine inlet duct Rake Kiel combination probe 

Notes

Acknowledgements

This work was supported by “Test and Evaluation Facilities Operation for Aeronautical Vehicles” of Korea Aerospace Research Institute (grand No. FR 19843).

References

  1. 1.
    Ashwood PF (1973) An altitude test facility for large turbofan engines. J Aircr 10(8):468–474CrossRefGoogle Scholar
  2. 2.
    Castner R, Wyzykowski J, Chiapetta S (2002) High altitude small engine test techniques at the NASA glenn propulsion systems LAB. In: 22nd AIAA aerodynamic measurement technology and ground testing conference, St. Louise, MOGoogle Scholar
  3. 3.
    Soeder R (1994) NASA Lewis propulsion system laboratory customer guide manual. NASA TM-106569Google Scholar
  4. 4.
    Smith RE (1996) Marrying airframes and engines in ground test facilities—an evolutionary revolution. J Aircr 33(4):649–679CrossRefGoogle Scholar
  5. 5.
    Jun Y, Yang I, Nam S, Kim C, Yang S, Lee D (2002) Small turbojet engine test and uncertainty analysis. J Korean Soc Aeronaut Sp Sci 30(5):118–126Google Scholar
  6. 6.
    Lee D, Yang I, Jun Y, Kim C, Yang S (2002) Improving the measurement uncertainty of altitude test facility for gas turbine engines. J Korean Soc Mech Eng 26(11):1496–1502CrossRefGoogle Scholar
  7. 7.
    Jun Y, Yang I, Kim C, Yang S, Lee D (2004) Uncertainty analysis and improvement of an altitude test facility for small jet engines. J Korean Soc Aeronaut Sp Sci 5(1):46–56Google Scholar
  8. 8.
    Lee J, Yang I, Yang S, Kwak J (2007) Uncertainty analysis and ANOVA for the measurement reliability estimation of altitude engine test. J Mech Sci Technol 21(4):664–671CrossRefGoogle Scholar
  9. 9.
    Arrington EA, Gonsalez JC (2005) Improvements to the total temperature calibration of the NASA glenn icing research tunnel. NASA/CR-2005-213875Google Scholar
  10. 10.
    Stickney TM (1955) Recovery and time-response characteristics of six thermocouple probes in subsonic and supersonic flow. National Advisory Committee for Aeronautics, Lewis Flight Propulsion Laboratory, Technical Note 3455Google Scholar
  11. 11.
    Dudziniski TJ, Krause LN (1971) Effect of inlet geometry on flow-angle characteristics of miniature total-pressure tubes. NASA TN D-6406Google Scholar
  12. 12.
    Saravanamuttoo HIH (1990) Recommended practices for measurement of gas path pressures and temperatures for performance assessment of aircraft turbine engines and components. AGARD Advisory Report No. 245Google Scholar
  13. 13.
    Glawe GE, Krause LN, Dudzinski TJ (1968) A small combination sensing probe for measure of temperature, pressure, and flow direction. NASA TN D-4816Google Scholar
  14. 14.
    Smout PD, CooK SC (1996) Simple instrumentation rake designs for gas turbine engine testing. International Gas Turbine and Aeroengine Congress & Exhibition, BirminghamCrossRefGoogle Scholar
  15. 15.
    Aeroprobe Corporation: Kiel and Total Air Temperature (TAT) Probes (2015) Document no. 90001-02-UMN-03, revisionGoogle Scholar
  16. 16.
    ISO/IEC (2008) Uncertainty of measurement—part 3: guide to the expression of uncertainty in measurement, ISO/IEC guide 98-3Google Scholar

Copyright information

© The Korean Society for Aeronautical & Space Sciences 2019

Authors and Affiliations

  1. 1.Aeropropulsion OfficeKorea Aerospace Research InstituteDaejeonRepublic of Korea

Personalised recommendations