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Investigation of Performance Degradation in a Mixed Flow Low Bypass Turbofan Engine

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Abstract

A low bypass turbofan engine is investigated for performance degradation (low thrust), while high-pressure spool speed could not reach the maximum value at max throttle setting. Teardown examination of the engine revealed compressor fouling and erosion of the high-pressure turbine blades. Investigation shows that compressor fouling is responsible for reducing air flow rate and its efficiency. This in turn reduced engine thrust by approximately 7% compared to the minimum guaranteed thrust at max power setting. As the fuel control system supplies the required fuel to the engine corresponding to the power setting, it created a rich fuel–air ratio resulting high turbine entry temperature and subsequent blade erosion. GasTurb performance model can be developed based on the current study to assess the performance degradations at any flight condition where limited engine parameters are captured, and degradation trend of the engine can be generated. Based on the degradation trend, engine degradation prognostic can be developed to assess engine performance capability to meet the operational and maintenance requirements.

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Authors and Affiliations

  1. Hindustan Aeronautics Limited, Koraput, Odisha, India

    Narahari Rath

  2. Regional Center for Military Airworthiness (Engines), Bangalore, India

    R. K. Mishra

  3. Department of Aerospace Engineering, Indian Institute of Technology, Kanpur, India

    Narahari Rath & Abhijit Kushari

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  1. Narahari Rath
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  2. R. K. Mishra
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  3. Abhijit Kushari
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Rath, N., Mishra, R.K. & Kushari, A. Investigation of Performance Degradation in a Mixed Flow Low Bypass Turbofan Engine. J Fail. Anal. and Preven. 23, 378–388 (2023). https://doi.org/10.1007/s11668-023-01590-2

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