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Modeling the Deterioration of Engine and Low Pressure Compressor Performance During a Roll Back Event Due to Ice AccretionThe main focus of this study is to apply a computational tool for the flow analysis of the engine that has been tested with ice crystal ingestion in the Propulsion Systems Laboratory (PSL) of NASA Glenn Research Center. A data point was selected for analysis during which the engine experienced a full roll back event due to the ice accretion on the blades and flow path of the low pressure compressor. The computational tool consists of the Numerical Propulsion System Simulation (NPSS) engine system thermodynamic cycle code, and an Euler-based compressor flow analysis code, that has an ice particle melt estimation code with the capability of determining the rate of sublimation, melting, and evaporation through the compressor blade rows. Decreasing the performance characteristics of the low pressure compressor (LPC) within the NPSS cycle analysis resulted in matching the overall engine performance parameters measured during testing at data points in short time intervals through the progression of the roll back event. Detailed analysis of the fan-core and LPC with the compressor flow analysis code simulated the effects of ice accretion by increasing the aerodynamic blockage and pressure losses through the low pressure compressor until achieving a match with the NPSS cycle analysis results, at each scan. With the additional blockages and losses in the LPC, the compressor flow analysis code results were able to numerically reproduce the performance that was determined by the NPSS cycle analysis, which was in agreement with the PSL engine test data. The compressor flow analysis indicated that the blockage due to ice accretion in the LPC exit guide vane stators caused the exit guide vane (EGV) to be nearly choked, significantly reducing the air flow rate into the core. This caused the LPC to eventually be in stall due to increasing levels of diffusion in the rotors and high incidence angles in the inlet guide vane (IGV) and EGV stators. The flow analysis indicating compressor stall is substantiated by the video images of the IGV taken during the PSL test, which showed water on the surface of the IGV flowing upstream out of the engine, indicating flow reversal, which is characteristic of a stalled compressor.
Document ID
20140013261
Document Type
Technical Memorandum (TM)
Authors
Veres, Joseph P. (NASA Glenn Research Center Cleveland, OH, United States)
Jorgenson, Philip, C. E. (NASA Glenn Research Center Cleveland, OH, United States)
Jones, Scott M. (NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
October 29, 2014
Publication Date
October 1, 2014
Subject Category
Aeronautics (General)
Aircraft Propulsion and Power
Air Transportation and Safety
Report/Patent Number
E-18965
AIAA Paper 2014-3842
NASA/TM-2014-218495
Meeting Information
Joint AIAA/ASME/SAE/ASEE Propulsion Conference(Cleveland, OH)
Funding Number(s)
WBS: WBS 648987.02.02.03.20
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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