COMDES-MELT: A Turbofan Engine Icing Risk Analysis Tool, User’s Manual

Philip C. E. Jorgenson; Joseph P. Veres

The computational tool COMDES-MELT was developed to predict the susceptibility of turbofan engines to ice accretion when flying in an ice crystal environment. COMDES-MELT is a first-generation computational tool that can estimate the conditions at which the accretion of ice can occur, location within the turbofan engine compression system, and at which engine operating points within the flight trajectory. This is accomplished by tracking the parameters of static wet bulb temperature, ice particle melt ratio, and the ice-water to airflow rates ratio as ice crystals are ingested into the engine compression system. It has been used successfully to predict engine operating points for simulation in an altitude wind tunnel with ice crystal ingestion. These engine tests occur in a simulated ice crystal cloud environment. This predictive analysis has been used to generate the test matrix in preparation for tests in the Propulsion Systems Laboratory, an altitude test facility at the NASA Glenn Research Center. Furthermore, due to the speed of the code during an engine icing test, adjustments to the test matrix can be provided to the test engineer in real time to focus on a particular area of ice accretion susceptibility. The use of the COMDES-MELT code will be examined in this manual.

Document ID

20200001992

Acquisition Source

Glenn Research Center

Document Type

Technical Memorandum (TM)

External Source(s)

https://software.nasa.gov/software/LEW-20027-1

Authors

Date Acquired

March 27, 2020

Publication Date

March 1, 2020

Subject Category

Report/Patent Number

Funding Number(s)

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Public

Public Use Permitted.

Technical Review

Single Expert

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TM-2020-220457.pdf

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