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Modeling Turboshaft Engines for the Revolutionary Vertical Lift Technology ProjectTurboshaft engine performance and weight models were developed to support conceptual propulsion and vehicle mission design and performance under the Revolutionary Vertical Lift Technology (RVLT) Project. These models were developed using open data sources, assuming current and advanced technology levels, and range from 650 to 7,500 shaft output horsepower (485 to 5,600 kW). Documenting the methodology, assumptions, and resulting performance realizes important benefits NASA and the aviation community. NASA concept vehicle efforts using these propulsion models can be more readily shared among the government, industry and university community as common baselines to support current and future work. Assessing the benefits of advanced technologies and new configurations can be facilitated using these models, which helps guide technology investment. As the various modeling conceptual vehicle and mission analysis environments advanced, these models can be used directly for broader systems analysis studies, including optimization within the propulsion model itself. To perform this effort, the turboshaft engine is briefly discussed, highlighting the specific components and their expected performance characteristics over the power range and technology levels considered. Engine configurations will also be discussed as they will vary based on power output and assumed technology level. Engine performance, such as airflow, power output and weight will be reported, noting trends that are important for system studies. The effect of advanced propulsion technologies on RVLT concept vehicles are also reported. Finally, potential future propulsion modeling work will be proposed.
Document ID
20190025407
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Snyder, Christopher A. (NASA Glenn Research Center Cleveland, OH, United States)
Tong, Michael T. (NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
May 30, 2019
Publication Date
May 13, 2019
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
GRC-E-DAA-TN66991
Meeting Information
Meeting: Annual Forum and Technology Display: The Future of Vertical Flight
Location: Philadelphia, PA
Country: United States
Start Date: May 13, 2019
End Date: May 16, 2019
Sponsors: Vertical Flight Society
Funding Number(s)
WBS: 664817.02.03.04.01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Technical Review
Single Expert

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