NDLI: Computer program for the design and off-design performance of turbojet and turbofan engine cycles

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Computer program for the design and off-design performance of turbojet and turbofan engine cycles

Content Provider	NASA Technical Reports Server (NTRS)
Author	Morris, S. J.
Copyright Year	1978
Description	The rapid computer program is designed to be run in a stand-alone mode or operated within a larger program. The computation is based on a simplified one-dimensional gas turbine cycle. Each component in the engine is modeled thermo-dynamically. The component efficiencies used in the thermodynamic modeling are scaled for the off-design conditions from input design point values using empirical trends which are included in the computer code. The engine cycle program is capable of producing reasonable engine performance prediction with a minimum of computer execute time. The current computer execute time on the IBM 360/67 for one Mach number, one altitude, and one power setting is about 0.1 seconds. about 0.1 seconds. The principal assumption used in the calculation is that the compressor is operated along a line of maximum adiabatic efficiency on the compressor map. The fluid properties are computed for the combustion mixture, but dissociation is not included. The procedure included in the program is only for the combustion of JP-4, methane, or hydrogen.
File Size	3333846
Page Count	76
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19780022179
Archival Resource Key	ark:/13960/t6547hj4b
Language	English
Publisher Date	1978-06-01
Access Restriction	Open
Subject Keyword	Aircraft Propulsion And Power Engine Design Gas Turbine Engines Performance Prediction Thermodynamic Cycles Combustion Efficiency Computer Aided Design Computer Programs Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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