NDLI: Effect of spatial inlet temperature and pressure distortion on turbofan engine stability

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Effect of spatial inlet temperature and pressure distortion on turbofan engine stability

Content Provider	NASA Technical Reports Server (NTRS)
Author	Mehalic, Charles M.
Copyright Year	1988
Description	The effects of circumferential and radial inlet temperature distortion, circumferential pressure distortion, and combined temperature and pressure distortion on the stability of an advanced turbofan engine were investigated experimentally at simulated altitude conditions. With circumferential and radial inlet temperature distortion, a flow instability generated by the fan operating near stall caused the high-pressure compressor to surge at, or near, the same time as the fan. The effect of combined distortion was dependent on the relative location of the high-temperature and low-pressure regions; high-pressure compressor stalls occurred when the regions coincided, and fan stalls occurred with the regions separated.
File Size	4266835
Page Count	19
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19880011778
Archival Resource Key	ark:/13960/t9q28t356
Language	English
Publisher Date	1988-01-01
Access Restriction	Open
Subject Keyword	Aircraft Propulsion And Power Flow Stability Inlet Temperature Gas Turbine Engines Distortion Temperature Profiles Pressure Measurement Aerodynamic Stalling Space-time Functions Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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