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Effect of steady-state temperature distortion and combined distortion on inlet flow to a turbofan engine
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Soeder, R. H. Bobula, G. A. |
| Copyright Year | 1979 |
| Description | Flow angle, static pressure, total temperature and total pressure were measured in the inlet duct upstream of a turbofan engine operating with temperature distortion or combined pressure-temperature distortion. Such measurements are useful in the evaluation of analytical models of inlet distortion. A rotating gaseous-hydrogen burner and a circumferential 180 degrees-extent screen configuration mounted on a rotatable assembly generated the distortions. Reynolds number index was maintained at 0.5 and engine corrected low-rotor speeds were held at 6000 and 8600 rpm. The measurements showed that at the entrance to the engine, flow angle was largest in the hub region. As flow approached the engine, yaw angle (circumferential variation) increased and pitch angle (radial variation) decreased. The magnitude of static-pressure distortion measured along the inlet-duct and extended bullet nose walls increased exponentially as flow approached the engine. |
| File Size | 1403101 |
| Page Count | 42 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19790022016 |
| Archival Resource Key | ark:/13960/t3jx35s0d |
| Language | English |
| Publisher Date | 1979-08-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Pressure Effects Temperature Inversions Reynolds Number Flow Measurement Turbofan Engines Rotor Speed Inlet Flow Flow Geometry Steady State 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 |
