PERFORMANCE OF BASIC XJ79-GE-1 TURBOJET ENGINE AND ITS COMPONENTS
Abstract
An investigation to determine the performance of the XJ79-GE-1 turbojet engine and its components, while operating as integral parts of the engine, was conducted in an altitude test chamber. Data were obtained over a range of Reynolds number indices from 0.60 to 0.08 and for various settings of the variable compressor stators and variable-area exhaust nozzle from fully open to fully closed positions. Compressor performance and turbine performance are presented in the form of performance maps at selected values of Reynolds number index; the effects of Reynolds number on performance are summarized. The effects of variable stator angle and high inlet-air temperatures on compressor performance are also shown. Over-all engine performance (net thrust and specific fuel consumption) is presented for a flight Mach number of 0.9 at rated engine conditions over a range of altitudes to illustrate performance losses resulting from decreased Reynolds number index. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 08, 1958
- Accession Number
- AD0256960
Entities
People
- Carl E. Campbell
Organizations
- National Aeronautics and Space Administration