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Measurement of Exhaust Emissions From Two J-58 Engines at Simulated Supersonic Cruise Flight Conditions FREE

[+] Author Affiliations
J. D. Holdeman

National Aeronautics and Space Administration, Lewis Research Center, Cleveland, OH

Paper No. 76-GT-8, pp. V01AT01A008; 13 pages
doi:10.1115/76-GT-8
From:
  • ASME 1976 International Gas Turbine and Fluids Engineering Conference
  • Volume 1A: General
  • New Orleans, Louisiana, USA, March 21–25, 1976
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7974-0
  • Copyright © 1976 by ASME

abstract

Emissions of total oxides of nitrogen, unburned hydrocarbons, carbon monoxide, and carbon dioxide from two J-58 afterburning turbojet engines at simulated high-altitude flight conditions are reported. Test conditions included flight speeds from Mach 2 to 3 at altitudes from 16 to 23 km. For each flight condition, exhaust measurements were made for four or five power levels from maximum power without afterburning through maximum afterburning. The data show that exhaust emissions vary with flight speed, altitude, power level, and radial position across the exhaust. Oxides of nitrogen (NOx) emissions decreased with increasing altitude and increased with increasing flight speed. NOx emission indices with afterburning were less than half the value without afterburning. Carbon monoxide and hydrocarbon emissions increased with increasing altitude and decreased with increasing flight speed. Emissions of these species were substantially higher with afterburning than without.

Copyright © 1976 by ASME
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