Altitude performance investigation of two single-annular type combustors and the prototype J40-WE-8 turbojet engine combustor with various combustor-inlet air pressure profiles

Sobolewski, Adam E., Miller, Robert R., McAulay, John E.
naca-rm-e52j07
1953


Data obtained for three single-annular type combustors over a range of engine speeds at an altitude of 30,000 feet and flight Mach number of 0.62 indicated that changes in combustor hole geometry and combustor-inlet air-pressure profiles affected the combustor-outlet temperature profile and the combustor pressure-loss coefficient but had no discernible effect on combustion efficiency. Performance data for the prototype J40-WE-8 turbojet-engine combustor were obtained over a range of altitudes from 15,000 to 55,000 feet and flight Mach numbers from 0.17 to 0.99. A good correlation was obtained when combustion efficiency was presented as a function of a combustion parameter and engine fuel-air ratio.

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