Method for low nitrogen oxide combustion in supersonic transport

Details Method for low nitrogen oxide combustion in supersonic transport Method for low nitrogen oxide combustion in supersonic transport

1991-09-24

1993-03-09

Heller, Gregory A.

Chemistry of inorganic compounds

Modifying or removing component of normally gaseous mixture

Nitrogen or nitrogenous component

C01B 2100

Patent

active

051925168

ABSTRACT:
A method for reducing the NO.sub.x produced by the engine of a supersonic aircraft. A reducing agent is injected into the combustor or the exhaust region of the engine. The reducing agent can be either hydrogen azide or hydrazine in an aqeuous form. For injection into the combustor, injection will be perpendicular to the main air flow through the engine and into a downstream portion of the combustor. Injection is carried out whenever NO.sub.x reduction is needed. By injecting the reducing agent into the downstream portion of the combustor or into the exhaust region, the reduction reaction is decoupled from the combustion process so that engine performance is not impaired.

REFERENCES:
patent: 3846981 (1974-11-01), Paczkowski
patent: 4761270 (1988-08-01), Turchan

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