Injection assembly for an aircraft turbine engine and combustion device comprising the injection assembly

Abstract

The invention relates to an injection assembly (70) for an aircraft turbine engine, including: a fuel mixing duct (30) which comprises a fuel mixing throat (37) and is intended to communicate with a combustion chamber (90) in order to supply the combustion chamber (90) with a fuel mixture flow (32); an external air duct (40) which extends around the fuel mixing duct (30) and is intended to communicate with the combustion chamber (90) in order to supply the combustion chamber (90) with an external air flow (42); a gaseous fuel injection device (8), the gaseous fuel injection device (8) including a fuel injection duct (10) which communicates with the fuel mixing duct (30); and a combustion air duct (20) which extends coaxially to the fuel injection duct (10) and communicates with the fuel mixing duct (30).

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