Annular combustion chamber for an aircraft turbomachine
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United States of America Patent
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May 21, 2024
Grant Date -
Aug 10, 2023
app pub date -
Jul 2, 2021
filing date -
Jul 10, 2020
priority date (Note) -
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Abstract
Annular combustion chamber for an aircraft turbomachine, said chamber having two coaxial annular walls, an inner annular wall and an outer annular wall, respectively, which are connected upstream by an annular bottom wall of the chamber, wherein an injection device passes through an axis and comprises an air injection system and a frustoconical bowl which is flared downstream and has air passage openings, the chamber further having an annular deflector placed downstream of the bottom wall substantially parallel to the latter; and wherein the air injection system, the bottom wall, the deflector and the bowl are integrally formed.
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