#$%^&*AU2019264621A120200604.pdf#####INVOLUTE TRAPPED VORTEX COMBUSTOR ASSEMBLY ABSTRACT A gas turbine engine including a trapped vortex combustor assembly is generally provided. The combustor assembly includes an inner liner wall extended annularly around a combustor centerline, and an outer liner wall extended annularly around the combustor centerline. The inner liner wall and the outer liner wall together define an involute wall extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline. The involute wall defines an involute combustion chamber. One or more of the inner liner wall and the outer liner wall each define a first dilution opening and a shaped dilution opening.2/4 C= C% C= In C= C= C= m C-4 C-4 Ln cv% C-4 C-4 C*4 C*4 C= k- C= C= C 4 C= C= L^ C*4 CN WN 011) C-4 C'*4 co C2%1 0%
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机译：＃$％^＆* AU2019264621A120200604.pdf #####渐进式涡流燃烧器总成抽象包括截留涡流燃烧器组件的燃气涡轮发动机通常是提供。燃烧器组件包括环形地延伸的内衬壁围绕燃烧器中心线，外衬壁围绕燃烧室中心线。内衬壁和外衬壁共同限定了一个渐开线壁从圆周参考至少部分地以螺旋曲线的形式延伸燃烧器中心线周围的直线。渐开线壁限定渐开线燃烧室。内衬壁和外衬壁中的一个或多个分别限定第一稀释口和定型稀释口。2/4C = C％C =在C =C =C =m C-4C-4n简历％C-4C-4 C * 4C * 4C = k- C = C =C 4C = C =L ^ C * 4 CNWN011）C-4C'* 4合作C2％10％
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