公开(公告)号：US20050188698A1

公开(公告)日：2005-09-01

申请号：US10386771

申请日：2003-03-11

申请人： Ly Nguyen ,  Hakan Aksoy ,  Stony Kujala ,  Cristoper Frost

发明人： Ly Nguyen ,  Hakan Aksoy ,  Stony Kujala ,  Cristoper Frost

IPC分类号： F23R3/42 ,  F23R3/52

CPC分类号： F23R3/52 ,  F23R3/425

摘要： A conical helical design for a turbine combustor scroll utilizes as much cavity of the combustor housing as possible by adding an axial shift and an irregular cross sectional shape in the scroll without adversely effecting aerodynamic performance. The axial shift region of the combustor scroll extends the cross-sectional area centroid of the scroll beyond the scroll's discharge area B-width. The resulting scroll design allows for the use of a high performance engine with a larger combustor while reducing the weight of the system by making the combustor housing as small as possible. Furthermore, the scroll design increases the air velocity for convection cooling by reducing the gap between the scroll and the housing. The turbine scroll of the present invention is useful in engines for which high performance is required, such as certain high performance aircraft.

摘要翻译： 用于涡轮机燃烧器涡旋盘的锥形螺旋设计通过在涡旋中增加轴向移动和不规则横截面形状而尽可能多地利用燃烧器壳体的空腔，而不会不利地影响空气动力性能。 燃烧器涡旋件的轴向移动区域将涡旋件的横截面积重心延伸超过涡旋件的排放区域B-宽度。 所得到的涡卷设计允许使用具有较大燃烧器的高性能发动机，同时通过使燃烧器壳体尽可能小地减小系统的重量。 此外，涡旋设计通过减小涡旋件和壳体之间的间隙来增加用于对流冷却的空气速度。 本发明的涡轮涡旋盘可用于需要高性能的发动机，例如某些高性能飞机。