公开(公告)号：WO2013162665A3

公开(公告)日：2013-12-27

申请号：PCT/US2013024924

申请日：2013-02-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： LOVETT JEFFERY A ,  HAUTMAN DONALD J ,  BROGAN TORENCE P ,  ECKETT CHRISTOPHER A ,  COLKET III MEREDITH B

IPC: F02C7/00 ,  F02C7/26 ,  F02K3/00

CPC classification number: F02K3/10

Abstract: A gas turbine or rocket engine hot section includes a first duct case, a second duct case, a plurality of vanes arranged about an axial centerline, and an igniter located with a first of the plurality of vanes. The first of the plurality of vanes extends axially between a leading edge and a flame holder surface at a trailing edge. The flame holder surface extends radially between a first vane end connected to the first duct case and a second vane end connected to the second duct case. The flame holder surface includes a first section that tapers towards the first vane end, and a second section that tapers away from the first section and towards the second vane end.

Abstract translation: 燃气轮机或火箭发动机热部分包括第一管道壳体，第二管道壳体，围绕轴向中心线布置的多个叶片以及位于多个叶片中的第一个的点火器。 多个叶片中的第一个在后缘处在前缘和火焰保持器表面之间轴向延伸。 火焰保持器表面在连接到第一管道壳体的第一叶片端部和连接到第二管道壳体的第二叶片端部之间径向延伸。 火焰保持器表面包括朝向第一叶片端逐渐变细的第一部分和从第一部分逐渐变细并朝向第二叶片端的第二部分。

公开(公告)号：WO2015069354A3

公开(公告)日：2015-07-16

申请号：PCT/US2014051589

申请日：2014-08-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DAI ZHONGTAO ,  SMITH RANDOLPH J ,  KOPP-VAUGHAN KRISTIN ,  SNYDER TIMOTHY S ,  HAUTMAN DONALD J

IPC: F23R3/28 ,  F02C7/22 ,  F23R3/02

CPC classification number: F23R3/12 ,  F02C7/22 ,  F23D11/383 ,  F23D2900/11101 ,  F23R3/14 ,  F23R3/28 ,  F23R3/283 ,  F23R3/286 ,  F23R3/36 ,  Y02T50/675

Abstract: A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, said outer air swirler defines an outer annular air passage between an outer wall and an inner wall, the outer wall defines a convergent-divergent nozzle. An inner air swirler along the axis to define an annular liquid passage therebetween, the annular liquid passage terminates upstream of the convergent-divergent nozzle and an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler.

Abstract translation: 用于燃气涡轮发动机的燃烧器的燃料喷嘴包括沿轴线的外部空气旋流器，所述外部空气旋流器在外壁和内壁之间限定外部环形空气通道，外壁限定会聚发散喷嘴。 沿着轴线的内部空气旋流器限定其间的环形液体通道，环形液体通道终止在会聚发散喷嘴的上游，并且围绕外部空气旋流器和内部空气旋流器之间的轴线的环形燃料气体通道。

公开(公告)号：EP3039345A4

公开(公告)日：2017-04-26

申请号：EP14859549

申请日：2014-08-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DAI ZHONGTAO ,  SMITH RANDOLPH J ,  KOPP-VAUGHAN KRISTIN ,  SNYDER TIMOTHY S ,  HAUTMAN DONALD J

IPC: F23R3/28 ,  F02C7/22 ,  F23R3/02 ,  F23R3/36

CPC classification number: F23R3/12 ,  F02C7/22 ,  F23D11/383 ,  F23D2900/11101 ,  F23R3/14 ,  F23R3/28 ,  F23R3/283 ,  F23R3/286 ,  F23R3/36 ,  Y02T50/675

Abstract: A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, said outer air swirler defines an outer annular air passage between an outer wall and an inner wall, the outer wall defines a convergent-divergent nozzle. An inner air swirler along the axis to define an annular liquid passage therebetween, the annular liquid passage terminates upstream of the convergent-divergent nozzle and an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler.

Abstract translation: 用于燃气涡轮发动机的燃烧器的燃料喷嘴包括沿着轴线的外部空气旋流器，所述外部空气旋流器限定外壁和内壁之间的外部环形空气通道，外壁限定会聚 - 扩散喷嘴。 沿着轴线形成内部空气旋流器以在它们之间限定环形液体通道，环形液体通道终止于会聚 - 发散喷嘴的上游，并且围绕外部空气旋流器和内部空气旋流器之间的轴线的环形燃料气体通道。