公开(公告)号：US20160327273A1

公开(公告)日：2016-11-10

申请号：US15108107

申请日：2015-01-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frank J. Cunha ,  Timothy S. Snyder

IPC: F23R3/06 ,  F02C3/14 ,  F23R3/14 ,  F23R3/58 ,  F23M5/08

CPC classification number: F23R3/06 ,  F02C3/14 ,  F05D2210/33 ,  F05D2220/32 ,  F05D2240/35 ,  F23M5/085 ,  F23R3/005 ,  F23R3/007 ,  F23R3/14 ,  F23R3/58 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A heat resistant panel has a bulkhead and a swirler adjacent a combustion chamber. The heat resistant panel comprises an inner panel for facing the combustion chamber and defining a first exit port at an upstream end thereof configured to direct cooling air into the combustor chamber in a first direction adjacent the bulkhead. A second exit port at a downstream end thereof is configured to direct cooling air into the combustor chamber in a second direction with an axial direction defined between the upstream and downstream ends. The first and second directions have opposed axial components. A heat resistant structure and a combustor are also disclosed.

Abstract translation: 耐热面板具有邻近燃烧室的隔板和旋流器。 耐热面板包括用于面向燃烧室并且在其上游端限定出第一出口的内板，所述第一出口构造成沿着与隔板相邻的第一方向将冷却空气引导到燃烧室中。 其下游端的第二出口构造成在第二方向上将冷却空气引导到燃烧室中，其中轴向限定在上游和下游端之间。 第一和第二方向具有相反的轴向分量。 还公开了耐热结构和燃烧器。

公开(公告)号：US20160209037A1

公开(公告)日：2016-07-21

申请号：US14914825

申请日：2014-08-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Zhongtao Dai ,  Randolph J Smith ,  Kristin Kopp-Vaughan ,  Timothy S. Snyder ,  Donald J Hautman

IPC: F23R3/12 ,  F02C7/22 ,  F23R3/28

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：US20160186998A1

公开(公告)日：2016-06-30

申请号：US14910827

申请日：2014-06-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Stanislav Kostka, Jr. ,  Randal G. McKinney ,  James B. Hoke ,  Timothy S. Snyder ,  Frank J. Cunha

IPC: F23R3/06 ,  F23R3/00 ,  F02C7/18

CPC classification number: F23R3/06 ,  F02C7/18 ,  F23R3/002 ,  F23R3/04 ,  F23R3/045 ,  F23R3/26 ,  F23R2900/03041 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than the first inner periphery. Another wall assembly for use in a combustor of a gas turbine engine includes an annular grommet mounted between the support shell and the liner panel. The annular grommet defines a contoured inner wall.

Abstract translation: 用于燃气涡轮发动机的燃烧器的壁组件包括：具有沿着轴线的第一内周边的支撑壳体和具有沿轴线的第二内周边的衬板。 第二内周小于第一内周。 用于燃气涡轮发动机的燃烧器中的另一壁组件包括安装在支撑壳和衬板之间的环形垫圈。 环形垫圈限定了一个轮廓的内壁。

公开(公告)号：US20150316000A1

公开(公告)日：2015-11-05

申请号：US14800762

申请日：2015-07-16

Applicant: United Technologies Corporation

Inventor： Timothy S. Snyder ,  Steven W. Burd ,  Randal G. McKinney ,  George F. Titterton, III

IPC: F02K3/10 ,  F02K1/82 ,  F02C7/32 ,  F02C7/22 ,  F01D25/30

CPC classification number: F23R3/20 ,  F01D25/305 ,  F02C7/22 ,  F02C7/2365 ,  F02K1/822 ,  F02K3/10 ,  F05D2240/36 ,  F05D2260/202 ,  F05D2260/30 ,  F23D2207/00 ,  F23R3/28

Abstract: Gas turbine engine systems and methods involving enhanced fuel dispersion are provided. In this regard, a representative method for operating a gas turbine engine includes: providing a gas path through the engine; introducing a spray of fuel along the gas path downstream of a turbine of the engine; and impinging the spray of fuel with a relatively higher velocity flow of air such that atomization of the fuel is increased.

Abstract translation: 提供了燃气涡轮发动机系统和涉及增强的燃料分散的方法。 在这方面，用于操作燃气涡轮发动机的代表性方法包括：提供通过发动机的气体路径; 沿着发动机的涡轮机下游的气体路径引入燃料喷射; 并以相对较高速度的空气流冲击燃料喷射，使得燃料的雾化增加。