公开(公告)号：US20160201897A1

公开(公告)日：2016-07-14

申请号：US14913056

申请日：2014-08-19

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F23C1/08 ,  F23D14/48

CPC classification number: F23C1/08 ,  F23D14/48 ,  F23D2900/11101 ,  F23R3/286 ,  F23R3/36

Abstract: In various embodiments, a dual fuel nozzle (200) for use in a gas 200 turbine engine is provided. The nozzle may be configured to supply and gas and a liquid. The dual fuel nozzle (200) may include an interior wall (217). The interior wall (217) may include a shoulder (219). The shoulder (219) may include one or more gas ports (216). Gas may be discharged through the gas ports (216) and penetrate a mixing zone.

Abstract translation: 在各种实施例中，提供了用于气体200涡轮发动机的双燃料喷嘴（200）。 喷嘴可以被配置成供应气体和液体。 双燃料喷嘴（200）可包括内壁（217）。 内壁（217）可包括肩部（219）。 肩部（219）可以包括一个或多个气体端口（216）。 气体可以通过气体端口（216）排出并穿过混合区域。

公开(公告)号：US20160209038A1

公开(公告)日：2016-07-21

申请号：US14914802

申请日：2014-08-19

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F23R3/14 ,  F23R3/28

CPC classification number: F23R3/14 ,  F23C1/08 ,  F23D11/106 ,  F23D11/107 ,  F23D2900/11101 ,  F23R3/12 ,  F23R3/28 ,  F23R3/36 ,  Y02T50/675

Abstract: A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, the outer air swirler defines an outer annular air passage. An inner air swirler along the axis defines an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler, the annular fuel gas passage terminates with a multiple of skewed slots.

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，外部空气旋流器限定外部环形空气通道。 沿着轴线的内部空气旋流器限定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，环形燃料气体通道以多个倾斜槽终止。

公开(公告)号：US10228137B2

公开(公告)日：2019-03-12

申请号：US14914802

申请日：2014-08-19

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F23R3/12 ,  F23R3/14 ,  F23R3/28 ,  F23R3/36 ,  F23D11/10 ,  F23C1/08

Abstract: A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, the outer air swirler defines an outer annular air passage. An inner air swirler along the axis defines an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler, the annular fuel gas passage terminates with a multiple of skewed slots.