公开(公告)号：US10794596B2

公开(公告)日：2020-10-06

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: F23R3/36 ,  F23R3/12 ,  F23R3/28 ,  F23D11/38 ,  F23R3/14 ,  F23D11/10 ,  F23D11/12 ,  F23D17/00 ,  F02C7/22

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.

公开(公告)号：US10294873B2

公开(公告)日：2019-05-21

申请号：US15420808

申请日：2017-01-31

Applicant: United Technologies Corporation

Inventor： Federico Papa ,  Bradley C Farnum ,  Kristin Kopp-Vaughan ,  Nathan Roe

IPC: F02C9/18 ,  B64D13/02 ,  B64D13/08 ,  F02C6/08 ,  B64D13/00 ,  B64D15/04 ,  F02C7/047 ,  F02C7/18 ,  B64D13/06 ,  B64D33/02

Abstract: A method of controlling an aircraft bleed may include the steps of monitoring a temperature of a precooled airflow exiting a precooler, and determining a status of a wing anti-ice system of an aircraft. The wing anti-ice system may be configured to receive the precooled airflow from the precooler. The method may further comprise the steps of determining whether an engine operating condition of the aircraft is within an icing envelope, selecting a temperature set point for the precooled airflow based on the status of the wing anti-ice system and whether the aircraft is within an icing envelope, and modulating a fan airflow from a fan to the precooler to adjust the temperature of the precooled airflow to the temperature set point.

公开(公告)号：US20160245523A1

公开(公告)日：2016-08-25

申请号：US14627709

申请日：2015-02-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Wookyung Kim ,  Zhongtao Dai ,  Kristin Kopp-Vaughan

IPC: F23R3/28

CPC classification number: F23R3/286 ,  F23R3/28 ,  F23R3/283 ,  F23R3/34 ,  F23R3/346 ,  F23R3/50

Abstract: A combustor is provided. The combustor may comprise an axial fuel delivery system, and a radial fuel delivery system aft of the axial fuel delivery system. The radial fuel delivery system may be configured to direct fuel at least partially towards the axial fuel delivery system. A radial fuel delivery system is also provided. The system may comprise a combustor including a combustor liner, a mixer coupled to the combustor liner, and a nozzle disposed within the mixer, wherein the mixer and the nozzle are configured to direct fuel in a direction at least partially forward.

Abstract translation: 提供燃烧器。 燃烧器可以包括轴向燃料输送系统和轴向燃料输送系统后部的径向燃料输送系统。 径向燃料输送系统可以构造成将燃料至少部分地引向轴向燃料输送系统。 还提供径向燃料输送系统。 该系统可以包括燃烧器，该燃烧器包括燃烧器衬套，联接到燃烧器衬套的混合器和设置在混合器内的喷嘴，其中混合器和喷嘴构造成沿至少部分向前的方向引导燃料。

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。