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.

公开(公告)号：US20180216538A1

公开(公告)日：2018-08-02

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 ,  F02C6/08 ,  B64D13/02 ,  B64D13/08

CPC classification number: F02C9/18 ,  B64C2230/04 ,  B64C2230/06 ,  B64D13/006 ,  B64D13/02 ,  B64D13/08 ,  B64D15/04 ,  B64D2013/0618 ,  B64D2033/0233 ,  F02C6/08 ,  F02C7/047 ,  F02C7/185 ,  Y02T50/675

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：US10054312B2

公开(公告)日：2018-08-21

申请号：US14631499

申请日：2015-02-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Zhongtao Dai ,  Kristin Kopp-Vaughan

IPC: F23R3/28 ,  F23R3/14 ,  F23R3/34

CPC classification number: F23R3/283 ,  F23R3/14 ,  F23R3/286 ,  F23R3/343 ,  F23R2900/03042 ,  Y02T50/675

Abstract: A mixer assembly for a gas turbine engine is provided, including a main mixer, and a pilot mixer having an annular housing. The pilot mixer can further include features to cool portions of the annular housing, such as a radial edge of the annular housing.

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：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：US10060629B2

公开(公告)日：2018-08-28

申请号：US14627709

申请日：2015-02-20

Applicant: United Technologies Corporation

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

IPC: F23R3/34 ,  F23R3/28 ,  F23R3/50

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.

公开(公告)号：US09791153B2

公开(公告)日：2017-10-17

申请号：US14634057

申请日：2015-02-27

Applicant: United Technologies Corporation

Inventor： Zhongtao Dai ,  Kristin Kopp-Vaughan ,  Dave Hyland ,  Russell B. Hanson ,  Lexia Kironn

IPC: F23D17/00 ,  F23R3/28 ,  F23R3/36 ,  F23R3/14 ,  F23R3/34 ,  F02C3/04 ,  F02C7/22 ,  F23R3/60

CPC classification number: F23R3/28 ,  F02C3/04 ,  F02C7/22 ,  F05D2220/32 ,  F05D2240/35 ,  F23D17/002 ,  F23R3/14 ,  F23R3/286 ,  F23R3/343 ,  F23R3/36 ,  F23R3/60 ,  F23R2900/00004 ,  F23R2900/00018

Abstract: In various embodiments, a fuel injector may comprise a fuel nozzle and a pilot stage. The fuel nozzle may define a main fuel channel, a secondary fuel channel, a simplex fuel channel and a heat shield area. The main fuel channel may be disposed about at least a portion of the simplex fuel channel. The secondary fuel channel may be disposed about at least a portion of the simplex fuel channel. The heat shield area may be configured to separate and protect the fuel channels from a heat load to prevent fuel coking. The pilot stage may be operatively coupled to the fuel nozzle and may be configured to receive fuel from the secondary fuel channel or the simplex fuel channel. The main stage may be operatively coupled to the fuel nozzle. The main stage may be configured to receive fuel from the main fuel channel.

公开(公告)号：US20150219338A1

公开(公告)日：2015-08-06

申请号：US14335334

申请日：2014-07-18

Applicant: United Technologies Corporation

Inventor： Zhongtao Dai ,  Jeffrey M. Cohen ,  Kristin Kopp-Vaughan ,  James B. Hoke

IPC: F23R3/34 ,  F02C7/22 ,  F23R3/00

CPC classification number: F23R3/346 ,  F02C7/22 ,  F23R3/06 ,  F23R3/34 ,  F23R3/50 ,  F23R2900/00013 ,  F23R2900/00014

Abstract: A combustor assembly includes a first wall, a second wall, a bulkhead and a plurality of fuel injectors. The bulkhead forms a combustion chamber with the first and the second walls. The fuel injectors are configured with the first wall in a unique and/or a fluctuating pattern.

Abstract translation: 燃烧器组件包括第一壁，第二壁，隔板和多个燃料喷射器。 隔板形成具有第一和第二壁的燃烧室。 燃料喷射器以唯一的和/或波动的图案配置有第一壁。

公开(公告)号：US09958162B2

公开(公告)日：2018-05-01

申请号：US14335334

申请日：2014-07-18

Applicant: United Technologies Corporation

Inventor： Zhongtao Dai ,  Jeffrey M. Cohen ,  Kristin Kopp-Vaughan ,  James B. Hoke

IPC: F23R3/34 ,  F23R3/50 ,  F02C7/22 ,  F23R3/06

CPC classification number: F23R3/346 ,  F02C7/22 ,  F23R3/06 ,  F23R3/34 ,  F23R3/50 ,  F23R2900/00013 ,  F23R2900/00014

Abstract: A combustor assembly includes a first wall, a second wall, a bulkhead and a plurality of fuel injectors. The bulkhead forms a combustion chamber with the first and the second walls. The fuel injectors are configured with the first wall in a unique and/or a fluctuating pattern.

公开(公告)号：US20160252252A1

公开(公告)日：2016-09-01

申请号：US14634057

申请日：2015-02-27

Applicant: United Technologies Corporation

Inventor： Zhongtao Dai ,  Kristin Kopp-Vaughan ,  Dave Hyland ,  Russell B. Hanson ,  Lexia Kironn

IPC: F23R3/28 ,  F23R3/60 ,  F02C7/22 ,  F02C3/04

CPC classification number: F23R3/28 ,  F02C3/04 ,  F02C7/22 ,  F05D2220/32 ,  F05D2240/35 ,  F23D17/002 ,  F23R3/14 ,  F23R3/286 ,  F23R3/343 ,  F23R3/36 ,  F23R3/60 ,  F23R2900/00004 ,  F23R2900/00018

Abstract: In various embodiments, a fuel injector may comprise a fuel nozzle and a pilot stage. The fuel nozzle may define a main fuel channel, a secondary fuel channel, a simplex fuel channel and a heat shield area. The main fuel channel may be disposed about at least a portion of the simplex fuel channel. The secondary fuel channel may be disposed about at least a portion of the simplex fuel channel. The heat shield area may be configured to separate and protect the fuel channels from a heat load to prevent fuel coking. The pilot stage may be operatively coupled to the fuel nozzle and may be configured to receive fuel from the secondary fuel channel or the simplex fuel channel. The main stage may be operatively coupled to the fuel nozzle. The main stage may be configured to receive fuel from the main fuel channel.

Abstract translation: 在各种实施例中，燃料喷射器可以包括燃料喷嘴和先导级。 燃料喷嘴可以限定主燃料通道，辅助燃料通道，单体燃料通道和隔热区域。 主燃料通道可以围绕单燃料通道的至少一部分设置。 二次燃料通道可以围绕单燃料通道的至少一部分设置。 隔热区域可以被构造成分离和保护燃料通道免受热负荷以防燃料焦化。 先导级可以可操作地联接到燃料喷嘴，并且可以被配置为从二次燃料通道或单燃料通道接收燃料。 主级可以可操作地联接到燃料喷嘴。 主级可以被配置为从主燃料通道接收燃料。