公开(公告)号：JP2000320836A

公开(公告)日：2000-11-24

申请号：JP2000115028

申请日：2000-04-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOKE JAMES B

IPC: F23R3/28 ,  F23D11/10

Abstract: PROBLEM TO BE SOLVED: To supply a completely and uniformly mixed air-fuel mixture to a combustion can of a gas-turbine engine. SOLUTION: A hybrid fuel injector 20 comprises a pressure atomization core fuel nozzle 66 and a secondary air injection portion, which operates with a core nozzle 66 to lead a fuel-air mixture to a low-emission combustion can. The air injection portion of the injector 20 includes inner and outer annular air ducts 98 and 138, which comprise swirlers 108 and 152 for swirling inner and outer airflows in a common direction, respectively. The injector 20 further comprises an air distribution baffle 154, which separates the inner airflow into an annular sub-stream radially separated from the centerline 68 of the injector and a plurality of air jets.

公开(公告)号：JP2000304261A

公开(公告)日：2000-11-02

申请号：JP2000115027

申请日：2000-04-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOKE JAMES B ,  MOUNTZ DARYL B ,  OLSEN HOWARD ,  SONNTAG ROBERT M

IPC: F23R3/42 ,  F23D11/00 ,  F23R3/06 ,  F23R3/28 ,  F23R3/46

Abstract: PROBLEM TO BE SOLVED: To reduce exhausting of an NOx, a UHC and smoke by incorporating a first row passing a combustor liner at an intermediate portion of the liner, a second row coincident with the first row rear in a circumferential direction and a third row rear from the first row in a row of a dilution hole, and incorporating a specific size and a circumferential array in the hole of the third row. SOLUTION: In order to supply a jet of dilute air in a combustion area 50, a first row 52 of a dilute hole passes a liner at a substantially intermediately axially common position of an effective axial length L of the liner. A second row 54 of the hole passes the liner at a rear common axial position from the row 52 at a predetermined distance. A third row 56 of the hole passes the liner a rear common axial position at the specific distance. The specific length is longer than a predetermined distance. An arrangement with the size and circumferential direction of the hole 56 of the third row is selected to simulate to a profile specified in a flow of combustion gas generated from a rear end of the combustion can 18.

公开(公告)号：JP2012154617A

公开(公告)日：2012-08-16

申请号：JP2012010600

申请日：2012-01-23

Applicant: United Technologies Corp ,  ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation

Inventor： HOKE JAMES B

IPC: F23R3/14 ,  F02C9/34 ,  F23R3/06 ,  F23R3/28 ,  F23R3/46

CPC classification number: F23R3/14 ,  F23R3/06 ,  F23R3/343 ,  F23R3/50 ,  Y02T50/675

Abstract: PROBLEM TO BE SOLVED: To provide a gas turbine combustor indicative of effective NOemission reduction performance in view of all engine operating conditions.SOLUTION: The gas turbine engine combustor with an annular combustor chamber includes a plurality of main fuel injection/air swirl vane assemblies that are disposed within a peripheral ring extending to enclose the spread in a circumferential direction of a front partition and a plurality of pilot fuel injection/air swirl vane assemblies that are disposed to be dispersed within the peripheral ring of the main fuel injection/air swirl vane assemblies. Fuel supplied to the combustor is selectively distributed between the plurality of main fuel injection/air swirl vane assemblies and the plurality of pilot fuel injection/air swirl vane assemblies according to the level of an output request by the gas turbine engine.

Abstract translation: 要解决的问题：考虑到所有的发动机工作条件，提供一种指示有效NO X 排放减少性能的燃气轮机燃烧器。 解决方案：具有环形燃烧室的燃气涡轮发动机燃烧器包括多个主燃料喷射/空气旋流叶片组件，其设置在外围环中，该外围环围绕前分隔件的圆周方向包围扩展部， 设置成分散在主燃料喷射/空气涡流叶片组件的周围环内的先导燃料喷射/空气涡流叶片组件。 根据燃气涡轮发动机的输出要求的水平，供应到燃烧器的燃料选择性地分配在多个主燃料喷射/空气涡流叶片组件和多个先导燃料喷射/空气涡流叶片组件之间。 版权所有（C）2012，JPO＆INPIT

公开(公告)号：JPH11257665A

公开(公告)日：1999-09-21

申请号：JP37287298

申请日：1998-12-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOKE JAMES B ,  SEGALMAN IRVING ,  SISKIND KENNETH S ,  SMITH REID D C ,  STURGESS GEOFFREY J

IPC: F23R3/26 ,  F23C6/04 ,  F23C7/00 ,  F23C7/02 ,  F23D11/10 ,  F23R3/06 ,  F23R3/58

Abstract: PROBLEM TO BE SOLVED: To contribute to the reduction of discharging of NOx in a gas turbine engine by a method wherein the air stream of a specified amount is introduced from the air port of a combustor at the downstream of a dome by a specified distance into a fuel air spray pattern. SOLUTION: A combustion chamber 6 is provided with side walls 7, 8, connected to a dome or an end surface 9, so as to form a slender and annular combustion chamber 11. Fuel and a first specified amount of air stream are injected into the combustion chamber 6 to form uniformly distributed fuel air spray pattern, flowing at the downstream of the combustion chamber 6 and mixed so as to contain highly rich fuel. A second specified amount of air stream is introduced from the dome 9 into the fuel air spray pattern through the air port 17 of a combustor at the downstream of the dome 9 by a first specified distance. In this case, the first specified distance is 0.75 times of the height of the dome 9 and the second specified amount of air stream is the amount of dilute air enough to cause rapid mixing and quenching of mixture of fuel and air in the mixture of dilute fuel and air.

公开(公告)号：JPH11257664A

公开(公告)日：1999-09-21

申请号：JP37287198

申请日：1998-12-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOKE JAMES B ,  RUP JOHN J JR

IPC: F02C7/232 ,  F23C7/00 ,  F23C7/02 ,  F23D11/10 ,  F23R3/14 ,  F23R3/58

Abstract: PROBLEM TO BE SOLVED: To contribute the reduction or the control of discharging of NOx by a method wherein an axial direction inflow swirler, having an outlet port providing discharged fuel with swirl air, and a radial direction inflow flow swirler, having an outlet port supplying swirler air, are provided in the subject assembly. SOLUTION: A fuel sending system is provided with a fuel sending passage, arriving at an annular discharging part 30 for sending out fuel from a fitting to the discharging port 30. A nozzle head 18 comprises an axial direction inflow flow swirler 32 and a radial direction inflow flow swirler 34. The whirler 32 is constituted of an inlet port end part, for receiving axial direction inflow air, a vane assembly 40, for providing air with swirl, and an air passage 36, coaxial with the center line of the head 18 having an outlet port end part 42 neighbored to the fuel discharging port 30. The radial direction inflow flow swirler 34 is constituted of an outlet port end part 48, neighbored to the fuel discharging port 30, and an annular air passage 46, coaxial with a center line of the outlet port end part 48 as well as an inside end unit 50.

公开(公告)号：WO2014197045A2

公开(公告)日：2014-12-11

申请号：PCT/US2014023504

申请日：2014-03-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ERBAS-SEN NURHAK ,  HOKE JAMES B ,  TU JOHN S ,  PACHECO-TOUGAS MONICA

IPC: F02C7/12 ,  F02C3/14 ,  F23M5/04 ,  F23R3/42

CPC classification number: F23R3/002 ,  F02C7/18 ,  F23R3/005 ,  F23R3/007 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A liner assembly for a combustor of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a grommet with a multiple of grommet cooling passages.

Abstract translation: 根据本公开的一个公开的非限制性实施例的用于燃气涡轮发动机的燃烧器的衬套组件包括具有多个索环冷却通道的索环。

公开(公告)号：WO2015126501A3

公开(公告)日：2015-10-22

申请号：PCT/US2014068377

申请日：2014-12-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： TU JOHN S ,  SNYDER TIMOTHY S ,  HOKE JAMES B ,  BANGERTER JAMES P ,  DUHAMEL DENNIS J ,  BURNS DAVID A

IPC: F23R3/12 ,  F23R3/26 ,  F23R3/42

CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R2900/03041 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A liner panel for use in a combustor for a gas turbine engine includes a forward region including a multiple of effusion passages each directed at an orientation consistent with a local swirl direction of combustion gases. Another liner panel for use in a combustor for a gas turbine engine includes a forward region forward of a dilution passage and an aft region aft of the forward region. The forward region includes a multiple of effusion passages each directed generally circumferentially. The aft region includes a multiple of effusion passages each directed at an orientation generally axially. A method of cooling a wall assembly within a combustor of a gas turbine engine includes orienting a multiple of effusion passages within a forward region consistent with a local swirl direction of combustion gases.

Abstract translation: 用于燃气涡轮发动机的燃烧器中的衬板包括一个包括多个喷射通道的前部区域，每个喷射通道以与燃烧气体的局部涡流方向一致的方向指向。 用于燃气涡轮发动机的燃烧器中的另一衬套面板包括稀释通道前方的前部区域和前部区域的后部后部区域。 前部区域包括多个通常沿周向引导的排出通道。 后部区域包括多个通过轴向大致定向的排出通道。 一种冷却燃气涡轮发动机的燃烧器内的壁组件的方法包括在与燃烧气体的局部涡流方向一致的前向区域内定向多个排出通道。

公开(公告)号：WO2014123624A3

公开(公告)日：2014-10-23

申请号：PCT/US2013075388

申请日：2013-12-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ERBAS-SEN NURHAK ,  HOKE JAMES B ,  CUNHA FRANK J

IPC: F02C7/24 ,  F02C7/12 ,  F23R3/00

CPC classification number: F23R3/002 ,  F23R3/06 ,  F23R2900/03042 ,  Y02T50/675

Abstract: A heat shield for a gas turbine engine includes a hot side with one or more raised features that extend therefrom.

Abstract translation: 用于燃气涡轮发动机的隔热罩包括具有从其延伸的一个或多个凸起特征的热侧。

公开(公告)号：DE60032663T2

公开(公告)日：2007-10-04

申请号：DE60032663

申请日：2000-04-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOKE JAMES B

IPC: F23D11/10 ,  F23R3/28

Abstract: A coke resistant fuel injector 20 for a low emissions combustor can 18 includes a pressure atomizing core nozzle 66 and an airblast secondary injector. The airblast portion of the injector includes inner and outer air passages 98 , 138 for injecting coannular, coswirling streams of inner and outer air into the combustor can. The injector also includes an air distribution baffle 154 that extends radially across the inner air passage 98 to divide the inner air stream into an annular substream A A and a plurality of air jets A J . The presence of the air distribution baffle and the coswirling inner and outer air streams ensures superior fuel-air mixing, which promotes clean burning, helps resist coke formation on the injector surfaces and produces a slightly enriched core of fuel and air to guard against flame blowout during rapid reductions in engine power.

公开(公告)号：AT350623T

公开(公告)日：2007-01-15

申请号：AT00303178

申请日：2000-04-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOKE JAMES B

IPC: F23R3/28 ,  F23D11/10

Abstract: A coke resistant fuel injector 20 for a low emissions combustor can 18 includes a pressure atomizing core nozzle 66 and an airblast secondary injector. The airblast portion of the injector includes inner and outer air passages 98 , 138 for injecting coannular, coswirling streams of inner and outer air into the combustor can. The injector also includes an air distribution baffle 154 that extends radially across the inner air passage 98 to divide the inner air stream into an annular substream A A and a plurality of air jets A J . The presence of the air distribution baffle and the coswirling inner and outer air streams ensures superior fuel-air mixing, which promotes clean burning, helps resist coke formation on the injector surfaces and produces a slightly enriched core of fuel and air to guard against flame blowout during rapid reductions in engine power.