公开(公告)号：US20200025090A1

公开(公告)日：2020-01-23

申请号：US16270226

申请日：2019-02-07

Applicant: United Technologies Corporation

Inventor： James B. Hoke ,  Timothy S. Snyder ,  David Kwoka ,  Robert M. Sonntag

IPC: F02C7/22 ,  F02C7/228 ,  F02C9/28

Abstract: A fuel system for a gas turbine engine includes a plurality of duplex nozzles arranged on each side of top dead center and a plurality of simplex nozzles. A primary manifold is operable to communicate fuel to a primary flow jet in each of the plurality of duplex nozzles and a secondary manifold is operable to communicate fuel to a secondary flow jet in each of the plurality of duplex nozzles and a secondary flow jet in each of the plurality of simplex nozzles. An equalizer valve that is in communication with both the primary manifold and the secondary manifold distributes fuel at various pressures to both the primary and secondary manifolds.

公开(公告)号：US10240533B2

公开(公告)日：2019-03-26

申请号：US13832507

申请日：2013-03-15

Applicant: United Technologies Corporation

Inventor： James B. Hoke ,  Timothy S. Snyder ,  David Kwoka ,  Robert M. Sonntag

IPC: F02C7/22 ,  F02C7/228 ,  F02C9/28

Abstract: A fuel system for a gas turbine engine includes a plurality of duplex nozzles arranged on each side of top dead center and a plurality of simplex nozzles. A primary manifold is operable to communicate fuel to a primary flow jet in each of the plurality of duplex nozzles and a secondary manifold is operable to communicate fuel to a secondary flow jet in each of the plurality of duplex nozzles and a secondary flow jet in each of the plurality of simplex nozzles. An equalizer valve that is in communication with both the primary manifold and the secondary manifold distributes fuel at various pressures to both the primary and secondary manifolds.

公开(公告)号：US20170254538A1

公开(公告)日：2017-09-07

申请号：US15062440

申请日：2016-03-07

Applicant: United Technologies Corporation

Inventor： John S. Tu ,  James B. Hoke ,  David Kwoka ,  Jonathan Jeffery Eastwood

IPC: F23R3/00 ,  F02C3/04

CPC classification number: F23R3/002 ,  F05D2240/15 ,  F05D2260/201 ,  F23M5/00 ,  F23M5/04 ,  F23M5/08 ,  F23M5/085 ,  F23R3/005 ,  F23R3/04 ,  F23R3/06 ,  F23R2900/00005 ,  F23R2900/00017 ,  F23R2900/03041 ,  F23R2900/03044

Abstract: A combustor of a gas turbine engine including a combustor shell having an interior surface, a first panel mounted to the interior surface at a first position and a second panel mounted to the interior surface at a second position. The first panel has a first end, a first combustion chamber surface parallel with the interior surface, a first rail extending from the first combustion chamber surface toward the interior surface of the combustor shell, and a first extension extending axially from the first rail to the end of the first panel. The second panel has a second end, a second combustion chamber surface, and a second rail extending from the second combustion chamber surface toward the interior surface of the combustor shell. The first end and the second end are proximal to each other and define a circumferentially extending gap there between.

公开(公告)号：US09605598B2

公开(公告)日：2017-03-28

申请号：US14884487

申请日：2015-10-15

Applicant: United Technologies Corporation

Inventor： James B. Hoke ,  Anthony Van

IPC: F02C9/26 ,  F02C7/228 ,  F02C7/232 ,  F02C9/34

CPC classification number: F02C9/263 ,  F02C7/228 ,  F02C7/232 ,  F02C9/34 ,  F05D2260/96 ,  F05D2270/14

Abstract: Aspects of the disclosure are directed to controlling a distribution of fuel to a plurality of nozzles associated with at least one aircraft engine by: determining a state of operation associated with the at least one aircraft engine, causing a valve coupled to a fuel supply and each of the nozzles to open when it is determined that the state of operation indicates a high power state relative to at least one threshold, and causing the valve to close when it is determined that the state of operation indicates a low power state relative to the at least one threshold.

公开(公告)号：US20170003027A1

公开(公告)日：2017-01-05

申请号：US15106032

申请日：2015-01-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Stanislav Kostka ,  Frank J. Cunha ,  James B. Hoke ,  Timothy S. Snyder ,  Albert K. Cheung ,  Christos Adamopoulos

IPC: F23R3/00 ,  F02C7/18 ,  F23R3/06

CPC classification number: F23R3/005 ,  F02C7/18 ,  F02K1/822 ,  F05D2260/20 ,  F05D2260/201 ,  F23R3/007 ,  F23R3/06 ,  F23R2900/00017 ,  F23R2900/03041 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a cone shaped pin.

Abstract translation: 用于燃气涡轮发动机的燃烧器的衬板包括多个传热增强器。 多个传热增强器中的至少一个包括锥形销。

公开(公告)号：US20160209039A1

公开(公告)日：2016-07-21

申请号：US14601389

申请日：2015-01-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Albert K. Cheung ,  James B. Hoke ,  Randal G. McKinney

IPC: F23R3/28 ,  F02M61/16 ,  F02C7/22 ,  B01F15/02 ,  B01F3/04

CPC classification number: F23R3/286 ,  B01F3/04 ,  B01F15/0274 ,  F02C7/22 ,  F02M61/162 ,  F23D11/383 ,  F23R3/34

Abstract: A combustor is provided. The combustor may include an axial fuel injection system, and a radial fuel injection system aft of the axial fuel injection system. The axial fuel injection system includes a mixer having a bluff body at an exit port of the mixer, and a fuel injector disposed within the mixer. A fuel and air mixer is also provided and comprises an outer housing with an exit port and a bluff body. The bluff body extends across the exit port of the outer housing. A fuel injection system is also provided. The systems comprise a mixer having a bluff body at an exit port of the mixer and a fuel injector disposed within the mixer.

Abstract translation: 提供燃烧器。 燃烧器可以包括轴向燃料喷射系统和轴向燃料喷射系统后部的径向燃料喷射系统。 轴向燃料喷射系统包括在混合器的出口处具有非流线体的混合器和设置在混合器内的燃料喷射器。 还提供燃料和空气混合器，并且包括具有出口和非流线体的外壳。 非流线形体延伸穿过外壳的出口。 还提供燃料喷射系统。 该系统包括在混合器的出口处具有非流线体的混合器和设置在混合器内的燃料喷射器。

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：US20160010559A1

公开(公告)日：2016-01-14

申请号：US14770341

申请日：2014-02-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： James B. Hoke ,  James P. Bangerter

IPC: F02C7/25

CPC classification number: F02C7/25 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/231 ,  F23R3/002 ,  F23R2900/00004 ,  F23R2900/00012 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A heat shield for a combustor of a gas turbine engine includes a cold side opposite a hot side, the cold side defines a grommet that surrounds an igniter aperture, the grommet includes a multiple of fins.

Abstract translation: 用于燃气涡轮发动机的燃烧器的隔热罩包括与热侧相对的冷侧，冷侧限定围绕点火器孔的索环，护环包括多个翅片。

公开(公告)号：US11199326B2

公开(公告)日：2021-12-14

申请号：US16723074

申请日：2019-12-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jason M. Gringhaus ,  James B. Hoke ,  Fumitaka Ichihashi

IPC: F23R3/00 ,  F02C7/18 ,  F02C7/24 ,  F23R3/06

Abstract: A liner assembly for use in a combustor of a gas turbine engine is disclosed. In various embodiments, the liner assembly includes a panel defining a left side and a right side and a hot side and a cold side, the panel having a dilution hole and a plurality of effusion holes extending between the hot side and the cold side. In various embodiments, the plurality of effusion holes includes a first subgrouping of effusion holes disposed downstream of the dilution hole and aligned in a generally left to right orientation toward a dividing line extending downstream of the dilution hole and a second subgrouping of effusion holes disposed downstream of the dilution hole and aligned in a generally right to left orientation toward the dividing line extending downstream of the dilution hole.

公开(公告)号：US20200173660A1

公开(公告)日：2020-06-04

申请号：US16664419

申请日：2019-10-25

Applicant: United Technologies Corporation

Inventor： Timothy S. Snyder ,  James B. Hoke

IPC: F23R3/00 ,  F23R3/06 ,  F02C7/18

Abstract: In accordance with one aspect of the disclosure, a combustor is disclosed. The combustor may include a shell and a liner disposed within the shell. The combustor may further include a grommet at least partially defining a hole communicating through the shell and liner and a cooling channel communicating through the grommet.