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公开(公告)号：US10386067B2
公开(公告)日：2019-08-20
申请号：US15266036
申请日：2016-09-15
Applicant: United Technologies Corporation
Inventor： San Quach , Scott A. Elliott , Robert M. Sonntag , John S. Tu , Anthony Van , Joseph J. Sedor , Robert Selinsky, Jr. , John J. Rup, Jr. , Neil B. Ridgeway , Gerard V. Cadieux , Jeffrey Leon , Monica Pacheco-Tougas , Lisa A. Jenkins , Lisa Tse , Andrew Cervoni , Frank J. Trzcinski
Abstract: A wall panel assembly includes a first liner panel and a coating. The first liner panel has an inner first liner panel surface and a first liner panel outer surface each axially extending between a first liner panel first end and a first liner panel second end. The coating is disposed on at least one of the first liner panel inner surface and the first liner panel outer surface. The coating has an overall thickness that varies axially between the first liner panel first end and the first liner panel second end.
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公开(公告)号：US10655856B2
公开(公告)日：2020-05-19
申请号：US15105427
申请日：2014-12-19
Applicant: United Technologies Corporation
Inventor： Jonathan J. Eastwood , Dennis M. Moura , Lee E. Bouldin , Monica Pacheco-Tougas
Abstract: A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a major dilution passage having a lip and a first seal boss. The liner panel also includes a minor dilution passage having a second seal boss adjacent the first seal boss.
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公开(公告)号：US20180128485A1
公开(公告)日：2018-05-10
申请号：US15343988
申请日：2016-11-04
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Monica Pacheco-Tougas , Kevin Zacchera
IPC: F23R3/00
CPC classification number: F23R3/002 , F23R2900/00017 , F23R2900/03042
Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel includes a stud free zone downstream of a combustor swirler. A combustor for a gas turbine engine, the combustor including a liner panel mounted to the support shell via a multiple of studs, the liner panel including a stud free zone downstream of each respective combustor swirler, the stud free zone including a multiple of film cooling holes. A method of directing airflow through a wall assembly within a combustor of a gas turbine engine including providing a stud free zone in a forward liner panel downstream of a combustor swirler, the stud free zone including a multiple of film cooling holes.
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4.发明申请TURBINE ENGINE COMBUSTOR HEAT SHIELD WITH ONE OR MORE COOLING ELEMENTS 审中-公开涡轮发动机燃烧器带有一个或多个冷却元件的热风罩公开(公告)号：US20160258626A1
公开(公告)日：2016-09-08
申请号：US15032080
申请日：2014-11-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dennis M. Moura , Monica Pacheco-Tougas , Jonathan J. Eastwood , Lee E. Bouldin
Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a shell and a heat shield that is attacked to the shell. The heat shield includes a rail and a cooling element connected to the rail in a cavity. The cavity extends in a vertical direction between the shell and the heat shield. The cavity fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.
Abstract translation: 为涡轮发动机提供燃烧器壁。 燃烧室壁包括一个外壳和一个受到外壳侵蚀的隔热罩。 隔热罩包括一个导轨和一个连接到空腔中的导轨的冷却元件。 空腔在外壳和隔热罩之间沿垂直方向延伸。 空腔将壳体中的多个孔与隔热罩中的多个孔流体耦合。
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5.发明申请ANGLED COMBUSTOR LINER COOLING HOLES THROUGH TRANSVERSE STRUCTURE WITHIN A GAS TURBINE ENGINE COMBUSTOR 审中-公开燃气轮机内燃机通过在涡轮发动机燃烧器中的横向结构冷却球公开(公告)号：US20160208704A1
公开(公告)日：2016-07-21
申请号：US14913770
申请日：2014-09-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lee E. Bouldin , Dennis M. Moura , Jonathan J. Eastwood , Monica Pacheco-Tougas
Abstract: A wall assembly for use in a combustor of a gas turbine engine includes a transverse structure with at least one effusion passage that extends at an angle a therethrough. The effusion passage includes an inlet in an outer periphery of a wall. A wall assembly within a gas turbine engine include a liner panel generally parallel to a support shell and a transverse structure with at least one effusion passage that extends at an angle a therethrough. The effusion passage includes an inlet in an outer periphery of a wall that is transverse to the liner panel and the support shell.
Abstract translation: 用于燃气涡轮发动机的燃烧器的壁组件包括横向结构，其具有至少一个以其穿过的角度延伸的积液通道。 渗出通道包括在壁的外周的入口。 燃气涡轮发动机内的壁组件包括大致平行于支撑壳体的衬板和具有至少一个以一角度穿过其延伸的积液通道的横向结构。 渗出通道包括横向于衬垫板和支撑壳体的壁的外周中的入口。
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Patent Agency Ranking
公开(公告)号：US20160169515A1
公开(公告)日：2016-06-16
申请号：US14908751
申请日：2014-08-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： John S. Tu , James P. Bangerter , Robert Sze , James B. Hoke , Monica Pacheco-Tougas
CPC classification number: F23R3/06 , F02C7/18 , F23R3/002 , F23R3/005 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
Abstract: A combustor panel an increased cooling holes provided at at least one of a pair of circumferential edges, a leading edge, a trailing edge or a hole circumference. The increase may be defined as a reduction in spacing or an increase in density. In another feature, holes at the circumferential edges may extend outwardly to an outlet in alignment with rails.
Abstract translation: 燃烧器面板具有设置在一对周向边缘，前缘，后缘或孔圆周中的至少一个上的增加的冷却孔。 增加可以被定义为间隔的减小或密度的增加。 在另一个特征中，圆周边缘处的孔可以向外延伸到与轨道对准的出口。
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公开(公告)号：US20200292172A1
公开(公告)日：2020-09-17
申请号：US16799083
申请日：2020-02-24
Applicant: United Technologies Corporation
Inventor： Dennis M. Moura , Jonathan J. Eastwood , Lee E. Bouldin , Monica Pacheco-Tougas
Abstract: An assembly for a turbine engine includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular land. The heat shield is attached to the shell. The land extends vertically between the shell and the heat shield. The land extends laterally between a land outer surface and an inner surface, which at least partially defines a quench aperture in the combustor wall. A lateral distance between the land outer surface and the inner surface varies around the quench aperture.
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公开(公告)号：US10731858B2
公开(公告)日：2020-08-04
申请号：US14913795
申请日：2014-09-16
Applicant: United Technologies Corporation
Inventor： Lee E. Bouldin , Jonathan J. Eastwood , Dennis M. Moura , Monica Pacheco-Tougas
Abstract: A combustor of a gas turbine engine includes a multiple of liner panels mounted to the support shell, at least one of the multiple of liner panels includes a first impingement cavity that operates at a first pressure and a second impingement cavity that operates at a second pressure different than the first pressure. A method of cooling a wall assembly within a combustor of a gas turbine engine includes directing air through a support shell and a liner panel that defines a first impingement cavity and a second impingement cavity. The first impingement cavity operates at a first pressure and the second impingement cavity operates at a second pressure that is different than the first pressure.
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公开(公告)号：US10598382B2
公开(公告)日：2020-03-24
申请号：US14935076
申请日：2015-11-06
Applicant: United Technologies Corporation
Inventor： John S. Tu , James B. Hoke , Monica Pacheco-Tougas , Alexander W. Williams
Abstract: A liner associated with an engine of an aircraft is described. The liner includes a panel and an array of projections configured to enhance a cooling of the panel and distributed on at least part of a first side of the panel that corresponds to a cold side of the panel.
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公开(公告)号：US20160186994A1
公开(公告)日：2016-06-30
申请号：US14912175
申请日：2014-08-06
Applicant: UNITED TECHNOLOGIES CORPORATION
CPC classification number: F23M5/085 , F23R3/002 , F23R3/06 , F23R3/60 , F23R2900/03044 , Y02T50/675
Abstract: A combustor for use in a gas turbine engine has a combustor outer shell. A panel has an inner face which will face hot products of combustion, and a boss surrounding a feature, with the boss extending to an outer end. A spacing surface is spaced from the boss, and is at an outer position that is inward of the outer end of the boss. The spacing surface spaces the panel from the outer shell. A trough is intermediate the boss and the spacing surface. The trough extends to an outer end which is inward of the outer position of the spacing surface. A gas turbine engine is also disclosed.
Abstract translation: 用于燃气涡轮发动机的燃烧器具有燃烧器外壳。 面板具有面向热的燃烧产物的内表面和围绕特征的凸台，凸台延伸到外端。 间隔表面与凸台间隔开，并且处于位于凸台的外端内侧的外部位置。 间隔表面将面板与外壳隔开。 槽位于凸台和间隔表面之间。 槽延伸到位于间隔表面的外部位置内侧的外端。 还公开了一种燃气涡轮发动机。
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