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公开(公告)号：US20200277867A1
公开(公告)日：2020-09-03
申请号：US16751298
申请日：2020-01-24
发明人： Steven D. Porter , Shawn M. McMahon , Kevin Zacchera , Noah Wadsworth , Christopher Whitfield , Sean D. Bradshaw , Dennis M. Moura
摘要： A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.
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公开(公告)号：US10684017B2
公开(公告)日：2020-06-16
申请号：US15027082
申请日：2014-10-21
摘要： An annular grommet is provided for a wall assembly of a combustor section of a gas turbine engine. The annular grommet includes a wall that at least partially defines a chamber. A wall assembly within a gas turbine engine includes a liner panel with a hot side and a cold side. The wall assembly also includes an annular grommet with a passage wall and a flange wall transverse to the passage wall. The annular grommet includes a chamber therein. A method of cooling a wall assembly within a gas turbine engine includes injecting air through a chamber in an annular grommet.
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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
摘要： 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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4.发明申请公开(公告)号：US20190228514A1
公开(公告)日：2019-07-25
申请号：US15875607
申请日：2018-01-19
摘要： A method of assessing damage to a component includes displaying a sensor image of the component in a first viewing pane, displaying a reference image of the component, which is a graphical depiction of the component with accurate dimensions, in a second viewing pane, placing a plurality of first identification markers on the sensor image of the component in the first viewing pane to correspond to a matching location with a second identification marker on the component in the reference image, identifying a region of damage on the component in the sensor image, mapping the region of damage to the component in the reference image using the plurality of first and second identification markers, and calculating a size of the region of damage.
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5.发明申请公开(公告)号：US20190219266A1
公开(公告)日：2019-07-18
申请号：US16238660
申请日：2019-01-03
发明人： Dennis M. Moura , Carey Clum
CPC分类号： F23R3/06 , F01D25/12 , F05D2260/201 , F05D2260/202 , F05D2260/607 , F23R3/002 , F23R3/005 , F23R2900/00004 , F23R2900/03041 , F23R2900/03043 , F23R2900/03044
摘要： A gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface; a second component having an first surface oriented towards the second surface of the first component, a second surface opposite the first surface of the second component, and a cooling hole extending from the second surface of second component to the first surface of second component, wherein the second surface of the first component and the first surface of the second component define a cooling channel therebetween, and wherein the second component has a variable thickness along a first length of the second component, the variable thickness being configured to adjust a distance between the first surface of the second component and the second surface of the first component throughout the first length such that a Mach number of a cross airflow within the cooling channel is adjusted.
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6.发明申请公开(公告)号：US20190186740A1
公开(公告)日：2019-06-20
申请号：US16211805
申请日：2018-12-06
发明人： Dennis M. Moura , Carey Clum
CPC分类号： F23R3/06 , F01D5/189 , F01D9/065 , F05D2220/32 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/221 , F05D2260/607 , F23R3/002 , F23R2900/00004 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045
摘要： A gas turbine engine component assembly comprising: a first component having a first surface, a second surface opposite the first surface, and a plurality of cooling holes extending from the second surface to the first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; and a plurality of dimples located on the second surface of the second component, the plurality of dimples including: a plurality of primary dimples, wherein each of the plurality of primary dimples is located at an impingement point on the second surface of the second component; and a plurality of secondary dimples, each of the plurality of secondary dimples is located at an impingement flow convergence point.
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公开(公告)号：US20180298819A1
公开(公告)日：2018-10-18
申请号：US15490189
申请日：2017-04-18
发明人： Dennis M. Moura , James B. Hoke , Reza Rezvani
摘要： Combustor panels for use in gas turbine engine combustors having a panel body having a peripheral rail around a periphery of the panel body, a first boss formed on the panel body and surrounding a first aperture that passes through the panel body, and a first webbing that extends from the peripheral rail toward the first boss. A first annular channel is formed between the first webbing and the first boss and surrounds the first boss and a first web pocket is formed within the first webbing between the peripheral rail and the first boss and defines a local extension of the first annular channel extending from the first boss to the peripheral rail.
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8.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
摘要： 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.
摘要翻译： 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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9.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
摘要： 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.
摘要翻译： 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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10.发明申请Fuel Schedule for Robust Gas Turbine Engine Transition Between Steady States 审中-公开稳定燃气轮机发动机稳定状态转换燃油时间表公开(公告)号：US20160169120A1
公开(公告)日：2016-06-16
申请号：US14930743
申请日：2015-11-03
发明人： Anthony Van , Dennis M. Moura , James B. Hoke , Thomas A. Bush , Timothy J. Gaudet , Victor M. Pinedo , David Kwoka , Matthew G. Van Eck
CPC分类号： F02C9/28 , F02C7/222 , F02C7/228 , F02C7/232 , F02C9/34 , F05D2220/32 , F05D2270/03 , F05D2270/31 , F05D2270/331 , Y02T50/671
摘要： A fuel injection system for a gas turbine engine can be used to ensure successful transition in all conditions, while avoiding the possibility of steady state, or increasing power mode, operations with an insufficiently filled secondary fuel line. This may be accomplished by altering a pressure in a secondary fuel line. The present disclosure allows for the elimination of individual fuel injector valves, which may reduce the total complexity and number of parts of the fuel injection system.
摘要翻译： 用于燃气涡轮发动机的燃料喷射系统可以用于确保在所有条件下成功的过渡，同时避免在不充分的二次燃料管线下的稳定状态或增加动力模式的操作的可能性。 这可以通过改变二次燃料管线中的压力来实现。 本公开允许消除单独的燃料喷射阀，这可以降低燃料喷射系统的总体复杂性和部件数量。
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