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公开(公告)号：US11549437B2
公开(公告)日：2023-01-10
申请号：US17178418
申请日：2021-02-18
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Hamdullah Ozogul , Atul Verma , Amy Kujala , Michael Wedig , Ryan Meyer , Bradley Culbertson
Abstract: A combustor for a gas turbine engine includes an outer liner having a first end interconnected to an opposite second end by an outer liner wall composed of a plurality of outer segments. The inner liner has a first inner end interconnected to an opposite second inner end by an inner liner wall composed of a plurality of inner segments. The outer liner wall and the inner liner wall define a combustion chamber, and each of the outer wall segments extend at an angle of at least 40 degrees relative to a longitudinal axis. The outer wall segments includes a first segment, a second segment that extends at a second angle relative to the first segment, which is less than a third angle defined between the second segment and a third segment and is substantially the same as a fourth angle defined between the third segment and a fourth segment.
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公开(公告)号：US20160061451A1
公开(公告)日：2016-03-03
申请号：US14475106
申请日：2014-09-02
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Eric Blumer
CPC classification number: F23R3/06 , F01D5/186 , F01D9/023 , F05D2260/202 , F23R3/002 , F23R3/04 , F23R2900/03041 , F23R2900/03042 , Y02T50/675
Abstract: A combustor for a turbine engine is provided. A first liner has a first surface and a second surface. A second liner forms a combustion chamber with the second side of the first liner, and the combustion chamber configured to receive an air-fuel mixture for combustion therein. The first liner defines a plurality of effusion cooling holes configured to form a film of cooling air on the second surface of the first liner. The plurality of effusion cooling holes includes a first effusion cooling hole extending from the first surface to the second surface and including an inlet portion extending from the first surface, a metering portion fluidly coupled to the inlet portion, and an outlet portion fluidly coupled to the metering portion and extending to the second surface. The inlet portion is larger than the metering portion.
Abstract translation: 提供了一种用于涡轮发动机的燃烧器。 第一衬垫具有第一表面和第二表面。 第二衬套形成具有第一衬里的第二侧的燃烧室，并且燃烧室被配置为容纳用于在其中燃烧的空气 - 燃料混合物。 第一衬套限定了多个排出冷却孔，其构造成在第一衬里的第二表面上形成冷却空气的膜。 多个排出冷却孔包括从第一表面延伸到第二表面的第一渗出冷却孔，并且包括从第一表面延伸的入口部分，流体连接到入口部分的计量部分，以及流体连接到 计量部分并延伸到第二表面。 入口部分大于计量部分。
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3.发明申请GAS TURBINE ENGINE COMBUSTORS WITH EFFUSION AND IMPINGEMENT COOLING AND METHODS FOR MANUFACTURING THE SAME USING ADDITIVE MANUFACTURING TECHNIQUES 有权具有冲击和冲击冷却的气体涡轮发动机燃烧器及其使用添加剂制造技术制造相同方法公开(公告)号：US20150226433A1
公开(公告)日：2015-08-13
申请号：US14176686
申请日：2014-02-10
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Dustin Brandt , David Waldman , James Neumann , Art Payne
CPC classification number: F23R3/16 , F23R3/002 , F23R3/06 , F23R2900/00018 , F23R2900/03041 , F23R2900/03044 , Y02T50/675 , Y10T29/49229
Abstract: Disclosed in various exemplary embodiments are turbine engine combustors with effusion and impingement cooling and methods for manufacturing the same. In one exemplary embodiment, disclosed is a combustor for a turbine engine that includes an annular liner portion including a first metering hole positioned on a cold side annular surface of the annular liner portion and an impingement chamber positioned in the annular liner. The impingement chamber connects to an entry hole on the cold side annular surface and includes a cooling air outlet passageway that is angled with respect to a hot side annular surface of the annular liner portion and that connects to an exit hole positioned on the hot side annular surface of the annular liner portion. The first metering hole is connected to the impingement chamber. The cooling air outlet passageway directs the air onto the hot side annular surface and spreads the airflow axially and laterally parallel to the hot side annular surface. Furthermore, a ratio of a radial thickness of the annular liner portion to a diameter of the entry hole is from about 2 to about 6.
Abstract translation: 在各种示例性实施例中公开了具有渗出和冲击冷却的涡轮发动机燃烧器及其制造方法。 在一个示例性实施例中，公开了一种用于涡轮发动机的燃烧器，其包括环形衬套部分，其包括位于环形衬套部分的冷侧环形表面上的第一计量孔和定位在环形衬套中的冲击室。 冲击室连接到冷侧环形表面上的入口，并且包括冷却空气出口通道，其相对于环形衬套部分的热侧环形表面成角度并且连接到位于热侧环形的出口孔 环形衬垫部分的表面。 第一计量孔连接到冲击室。 冷却空气出口通道将空气引导到热侧环形表面上，并使气流沿轴向和横向平行于热侧环形表面扩散。 此外，环形衬套部分的径向厚度与入口孔的直径的比率为约2至约6。
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公开(公告)号：US12092032B1
公开(公告)日：2024-09-17
申请号：US18329041
申请日：2023-06-05
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout
CPC classification number: F02C7/224 , F02C3/22 , F02C7/232 , F05D2240/36 , F05D2260/213 , F05D2260/606
Abstract: A system and method for supplying hydrogen to a combustor of a gas turbine engine includes supplying liquid hydrogen from a liquid hydrogen supply source to a hydrogen supply line that is adapted to be coupled to the combustor of the gas turbine engine. The liquid hydrogen is converted to gaseous hydrogen at a first pressure and is to a pump, which increases the pressure of the gaseous hydrogen to a second pressure. A flowrate of the gaseous hydrogen discharged from the pump is controlled using a fuel metering valve. A portion of the gaseous hydrogen discharged from the pump is received and stored in a high-pressure gaseous hydrogen tank, and a pressure-regulating valve maintains the second pressure at a substantially constant pressure magnitude.
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5.发明授权公开(公告)号：US11988386B2
公开(公告)日：2024-05-21
申请号：US17457441
申请日：2021-12-03
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Duane Peterson , Girish Kanakagiri , Jaydeep Basani , Nagaraja Rudrapatna , Paul Yankowich , Richard R. Bohman , Rodolphe Dudebout , Venkatesha Prasad
CPC classification number: F23R3/283 , F02C7/22 , F02C9/40 , F02C9/44 , F23R3/346 , F23R3/36 , F05D2270/31
Abstract: An injector module includes an injector stem that extends along an injector longitudinal axis between an inlet end and an outlet end of the injector module. The injector module also includes a first fuel line of a first fuel circuit at least partly extending through the injector stem. The first fuel line has a first outlet disposed at the outlet end of the injector stem. The injector module further includes a second fuel line of a second fuel circuit at least partly extending through the injector stem. The second fuel line has a second outlet disposed at the outlet end of the injector stem. The first outlet and the second outlet are spaced apart and have different orientations relative to the injector longitudinal axis. The first fuel line is thermally coupled to the second fuel line.
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Patent Agency Ranking
公开(公告)号：US11959401B1
公开(公告)日：2024-04-16
申请号：US18189739
申请日：2023-03-24
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shakeel Nasir , Atul Verma , Jeffrey Krise , Doni Tapederi , Jacob Salai , Rodolphe Dudebout
CPC classification number: F01D9/04 , F02C3/04 , F23R3/26 , F05D2220/323 , F05D2240/127 , F05D2260/60
Abstract: A deswirl system for a gas turbine engine includes a deswirl shroud, and at least one deswirl vane having a leading end and a trailing end. The deswirl system includes a deswirl hub spaced apart from the deswirl shroud by the at least one deswirl vane. The deswirl hub includes a hub body that extends at a first angle and a hub extension that extends beyond the trailing end of the at least one deswirl vane. The hub extension extends from the hub body at a second angle, and the first angle is different than the second angle.
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公开(公告)号：US11085641B2
公开(公告)日：2021-08-10
申请号：US16200848
申请日：2018-11-27
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Nagaraja S. Rudrapatna , Atul Verma , David Chou , Christopher Zollars
IPC: F23R3/04
Abstract: A combustor for a gas turbine engine includes a first liner having a first surface, a second surface opposite the first surface, and a wall having a thickness defined between the first surface and the second surface. The first liner defines a plurality of effusion cooling holes, and at least one of the effusion cooling holes includes an inlet section spaced apart from the first surface, and a converging section downstream of the inlet section. The inlet section and the converging section are each defined so as to be outside of the thickness. The at least one of the effusion cooling holes includes a metering section downstream of the converging section and a portion of the metering section is defined within the thickness. The at least one of the effusion cooling holes includes an outlet section downstream of the metering section. The outlet section is proximate to the second surface.
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公开(公告)号：US20210116128A1
公开(公告)日：2021-04-22
申请号：US16988119
申请日：2020-08-07
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Sunil James
Abstract: A combustion system and a method of combustion for a gas turbine engine includes a combustor liner defining a combustion chamber. A plurality of fuel nozzle sets extend into, and supply fuel flow to, the combustion chamber. A pilot fuel nozzle injects a first fuel spray in a tangential direction relative to the combustion liner and toward the upstream end of the combustion chamber. A main fuel nozzle injects a second fuel spray toward the exit end of the combustion chamber. At ignition conditions, a majority of the fuel flow is injected through the pilot fuel nozzles, and at high power conditions a majority of the fuel flow is injected through the main fuel nozzles. At high power conditions, a fuel rich mixture is supplied to the combustion chamber, and a row of quench jets are configured to supply air to the combustion chamber, providing rich-quench-lean combustion.
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公开(公告)号：US20200378305A1
公开(公告)日：2020-12-03
申请号：US16423579
申请日：2019-05-28
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Nagaraja Rudrapatna
Abstract: An effusion cooling hole for a component associated with a gas turbine engine extends along a longitudinal axis. The effusion cooling hole includes an inlet section spaced apart from a first surface of the component. The inlet section includes a face orientated transverse to the first surface and defines an inlet through the face that has a first diameter. The effusion cooling hole includes an outlet at a second surface of the component and downstream from the inlet section. The effusion cooling hole includes a diverging section downstream from the inlet section and upstream from the outlet. The diverging section is defined substantially external to a thickness of the component, and the effusion cooling hole transitions from the first diameter to a second diameter at the diverging section. The effusion cooling hole includes an intermediate section that fluidly connects the diverging section to the outlet.
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10.发明授权Gas turbine engine combustors with effusion and impingement cooling and methods for manufacturing the same using additive manufacturing techniques 有权具有渗出和冲击冷却的燃气涡轮发动机燃烧器及其制造方法使用添加剂制造技术公开(公告)号：US09410702B2
公开(公告)日：2016-08-09
申请号：US14176686
申请日：2014-02-10
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Dustin Brandt , David Waldman , James Neumann , Art Payne
CPC classification number: F23R3/16 , F23R3/002 , F23R3/06 , F23R2900/00018 , F23R2900/03041 , F23R2900/03044 , Y02T50/675 , Y10T29/49229
Abstract: Disclosed in various exemplary embodiments are turbine engine combustors with effusion and impingement cooling and methods for manufacturing the same. In one exemplary embodiment, disclosed is a combustor for a turbine engine that includes an annular liner portion including a first metering hole positioned on a cold side annular surface of the annular liner portion and an impingement chamber positioned in the annular liner. The impingement chamber connects to an entry hole on the cold side annular surface and includes a cooling air outlet passageway that is angled with respect to a hot side annular surface of the annular liner portion and that connects to an exit hole positioned on the hot side annular surface of the annular liner portion. The first metering hole is connected to the impingement chamber. The cooling air outlet passageway directs the air onto the hot side annular surface and spreads the airflow axially and laterally parallel to the hot side annular surface. Furthermore, a ratio of a radial thickness of the annular liner portion to a diameter of the entry hole is from about 2 to about 6.
Abstract translation: 在各种示例性实施例中公开了具有渗出和冲击冷却的涡轮发动机燃烧器及其制造方法。 在一个示例性实施例中，公开了一种用于涡轮发动机的燃烧器，其包括环形衬套部分，其包括位于环形衬套部分的冷侧环形表面上的第一计量孔和定位在环形衬套中的冲击室。 冲击室连接到冷侧环形表面上的入口，并且包括冷却空气出口通道，其相对于环形衬套部分的热侧环形表面成角度并且连接到位于热侧环形的出口孔 环形衬垫部分的表面。 第一计量孔连接到冲击室。 冷却空气出口通道将空气引导到热侧环形表面上，并使气流沿轴向和横向平行于热侧环形表面扩散。 此外，环形衬套部分的径向厚度与入口孔的直径的比率为约2至约6。
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