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

IPC: F23R3/16 ,  F23R3/00

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。

公开(公告)号：US20140360698A1

公开(公告)日：2014-12-11

申请号：US13911904

申请日：2013-06-06

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： David Waldman ,  Mark C. Morris ,  Donald G. Godfrey

IPC: F28F1/10 ,  F28F5/00

CPC classification number: F28F1/10 ,  B22F3/1055 ,  F16L27/11 ,  F28D1/05316 ,  F28D7/0058 ,  F28D7/16 ,  F28D2021/0021 ,  F28F1/006 ,  F28F1/08 ,  F28F1/26 ,  F28F5/00 ,  F28F2255/02 ,  F28F2255/18 ,  F28F2265/26 ,  Y02P10/295

Abstract: Unitary heat exchangers having integrally-formed compliant heat exchanger tubes and heat exchange systems including the same are provided. The unitary heat exchanger comprises an inlet plenum and an outlet plenum and a plurality of integrally-formed compliant heat exchanger tubes. The plurality of integrally-formed compliant heat exchanger tubes extend between and are integral with the inlet and outlet plenums to define a heat exchanger first flow passage. Each integrally-formed compliant heat exchanger tube comprises a tubular member and a plurality of integral heat transfer fins extend radially outwardly from at least one portion of the tubular member. The tubular member has a proximal tube end and a distal tube end and comprises a tubular wall having an outer wall surface and an inner wall surface.

Abstract translation: 提供具有整体形成的顺应性热交换器管和包括其的热交换系统的单一热交换器。 整体热交换器包括入口气室和出口增压室以及多个整体形成的顺应性热交换器管。 多个整体形成的顺应性热交换器管在入口和出口增压室之间延伸并且与入口和出口增压室成一体，以限定热交换器第一流动通道。 每个整体形成的柔性热交换器管包括管状构件和从管状构件的至少一部分径向向外延伸的多个整体传热翅片。 管状构件具有近端管端和远端管端，并且包括具有外壁表面和内壁表面的管状壁。

公开(公告)号：US20200378277A1

公开(公告)日：2020-12-03

申请号：US16998523

申请日：2020-08-20

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Daniel C. Crites ,  Mark C. Morris ,  Steven Whitaker ,  David Waldman

IPC: F01D25/32 ,  F01D5/18 ,  F01D5/20

Abstract: A turbine blade includes an airfoil that has a tip region that extends from the leading edge toward the trailing edge, and the tip region is bounded by a wall that extends at an angle. The leading edge has a leading edge cooling circuit that is defined from the platform to a tip flag channel, and the leading edge cooling circuit is in fluid communication with the tip flag channel. The pressure side includes at least one tip dust hole defined through the wall proximate the pressure side, and the at least one tip dust hole has an inlet and an outlet. The airfoil has at least one rib defined on the wall that extends at a second angle to direct the particles and a portion of the cooling fluid into the inlet.

公开(公告)号：US10113433B2

公开(公告)日：2018-10-30

申请号：US13644824

申请日：2012-10-04

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Mark C. Morris ,  David Waldman ,  Malak Fouad Malak ,  Luis Tapia

IPC: F01D5/18

Abstract: An engine component includes a body having an internal surface and an external surface, the internal surface at least partially defining an internal cooling circuit. The engine component further includes a plurality of cooling holes formed in the body and extending between the internal cooling circuit and the external surface of the body. The plurality of cooling holes includes a first cooling hole with forward diffusion and lateral diffusion.

公开(公告)号：US09816389B2

公开(公告)日：2017-11-14

申请号：US14055568

申请日：2013-10-16

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Malak Fouad Malak ,  Mark C. Morris ,  David Waldman

IPC: F01D11/10 ,  F01D5/18

CPC classification number: F01D11/10 ,  F01D5/187 ,  F05D2240/307 ,  Y02T50/673 ,  Y02T50/676

Abstract: In accordance with an exemplary embodiment, a turbine rotor blade is provided for a turbine section of an engine. The turbine rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the turbine section. The airfoil includes a first side wall; a second side wall joined to the first side wall at a leading edge and a trailing edge; a tip cap extending between the first side wall and the second side wall; a first parapet wall extending from the first side wall; a first parapet wall cavity formed at least partially within the first parapet wall; and a first cooling hole extending between the first parapet wall cavity and a first surface of the first parapet wall such that cooling air flows through the first parapet wall cavity, through the first cooling hole, and out of the first parapet wall.

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

IPC: F23R3/16 ,  F23R3/00 ,  F23R3/06

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。

公开(公告)号：US20150110621A1

公开(公告)日：2015-04-23

申请号：US14061498

申请日：2013-10-23

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Marshall Saville ,  Keith Alan Hurley ,  Joseph Yanof ,  Tina Hynes ,  David Waldman

IPC: F16J15/16 ,  F16J15/32 ,  F04D29/12

CPC classification number: F16J15/164 ,  F01D11/025 ,  F04D29/10 ,  F04D29/102 ,  F05D2240/57 ,  F05D2240/59 ,  F16C17/024 ,  F16C2360/23 ,  F16J15/3212 ,  F16J15/3288 ,  F16J15/445

Abstract: Embodiments of a gas turbine engine including a finger-foil seal are provided, as are embodiments of a finger-foil seal. In one embodiment, the finger-foil seal includes an aerodynamic foil having a generally annular body through which a first opening is formed. A finger seal retention structure is disposed around the aerodynamic foil. A finger seal backing spring is coupled to the finger seal retention structure and extends radially inward therefrom to contact an outer circumference of the aerodynamic foil. A first anti-rotation pin extends radially from the finger seal retention structure and into the first opening formed in the aerodynamic foil to inhibit rotation of the aerodynamic foil during operation of the finger-foil seal.

Abstract translation: 提供包括指箔密封件的燃气涡轮发动机的实施例，如指箔密封件的实施例。 在一个实施例中，指箔密封件包括具有大致环形主体的空气动力箔，通过该主体形成第一开口。 手指密封保持结构设置在空气动力学箔的周围。 手指密封背衬弹簧联接到手指密封保持结构并且从其径向向内延伸以接触空气动力学箔的外周。 第一防旋转销从指状密封保持结构径向延伸并且形成在空气动力学箔中形成的第一开口中，以在手指箔密封件的操作期间阻止气动箔的旋转。

公开(公告)号：US20140099189A1

公开(公告)日：2014-04-10

申请号：US13644824

申请日：2012-10-04

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Mark C. Morris ,  David Waldman ,  Malak Fouad Malak ,  Luis Tapia

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F05D2250/324 ,  F05D2250/71 ,  F05D2250/711 ,  F05D2260/202 ,  Y02T50/676

Abstract: An engine component includes a body having an internal surface and an external surface, the internal surface at least partially defining an internal cooling circuit. The engine component further includes a plurality of cooling holes formed in the body and extending between the internal cooling circuit and the external surface of the body. The plurality of cooling holes includes a first cooling hole with forward diffusion and lateral diffusion.

Abstract translation: 发动机部件包括具有内表面和外表面的本体，所述内表面至少部分地限定内部冷却回路。 发动机部件还包括形成在主体中并在内部冷却回路和主体的外表面之间延伸的多个冷却孔。 多个冷却孔包括具有正向扩散和横向扩散的第一冷却孔。