公开(公告)号：US20170335699A1

公开(公告)日：2017-11-23

申请号：US15159355

申请日：2016-05-19

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Harry Lester Kington ,  James Neumann

IPC: F01D9/04 ,  F01D25/24

CPC classification number: F01D9/041 ,  B32B18/00 ,  C04B35/80 ,  C04B2237/343 ,  C04B2237/365 ,  C04B2237/38 ,  C04B2237/765 ,  F01D25/162 ,  F01D25/246 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673

Abstract: An inter-turbine duct includes a first annular wall with a ceramic composite material and including a first plurality of layers and a second plurality of layers, the first plurality of layers including a slot extending therethrough; and a first vane with a material of a metal alloy or a ceramic material. The first vane has a first end and a flange extending through the slot with the flange extending away from the first end and being retained between the first plurality of layers and the second plurality of layers of the first annular 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：US20130216368A1

公开(公告)日：2013-08-22

申请号：US13887801

申请日：2013-05-06

Applicant: Honeywell International Inc.

Inventor： Mark C. Morris ,  Harry Lester Kington ,  James Neumann

IPC: F01D9/00

CPC classification number: F01D9/00 ,  F01D5/284 ,  F01D9/041 ,  F05D2300/606 ,  Y02T50/673

Abstract: In accordance with an exemplary embodiment, a turbine stator component includes a first endwall; a second endwall; a first stator airfoil coupled between the first and second endwalls; and a second stator airfoil adjacent to the first airfoil and coupled between the first and second endwalls. The first stator airfoil has first crystallographic primary and secondary orientations. The second stator airfoil has second crystallographic primary and secondary orientations, the first crystallographic primary and secondary orientations being different from the second crystallographic primary and secondary orientations.

Abstract translation: 根据示例性实施例，涡轮机定子部件包括第一端壁; 第二端壁 耦合在第一和第二端壁之间的第一定子翼型件; 以及与第一翼型件相邻并且连接在第一和第二端壁之间的第二定子翼型件。 第一定子翼型件具有第一晶体初级和次级取向。 第二定子翼型具有第二晶体初级和次级取向，第一晶体初级和次级取向不同于第二晶体初级和次级取向。

公开(公告)号：US10294807B2

公开(公告)日：2019-05-21

申请号：US15159355

申请日：2016-05-19

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Harry Lester Kington ,  James Neumann

IPC: F01D9/04 ,  F01D25/24 ,  B32B18/00 ,  C04B35/80 ,  F01D25/16

Abstract: An inter-turbine duct includes a first annular wall with a ceramic composite material and including a first plurality of layers and a second plurality of layers, the first plurality of layers including a slot extending therethrough; and a first vane with a material of a metal alloy or a ceramic material. The first vane has a first end and a flange extending through the slot with the flange extending away from the first end and being retained between the first plurality of layers and the second plurality of layers of the first annular wall.

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：US08876471B2

公开(公告)日：2014-11-04

申请号：US13887801

申请日：2013-05-06

Applicant: Honeywell International Inc.

Inventor： Mark C. Morris ,  Harry Lester Kington ,  James Neumann

IPC: F01D9/04 ,  F01D9/00 ,  F01D5/28

CPC classification number: F01D9/00 ,  F01D5/284 ,  F01D9/041 ,  F05D2300/606 ,  Y02T50/673

Abstract: In accordance with an exemplary embodiment, a turbine stator component includes a first endwall; a second endwall; a first stator airfoil coupled between the first and second endwalls; and a second stator airfoil adjacent to the first airfoil and coupled between the first and second endwalls. The first stator airfoil has first crystallographic primary and secondary orientations. The second stator airfoil has second crystallographic primary and secondary orientations, the first crystallographic primary and secondary orientations being different from the second crystallographic primary and secondary orientations.

Abstract translation: 根据示例性实施例，涡轮机定子部件包括第一端壁; 第二端壁 耦合在第一和第二端壁之间的第一定子翼型件; 以及与第一翼型件相邻并且连接在第一和第二端壁之间的第二定子翼型件。 第一定子翼型件具有第一晶体初级和次级取向。 第二定子翼型具有第二晶体初级和次级取向，第一晶体初级和次级取向不同于第二晶体初级和次级取向。