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1.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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2.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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