公开(公告)号：US09856739B2

公开(公告)日：2018-01-02

申请号：US14030647

申请日：2013-09-18

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Loris Bedrosyan ,  Ardeshir Riahi ,  Daniel C. Crites

IPC: F01D5/20 ,  F01D5/18 ,  F01D11/10

CPC classification number: F01D5/20 ,  F01D5/186 ,  F01D5/187 ,  F01D11/10 ,  F05D2240/307 ,  F05D2260/20 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine rotor blade is provided with for a turbine section of an engine that includes a shroud surrounding the rotor blade. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, a tip cap extending between the suction side wall and the pressure side wall, a first squealer tip extension extending from the pressure side wall at a first angle relative to the pressure side wall, the first squealer tip extension defining a first cooling hole that converges between an inlet and an outlet; an internal cooling circuit configured to deliver cooling air to a gap between the pressure side squealer tip extension and the shroud via the first cooling hole.

公开(公告)号：US20160084103A1

公开(公告)日：2016-03-24

申请号：US14495319

申请日：2014-09-24

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Michael Kahrs ,  Timothy Vander Hoek ,  Loris Bedrosyan ,  Jason Smoke ,  Ardeshir Riahi ,  Daniel C. Crites

IPC: F01D11/12 ,  F01D5/22 ,  B23P15/04

CPC classification number: B23P15/04 ,  B23K20/02 ,  B23K20/233 ,  B23K2101/001 ,  B23K2103/18 ,  B23K2103/26 ,  B23P15/006 ,  F01D5/3061 ,  F01D5/34 ,  F05D2230/232

Abstract: Methods are provided for manufacturing a shrouded bonded turbine rotor. A shrouded blade ring is formed. The shrouded blade ring is formed by bonding a unitary shroud ring to an assembled blade ring or assembling a plurality of shrouded turbine blade segments. The shrouded blade ring is bonded to a hub. The shrouded bonded turbine rotors are also provided. The shrouded bonded turbine rotor comprises a shrouded blade ring and a shroud. The shrouded blade ring comprises a plurality of turbine blade segments and a shroud. Each turbine blade segment comprises an airfoil portion including an airfoil having a root and a tip. The shroud covers the tip of each airfoil in the shrouded blade ring. A hub is bonded with the shrouded blade ring.

Abstract translation: 提供了用于制造被覆盖的粘结涡轮转子的方法。 形成有盖的叶片环。 被覆盖的叶片环通过将整体护罩环结合到组装的叶片环或组装多个带盖的涡轮叶片段而形成。 被覆盖的叶片环结合到轮毂。 还提供了带盖的粘合涡轮转子。 被覆盖的粘合涡轮转子包括被覆盖的叶片环和护罩。 被覆盖的叶片环包括多个涡轮叶片段和护罩。 每个涡轮机叶片段包括翼型部分，其包括具有根部和尖端的翼型件。 护罩覆盖被覆盖的叶片环中每个翼型的末端。 轮毂与被覆盖的叶片环结合。

公开(公告)号：US20150078916A1

公开(公告)日：2015-03-19

申请号：US14030647

申请日：2013-09-18

Applicant: Honeywell International Inc.

Inventor： Loris Bedrosyan ,  Ardeshir Riahi ,  Daniel C. Crites

IPC: F01D5/20 ,  F01D5/18

CPC classification number: F01D5/20 ,  F01D5/186 ,  F01D5/187 ,  F01D11/10 ,  F05D2240/307 ,  F05D2260/20 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine rotor blade is provided with for a turbine section of an engine that includes a shroud surrounding the rotor blade. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, a tip cap extending between the suction side wall and the pressure side wall, a first squealer tip extension extending from the pressure side wall at a first angle relative to the pressure side wall, the first squealer tip extension defining a first cooling hole that converges between an inlet and an outlet; an internal cooling circuit configured to deliver cooling air to a gap between the pressure side squealer tip extension and the shroud via the first cooling hole.

Abstract translation: 涡轮转子叶片设置有用于包括围绕转子叶片的护罩的发动机的涡轮机部分。 转子叶片包括平台和从平台延伸到主流气体路径中的翼型件。 翼型件包括压力侧壁，连接到前缘处的压力侧壁的抽吸侧壁和后缘，在吸力侧壁和压力侧壁之间延伸的末端盖，从第一推进器尖端延伸部 压力侧壁相对于压力侧壁成第一角度，第一尖叫尖端延伸部限定在入口和出口之间会聚的第一冷却孔; 内部冷却回路，其构造成经由第一冷却孔将冷却空气输送到压力侧鸣响器末端延伸部和护罩之间的间隙。