公开(公告)号：US20150075178A1

公开(公告)日：2015-03-19

申请号：US14028734

申请日：2013-09-17

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Steve Halfmann ,  Mark C. Morris ,  Jason Smoke ,  Brandan Wakefield ,  Bob Mitlin

IPC: F01D5/14

CPC classification number: F01D5/14 ,  F01D5/141 ,  F01D5/22 ,  F01D5/3007 ,  F05D2240/80 ,  F05D2250/184 ,  F05D2250/75 ,  Y02T50/673 ,  Y10T29/49336

Abstract: A turbine rotor blade is provided. The turbine rotor blade includes a root, a platform coupled to the root, and an airfoil extending from the platform. The platform has a leading edge, a trailing edge, a suction side edge, and a pressure side edge. The pressure side edge includes a first concave portion.

Abstract translation: 提供涡轮转子叶片。 涡轮转子叶片包括根部，连接到根部的平台以及从平台延伸的翼型件。 平台具有前缘，后缘，吸力侧边缘和压力侧边缘。 压力侧边缘包括第一凹部。

公开(公告)号：US20190145266A1

公开(公告)日：2019-05-16

申请号：US15810809

申请日：2017-11-13

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Daniel C. Crites ,  Michael Kahrs ,  Brandan Wakefield ,  Ardeshir Riahi

IPC: F01D5/18

Abstract: An airfoil for a rotor blade in a gas turbine engine includes a first side wall and a second side wall joined to the first side wall at a leading edge and a trailing edge. The airfoil further includes a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip and an internal cooling system. The internal cooling system includes a leading edge cooling circuit, a central cooling circuit, and a trailing edge cooling circuit. Each of the internal passages within the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit is bounded in the radial outward direction with a surface that has at least one escape hole or that is positively angled in the radial outward direction relative to a chordwise axis.

公开(公告)号：US11199099B2

公开(公告)日：2021-12-14

申请号：US16826953

申请日：2020-03-23

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Daniel C. Crites ,  Michael Kahrs ,  Brandan Wakefield ,  Ardeshir Riahi

IPC: F01D5/18

Abstract: An airfoil for a rotor blade in a gas turbine engine includes a first side wall and a second side wall joined to the first side wall at a leading edge and a trailing edge. The airfoil further includes a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip and an internal cooling system. The internal cooling system includes a leading edge cooling circuit, a central cooling circuit, and a trailing edge cooling circuit. Each of the internal passages within the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit is bounded in the radial outward direction with a surface that has at least one escape hole or that is positively angled in the radial outward direction relative to a chordwise axis.

公开(公告)号：US20200378262A1

公开(公告)日：2020-12-03

申请号：US16826953

申请日：2020-03-23

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Daniel C. Crites ,  Michael Kahrs ,  Brandan Wakefield ,  Ardeshir Riahi

IPC: F01D5/18

Abstract: An airfoil for a rotor blade in a gas turbine engine includes a first side wall and a second side wall joined to the first side wall at a leading edge and a trailing edge. The airfoil further includes a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip and an internal cooling system. The internal cooling system includes a leading edge cooling circuit, a central cooling circuit, and a trailing edge cooling circuit. Each of the internal passages within the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit is bounded in the radial outward direction with a surface that has at least one escape hole or that is positively angled in the radial outward direction relative to a chordwise axis.

公开(公告)号：US09670781B2

公开(公告)日：2017-06-06

申请号：US14028734

申请日：2013-09-17

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Steve Halfmann ,  Mark C. Morris ,  Jason Smoke ,  Brandan Wakefield ,  Bob Mitlin

IPC: F01D5/14 ,  F01D5/22 ,  F01D5/30

CPC classification number: F01D5/14 ,  F01D5/141 ,  F01D5/22 ,  F01D5/3007 ,  F05D2240/80 ,  F05D2250/184 ,  F05D2250/75 ,  Y02T50/673 ,  Y10T29/49336

Abstract: A turbine rotor blade is provided. The turbine rotor blade includes a root, a platform coupled to the root, and an airfoil extending from the platform. The platform has a leading edge, a trailing edge, a suction side edge, and a pressure side edge. The pressure side edge includes a first concave portion.