公开(公告)号：US11753951B2

公开(公告)日：2023-09-12

申请号：US17380397

申请日：2021-07-20

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jason Husband ,  James Glaspey ,  Aaron John Pepin

IPC: F01D5/30 ,  F01D5/14 ,  F01D5/28 ,  F01D11/00 ,  F01D5/02

CPC classification number: F01D5/3053 ,  F01D5/02 ,  F01D5/147 ,  F01D5/282 ,  F01D5/3038 ,  F01D11/008 ,  F05D2240/301 ,  F05D2240/80 ,  F05D2260/30 ,  F05D2260/31 ,  F05D2300/603 ,  F05D2300/702

Abstract: A rotor assembly for a gas turbine engine includes a rotatable hub that has a main body and an array of annular flanges that extend about an outer periphery of the main body to define an array of annular channels. An array of airfoils are circumferentially distributed about the outer periphery. Each one of the airfoils includes an airfoil section extending from a root section received in the annular channels. Retention pins extend through the root section of a respective one of the airfoils and through the array of annular flanges to mechanically attach each root section to the hub.

公开(公告)号：US11499566B2

公开(公告)日：2022-11-15

申请号：US17196359

申请日：2021-03-09

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jason Husband ,  James Glaspey

IPC: F04D29/38 ,  F01D5/14 ,  F01D5/18 ,  F04D19/00 ,  F04D29/32 ,  F04D29/64 ,  F04D29/02 ,  F01D5/12 ,  B23P15/04

Abstract: A method for forming a blade for a gas turbine engine may include forming a suction side sheath and a pressure side sheath, a first cavity and a second cavity established on opposed sides of a rib, forming a structural core configured for positioning in an interior section of the blade between the suction side sheath and the pressure side sheath, the structural core including a first core member, a second core member and a root interconnecting the first and second core members, assembling the suction side sheath and the pressure side sheath with the structural core such that the first core member is positioned in the first cavity and such that the second core member is positioned in the second cavity, and securing the suction side sheath to the pressure side sheath to form the blade.

公开(公告)号：US20210231020A1

公开(公告)日：2021-07-29

申请号：US17030860

申请日：2020-09-24

Applicant: Raytheon Technologies Corporation

Inventor： Jason Husband ,  James Glaspey

IPC: F01D5/30 ,  F01D5/14 ,  F01D5/28

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending from a root section. The airfoil section includes a sheath that receives a core. The core includes first and second ligaments received in respective internal channels defined by the sheath, and each one of the first and second ligaments includes at least one interface portion in the root section dimensioned to receive a retention pin.

公开(公告)号：US20210348515A1

公开(公告)日：2021-11-11

申请号：US17380397

申请日：2021-07-20

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jason Husband ,  James Glaspey ,  Aaron John Pepin

IPC: F01D5/30 ,  F01D5/14 ,  F01D5/28 ,  F01D11/00 ,  F01D5/02

Abstract: A rotor assembly for a gas turbine engine includes a rotatable hub that has a main body and an array of annular flanges that extend about an outer periphery of the main body to define an array of annular channels. An array of airfoils are circumferentially distributed about the outer periphery. Each one of the airfoils includes an airfoil section extending from a root section received in the annular channels. Retention pins extend through the root section of a respective one of the airfoils and through the array of annular flanges to mechanically attach each root section to the hub.

公开(公告)号：US20210199124A1

公开(公告)日：2021-07-01

申请号：US17196359

申请日：2021-03-09

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jason Husband ,  James Glaspey

IPC: F04D29/38 ,  F01D5/14 ,  F01D5/18 ,  F04D19/00 ,  F04D29/32 ,  F04D29/64

Abstract: A method for forming a blade for use with a gas turbine engine may include forming a suction side sheath and a pressure side sheath, the suction side sheath and the pressure side sheath forming a continuous sheath that wraps around an interior section of the blade, a first cavity and a second cavity established on opposed sides of a rib, forming a structural core configured for positioning in the interior section between the suction side sheath and the pressure side sheath, the structural core including a first core member, a second core member and a root interconnecting the first and second core members, assembling the suction side sheath and the pressure side sheath with the structural core positioned there between such that the first core member is positioned in the first cavity and such that the second core member is positioned in the second cavity, and securing the suction side sheath to the pressure side sheath to form the blade. A blade for use in a gas turbine engine is also disclosed.