公开(公告)号：US12163582B2

公开(公告)日：2024-12-10

申请号：US17505015

申请日：2021-10-19

Applicant: RTX CORPORATION

Inventor： Michael E. McCune ,  Jason Husband

IPC: F01D25/16 ,  F02C7/36 ,  F02K3/06 ,  F04D25/02 ,  F04D29/053 ,  F04D29/056 ,  F16H1/28 ,  F16H57/028

Abstract: A gas turbine engine including a drive shaft that drives a propulsor. A frame which supports the drive shaft is a K-frame bearing support. A gear system is connected to the drive shaft. The gear system includes a gear mesh that defines a gear mesh lateral stiffness and a gear mesh transverse. A flexible support supports the gear system that defines a flexible support transverse stiffness and a flexible support lateral stiffness. The flexible support lateral stiffness is less than 8% of the gear mesh lateral stiffness.

公开(公告)号：US20230399956A1

公开(公告)日：2023-12-14

申请号：US18456126

申请日：2023-08-25

Applicant: RTX 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 ,  F01D5/147 ,  F01D5/282 ,  F01D11/008 ,  F01D5/02 ,  F01D5/3038 ,  F05D2240/301 ,  F05D2240/80 ,  F05D2260/30 ,  F05D2300/603 ,  F05D2300/702 ,  F05D2260/31

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：US12286905B2

公开(公告)日：2025-04-29

申请号：US18456126

申请日：2023-08-25

Applicant: RTX CORPORATION

Inventor： Jason Husband ,  James Glaspey ,  Aaron John Pepin

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

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：US20250163828A1

公开(公告)日：2025-05-22

申请号：US19027137

申请日：2025-01-17

Applicant: RTX CORPORATION

Inventor： Michael E. McCune ,  Jason Husband

IPC: F01D25/16 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/28 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F04D19/02 ,  F04D25/04 ,  F04D29/053 ,  F04D29/056 ,  F04D29/32

Abstract: A gas turbine engine includes a propulsor that has propulsor blades, a propulsor shaft for driving the propulsor, a propulsor shaft support that supports said propulsor shaft, said propulsor shaft support defining a propulsor shaft support transverse stiffness, a gear system connected to said propulsor shaft, said gear system includes a gear mesh defining a gear mesh transverse stiffness, and a flexible support which supports said gear system relative to a static structure and defines a flexible support transverse stiffness, wherein said flexible support transverse stiffness is less than 11% of said propulsor shaft support transverse stiffness and said flexible support transverse stiffness is less than 8% of said gear mesh transverse stiffness.