公开(公告)号：US20240141794A1

公开(公告)日：2024-05-02

申请号：US17976345

申请日：2022-10-28

Applicant: Raytheon Technologies Corporation

Inventor： Colin J. Kling ,  Nicholas J. Lawliss

IPC: F01D5/30 ,  F01D11/00

CPC classification number: F01D5/30 ,  F01D11/008 ,  F05D2220/32 ,  F05D2240/80 ,  F05D2250/70 ,  F05D2300/514

Abstract: A rotor assembly is provided that includes a rotor disk, a rotor blade and a rotor spacer. The rotor disk includes a slot. The rotor blade includes a blade root arranged within the slot. The root spacer is arranged within the slot between the rotor disk and the blade root. The root spacer is configured as or otherwise includes a cellular structure with a plurality of internal cells.

公开(公告)号：US12146421B2

公开(公告)日：2024-11-19

申请号：US17976345

申请日：2022-10-28

Applicant: Raytheon Technologies Corporation

Inventor： Colin J. Kling ,  Nicholas J. Lawliss

IPC: F01D11/00 ,  F01D5/30

Abstract: A rotor assembly is provided that includes a rotor disk, a rotor blade and a rotor spacer. The rotor disk includes a slot. The rotor blade includes a blade root arranged within the slot. The root spacer is arranged within the slot between the rotor disk and the blade root. The root spacer is configured as or otherwise includes a cellular structure with a plurality of internal cells.

公开(公告)号：US12065948B1

公开(公告)日：2024-08-20

申请号：US18207909

申请日：2023-06-09

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Colin J. Kling

IPC: F01D5/30 ,  F01D5/32

CPC classification number: F01D5/3007 ,  F01D5/323 ,  F01D5/326 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/60

Abstract: A fan includes a rotor hub comprising a slot and a blade comprising an airfoil extending from a blade root in a first direction. The blade root is configured to be received in the slot. The fan also includes a deformable spacer situated between the rotor hub and the blade root in the slot, a first blade lock situated at a first side of the slot, and a second blade lock situated at a second side of the slot opposite the first side. At least one of the first and second blade locks includes a tab configured to extend between the blade root and the rotor hub and to compress the spacer such that the spacer exerts a force on the blade in the first direction. A method of assembling a fan and another example fan are also disclosed.

公开(公告)号：US20240200659A1

公开(公告)日：2024-06-20

申请号：US18081978

申请日：2022-12-15

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Colin J. Kling ,  David R. Lyders

IPC: F16J15/3272 ,  F16J9/14 ,  F16J15/3284

CPC classification number: F16J15/3272 ,  F16J9/14 ,  F16J15/3284

Abstract: A gas turbine engine includes a rotor that has a sealing surface and a shaft that is rotatable about an engine central axis. The shaft has an annular seal channel that opens to the seal surface, and there is a split seal that is insertable into the annular seal channel for sealing against the seal surface. The split seal includes first and second end sections that are mateable to each other. The split seal has a helical shape when in a state of rest such that the first and second end sections are axially offset from each other.