Aircraft propulsion system geartrain

Patent metadata

Field	Value
Publication number	US-12492663-B2
Application number	US-202318233662-A
Country	US
Kind code	B2
Filing date	Aug 14, 2023
Priority date	Aug 12, 2022
Publication date	Dec 9, 2025
Grant date	Dec 9, 2025

Abstract

An assembly is provided for an aircraft. This assembly includes a first rotating structure, a second rotating structure and a seal assembly. The seal assembly is configured to seal an annular gap radially between the first rotating structure and the second rotating structure. The seal assembly includes an arm, a seal element and a seal land. The arm is cantilevered from and extends axially along the second rotating structure. The seal element is connected to the arm and forms a seal interface with the seal land. The seal land is connected to the first rotating structure.

First claim

What is claimed is:

1 . An assembly for an aircraft, comprising:
a first rotating structure; a second rotating structure, the second rotating structure extending axially through a bore of the first rotating structure; a seal assembly configured to seal an annular gap radially between the first rotating structure and the second rotating structure, the seal assembly comprising an arm, a seal element and a seal land, the arm cantilevered from and extending axially along the second rotating structure, the seal element connected to the arm and forming a seal interface with the seal land, and the seal land connected to the first rotating structure; and a bearing disposed radially between the arm and the first rotating structure, the bearing supporting the arm relative to the first rotating structure.

2 . An assembly for an aircraft, comprising:
a first rotating structure rotatable about a first axis; a second rotating structure rotatable about a second axis; a seal assembly configured to seal an annular gap radially between the first rotating structure and the second rotating structure, the seal assembly further configured to accommodate misalignment between the first axis and the second axis, and the seal assembly including a seal land, a seal element and a flexible member connecting the seal element to the second rotating structure, the seal land arranged with the first rotating structure, and the seal element configured to provide a seal interface with the seal land; and a rolling element bearing disposed radially between the flexible member and the first rotating structure, the rolling element bearing radially locating a portion of the flexible member, axially proximate the seal element, relative to the first rotating structure.

3 . The assembly of claim 2 , wherein the flexible member comprises an arm cantilevered from the second rotating structure.

4 . An assembly for an aircraft, comprising:
a first rotating structure; a second rotating structure; a seal assembly configured to seal an annular gap radially between the first rotating structure and the second rotating structure, the seal assembly comprising an arm, a seal element and a seal land, the arm cantilevered from and extending axially along the second rotating structure, the seal element connected to the arm and forming a seal interface with the seal land, and the seal land connected to the first rotating structure; and a bearing disposed radially between the arm and the first rotating structure, the bearing supporting the arm relative to the first rotating structure, and the bearing comprising a bearing inner race, a bearing outer race, and a bearing roller element disposed radially between and engaged with the bearing inner race and the bearing outer race.

5 . The assembly of claim 4 , wherein
the bearing inner race is connected to the arm; the bearing outer race is connected to the first rotating structure; and the bearing roller element is one of a plurality of bearing roller elements arranged circumferentially about a centerline axis of the bearing, and each of the plurality of bearing roller elements is disposed radially between and engaged with the bearing inner race and the bearing outer race.

6 . The assembly of claim 4 , wherein
the bearing inner race is integral with the arm; and the bearing outer race is integral with the first rotating structure.

Assignees

• Rtx Corp

Inventors

• Hanrahan Paul R

Classifications

• F02C7/06

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title

• F16J15/54

  Other sealings for rotating shafts · CPC title

• F05D2300/501

  Elasticity · CPC title

• F05D2230/644

  for adjusting the position or the alignment, e.g. wedges or eccenters · CPC title

• F05D2240/54

  Radial bearings · CPC title