Helical dynamic seal ring

Patent metadata

Field	Value
Publication number	US-12344369-B2
Application number	US-202318312863-A
Country	US
Kind code	B2
Filing date	May 5, 2023
Priority date	May 5, 2023
Publication date	Jul 1, 2025
Grant date	Jul 1, 2025

Abstract

A helically shaped dynamic seal ring is provided. The helically shaped dynamic seal ring includes a spirally wound body and a snubbing orifice area formed in the spirally wound body. The spirally wound body is configured to expand in response to contacting a snubbed stroke range of an actuator piston. The spirally wound body is configured to contract in response to distancing from the snubbed stroke range of the actuator piston.

First claim

What is claimed is:

1. A landing gear assembly, comprising:
an actuator cylinder;
an actuator piston slidably disposed within the actuator cylinder; and
a helically shaped dynamic seal ring, the helically shaped dynamic seal ring comprising:
a spirally wound body; and
a snubbing orifice area formed in the spirally wound body, wherein:
the spirally wound body is configured to expand in response to contacting a snubbed stroke range of the actuator piston, and
the spirally wound body is configured to contract in response to distancing from the snubbed stroke range of the actuator piston,

wherein the helically shaped dynamic seal ring is configured to be positioned within a seal groove of a bearing and held within the seal groove via a snap ring,
wherein the bearing is positioned within an end of the actuator cylinder and wherein the bearing is positioned around a shaft portion of the actuator piston, and
wherein fluid is configured to flow between the helically shaped dynamic seal ring and a standard stroke range of the actuator piston and out an opening of the bearing in response to the helically shaped dynamic seal ring being distanced from the snubbed stroke range of the actuator piston.

2. The landing gear assembly of claim 1 , wherein the snubbing orifice area may be decreased by removing material from a face of the spirally wound body.

3. The landing gear assembly of claim 1 , wherein the snubbing orifice area may be increased by removing material from at least one end of the spirally wound body.

4. The landing gear assembly of claim 1 , wherein the fluid is further configured to flow between the helically shaped dynamic seal ring and the seal groove and out an opening of the bearing in response to the helically shaped dynamic seal ring being in contact with the snubbed stroke range of the actuator piston.

5. The landing gear assembly of claim 1 , wherein the spirally wound body is at least one of a spirally or spring wound rectangular wire whose turns or revolutions are kept in contact or a spiral cut tube.

6. An aircraft, comprising:
a landing gear assembly, the landing gear assembly comprising:
an actuator cylinder;
an actuator piston slidably disposed within the actuator cylinder; and
a helically shaped dynamic seal ring, the helically shaped dynamic seal ring comprising:
a spirally wound body; and
a snubbing orifice area formed in the spirally wound body, wherein:
the spirally wound body is configured to expand in response to contacting a snubbed stroke range of the actuator piston, and
the spirally wound body is configured to contract in response to distancing from the snubbed stroke range of the actuator piston,

wherein the helically shaped dynamic seal ring is positioned within a seal groove of a bearing and wherein the helically shaped dynamic seal ring is held within the seal groove via a snap ring,
wherein the bearing is positioned within an end of the actuator cylinder and wherein the bearing is positioned around a shaft portion of the actuator piston, and
wherein fluid is configured to flow between the helically shaped dynamic seal ring and a standard stroke range of the actuator piston and out an opening of the bearing in response to the helically shaped dynamic seal ring being distanced from the snubbed stroke range of the actuator piston.

7. The aircraft of claim 6 , wherein the snubbing orifice area is changeable by removing material from the spirally wound body.

8. The aircraft of claim 6 , wherein the fluid is further configured to flow between the helically shaped dynamic seal ring and the seal groove and out an opening of the bearing in response to the helically shaped dynamic seal ring being in contact with the snubbed stroke range of the actuator piston.

Assignees

• Goodrich Corp

Inventors

• Madey Kyle M

Classifications

• F16J9/04

  Helical rings · CPC title

• F16F9/368

  Sealings in pistons · CPC title

• F16F9/362

  Combination of sealing and guide arrangements for piston rods (F16F9/361, F16F9/365 take precedence) · CPC title

• F16F9/36

  Special sealings, including sealings or guides for piston-rods ({F16F9/325, F16F9/3485 take precedence; arrangements for filling via piston rod sealing or guiding means F16F9/432} ; sealing of moving parts in general F16J15/16 - F16J15/56) · CPC title

• F15B15/1452

  Piston sealings · CPC title