Duct support

Patent metadata

Field	Value
Publication number	US-11028944-B2
Application number	US-201815994518-A
Country	US
Kind code	B2
Filing date	May 31, 2018
Priority date	May 31, 2018
Publication date	Jun 8, 2021
Grant date	Jun 8, 2021

Abstract

One example of a duct support for a rotorcraft includes a stabilizing mechanism configured to transfer a weight of a duct to an airframe of the rotorcraft, where the duct undergoes thermal expansion. The stabilizing mechanism includes a first stabilizing member attached to the duct, a second stabilizing member attached to the rotorcraft, and a coupling mechanism where the coupling mechanism is configured to couple the first stabilizing member to the second stabilizing member and accommodate thermal expansion of the duct by allowing for movement of the first stabilizing member relative to the second stabilizing member. In an example, the duct is an exhaust duct of an engine of the rotorcraft and heat from the engine cause the exhaust duct to undergo the thermal expansion.

First claim

What is claimed is:

1. A support for a component of a rotorcraft, the support comprising:
a stabilizing mechanism configured to transfer a weight of the component to an airframe of the rotorcraft, wherein the component of the rotorcraft undergoes thermal expansion, wherein the stabilizing mechanism includes:
a first stabilizing member attached to the component of the rotorcraft;
a second stabilizing member attached to the rotorcraft, wherein a portion of the second stabilizing member extends above the airframe of the rotorcraft; and
a coupling mechanism located in the portion of the second stabilizing member that extends above the airframe of the rotorcraft, the coupling mechanism including a barrel with a hollow inside portion and a rod that extends through the inside portion of the barrel along a first axis, wherein a portion of the first stabilizing member extends past the coupling mechanism, wherein the coupling mechanism is configured to rotatably couple the first stabilizing member to the second stabilizing member and-allow the first stabilizing member to simultaneously slide back and forth and to rotate relative to the second stabilizing member about the first axis.

2. The support of claim 1 , wherein the first stabilizing member is coupled to the rod and can slide back and forth on the rod to accommodate thermal expansion and allow for movement of the first stabilizing member relative to the second stabilizing member.

3. The support of claim 1 , wherein the first stabilizing member is secured to the rod and the rod can slide back and forth through the barrel to accommodate thermal expansion and allow for movement of the first stabilizing member relative to the second stabilizing member.

4. The support of claim 1 , wherein the first stabilizing member is an integral part of the component.

5. The support of claim 1 , wherein the component is an exhaust duct of an engine of the rotorcraft and heat from the engine can cause the exhaust duct to undergo the thermal expansion.

6. The support of claim 1 , wherein the first stabilizing member and the portion of the second stabilizing member that extends above the airframe of the rotorcraft extend from the airframe along a second axis, wherein the second axis is substantially perpendicular to the first axis.

7. The support of claim 1 , wherein the component is a duct.

8. The support of claim 7 , wherein the duct is an exhaust duct.

9. A rotorcraft comprising:
an airframe configured to support one or more components of the rotorcraft, the one or more components comprising:
an aircraft system comprising at least one heat generating element;
a duct configured to vent heat from the heat generating element to the environment;
a stabilizing mechanism configured to transfer a weight of the duct to the airframe of the rotorcraft, wherein the duct of the rotorcraft undergoes thermal expansion, wherein the stabilizing mechanism includes:
a first stabilizing member attached to the duct of the rotorcraft;
a second stabilizing member attached to the rotorcraft, wherein a portion of the second stabilizing member extends above the airframe of the rotorcraft; and
a coupling mechanism located in the portion of the second stabilizing member that extends above the airframe of the rotorcraft, the coupling mechanism including a barrel with a hollow inside portion and a rod that extends through the inside portion of the barrel along a first axis, wherein a portion of the first stabilizing member extends past the coupling mechanism, wherein the coupling mechanism is configured to rotatably couple the first stabilizing member to the second stabilizing member and allow the first stabilizing member to simultaneously slide back and forth and to rotate relative to the second stabilizing member about the first axis.

10. The rotorcraft of claim 9 , wherein the first stabilizing member is coupled to the rod and can slide back and forth on the rod to accommodate thermal expansion and allow for movement of the first stabilizing member relative to the second stabilizing member.

11. The rotorcraft of claim 9 , wherein the first stabilizing member is secured to the rod and the rod can slide back and forth through the barrel to accommodate thermal expansion and allowing for movement of the first stabilizing member relative to the second stabilizing member.

12. The rotorcraft of claim 9 , wherein the first stabilizing member is an integral part of the duct.

13. The rotorcraft of claim 9 , wherein the duct is an exhaust duct.

14. The rotorcraft of claim 9 , wherein the heat generating element is an engine, the duct is an exhaust duct of the engine, and heat from the engine can cause the exhaust duct to undergo the thermal expansion.

Assignees

• Bell Helicopter Textron Inc
• Textron Innovations Inc

Inventors

• Scannell Brent
• Mast Thomas
• Bennett Jon Damon
• Edler Joshua Allan
• Paradis Jean Pierre
• Pedersen Keith C

Classifications

• B64C5/00

  Stabilising surfaces · CPC title

• F02C7/00

  Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) · CPC title

• F16L3/202

  the transverse movement being converted to a rotational movement (F16L3/215 takes precedence) · CPC title

• F16L3/18 Primary

  allowing movement in axial direction · CPC title

• B64D33/04 Primary

  of exhaust outlets or jet pipes · CPC title