Auxiliary component mount including a fusible region configured to break at a predetermined load

Patent metadata

Field	Value
Publication number	US-9982605-B2
Application number	US-201314410487-A
Country	US
Kind code	B2
Filing date	Sep 13, 2013
Priority date	Sep 28, 2012
Publication date	May 29, 2018
Grant date	May 29, 2018

Abstract

A mount for mounting a component to a gas turbine engine is disclosed. The mount may include a central portion that attaches to the component, and a flange circumscribing the central portion and extending to the gas turbine engine, the flange including a fusible region that breaks at a predetermined load. A method for protecting a component mounted to a gas turbine engine is also disclosed. The method may include attaching a mount to a casing of the gas turbine engine, the mount including a fusible region that breaks at a predetermined load. The method may further include attaching the component to the mount. The method may further include the fusible region breaking when the mount experiences the predetermined load, detaching the component from the casing of the gas turbine engine.

First claim

What is claimed is:

1. A mount for mounting a component to a gas turbine engine, comprising:
a central portion that attaches to the component;
a retention element for retaining the component to the gas turbine engine; and
a flange circumscribing the central portion and extending to the gas turbine engine, the flange including a fusible region that breaks at a predetermined load;
wherein the fusible region is a fusible link having reduced stiffness than a rest of the flange, and wherein the retention element includes two retention flanges configured to engage with each other when the fusible link breaks, the fusible link positioned between the two retention flanges.

2. The mount of claim 1 , wherein the fusible region is of a reduced thickness than a thickness of a rest of the flange.

3. The mount of claim 1 , wherein the fusible region is a continuous region around an entire perimeter of the flange.

4. The mount of claim 1 , wherein the flange includes disconnected fusible regions around a perimeter of the flange.

5. The mount of claim 1 , wherein the predetermined load is between an inclusive range of twenty (20) to one hundred (100) times the weight of the component.

6. The mount of claim 1 , wherein the two retention flanges are genereally “L”—shaped.

7. The monut of claim 1 , wherein the central portion is centrally located within the mount and includes pins for receiving bolts.

8. The mount of claim 7 , wherein the flange extends around a perimeter of the central portion from an upper section of the central portion to an outer surface of a casing of the gas turbine engine.

9. A gas turbine engine, comprising:
a fan section;
a compressor section downstream of the fan section;
a combustor section downstream of the compressor section;
a turbine section downstream of the combustor section; and
a casing enclosing at least one of the fan section, the compressor section, the combustor section, and the turbine section, the casing including
a mount disposed on an outer surface of the casing and attached to a component, the mount including:
a central portion that attaches to the component;
a retention element for retaining the component to the casing; and
a flange circumscribing the central portion and extending to the casing, the flange including a fusible region that breaks at a predetermined load;
wherein the fusible region is a fusible link having reduced stiffness than a rest of the flange, and wherein the retention element includes two retention flanges configured to engage with each other when the fusible link breaks, the fusible link positioned between the two retention flanges.

10. The gas turbine engine of claim 9 , wherein the mount is located on the casing in a fan containment zone enclosing the fan section.

11. The gas turbine engine of claim 9 , wherein the mount is integral to the casing.

12. The gas turbine engine of claim 9 , wherein the mount is bonded to the casing.

13. The gas turbine of claim 12 , wherein the flange has a surface bonded to an outer surface of the engine casing.

14. A method for protecting a component mounted to a gas turbine, comprising:
attaching a mount to a casing of the gas turbine engine, the mount including:
a central portion that attaches to the component;
a retention element for retaining the component to the casing; and
a flange circumscribing the central portion and extending to the casing, the flange including a fusible region that breaks at a predetermined load;
wherein the fusible region is a fusible link having reduced stiffness than a rest of the flange, and wherein the retention element includes two retention flanges configured to engage with each other when the fusible link breaks, the fusible link positioned between the two retention flanges;

attaching the component to the mount; and
the fusible region breaking when the mount experiences the predetermined load, detaching the component from the casing of the gas turbine engine.

15. The method of claim 14 , further comprising retaining the component to the casing via the retention element after the fusible region breaks.

16. The method of claim 15 , further comprising the retention element restricting free motion of the component while preventing energy transmission from the casing to the component.

Assignees

• United Technologies Corp

Inventors

• Robertson Thomas J
• Clarkson Steven
• Costa Mark W

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F01D21/045

  special arrangements in stators or in rotors dealing with breaking-off of part of rotor · CPC title

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• F05D2240/90

  Mounting on supporting structures or systems · CPC title