Aircraft repair patch applicator tool

Patent metadata

Field	Value
Publication number	US-10875266-B2
Application number	US-201715610777-A
Country	US
Kind code	B2
Filing date	Jun 1, 2017
Priority date	Jun 1, 2017
Publication date	Dec 29, 2020
Grant date	Dec 29, 2020

Abstract

A repair tool for applying a coating patch includes a heating element, a flexible bladder disposed adjacent the heating element, and an inflexible shell disposed about the flexible bladder. The inflexible shell defines a negative space corresponding to a plurality of sides of an aircraft component. A controller is communicatively coupled to the heating element and the bladder, and is configured to control a temperature of the heating element and a pressure of the flexible bladder.

First claim

The invention claimed is:

1. A repair tool for applying a coating patch comprising:
a heating element including an approximately 180 degree bend at a patching position;
a flexible bladder disposed adjacent the heating element;
an inflexible shell disposed about the flexible bladder, the inflexible shell defining a negative space corresponding to a plurality of sides of an aircraft component; and
a controller communicatively coupled to the heating element and the flexible bladder, the controller being configured to control a temperature of the heating element and a pressure of the flexible bladder.

2. The repair tool of claim 1 , wherein the inflexible shell is configured to at least partially surround the aircraft component.

3. The repair tool of claim 1 , wherein the flexible bladder is filled with a fluid, and wherein a pressure exerted on the coating patch is controlled by an amount of fluid in the flexible bladder.

4. The repair tool of claim 1 , wherein the heating element is a heating blanket.

5. The repair tool of claim 4 , wherein the heating blanket is a silicon heating blanket.

6. The repair tool of claim 1 , further comprising at least one temperature sensor configured to detect the temperature of the heating element and at least one pressure sensor configured to detect the pressure exerted by the flexible bladder.

7. The repair tool of claim 6 , wherein each of the at least one temperature sensor and the at least one pressure sensor is communicatively coupled to the controller.

8. The repair tool of claim 1 , wherein the flexible bladder is thermally insulating.

9. The repair tool of claim 1 , wherein the flexible bladder is an air filled bladder.

10. The repair tool of claim 1 , wherein the negative space corresponds to a fan inlet case strut for a gas turbine engine.

11. The repair tool of claim 1 , wherein the flexible bladder includes an approximately 180 degree bend at the patching position.

12. The repair tool of claim 1 , wherein the inflexible shell further defines an outgas vent path configured to allow adhesive outgas sing to vent.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Eigner David J

Classifications

• B29L2031/08

  Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers · CPC title

• B29L2031/3076

  Aircrafts (blades, propellers B29L2031/08) · CPC title

• B29L2031/7504

  Turbines · CPC title

• B29C73/12 Primary

  Apparatus therefor, e.g. for applying (B29C73/30 takes precedence) · CPC title

• B29C73/32

  using an elastic element, e.g. inflatable bag · CPC title