Seal vacuum check tool

Patent metadata

Field	Value
Publication number	US-2016238480-A1
Application number	US-201514623329-A
Country	US
Kind code	A1
Filing date	Feb 16, 2015
Priority date	Feb 16, 2015
Publication date	Aug 18, 2016
Grant date	—

Abstract

Aspects of the disclosure are directed to installing a test assembly on an aircraft engine, connecting a vacuum source to at least one port of the test assembly, engaging the vacuum source, and based on determining that a vacuum is maintained in an amount greater than a threshold, determining that a plurality of seals are present in the engine.

First claim

What is claimed is:

1 . A method comprising:
installing a test assembly on an aircraft engine; connecting a vacuum source to at least one port of the test assembly; engaging the vacuum source; and based on determining that a vacuum is maintained in an amount greater than a threshold, determining that a plurality of seals are present in the engine.

2 . The method of claim 1 , wherein the seals are associated with a tube that is used to convey a fluid.

3 . The method of claim 2 , wherein the fluid comprises oil.

4 . The method of claim 2 , wherein the tube is a double-wall tube comprising a first wall that is exterior to a second wall.

5 . The method of claim 1 , wherein the seals comprise a first seal that provides sealing in an axial direction with respect to the engine.

6 . The method of claim 5 , wherein the seals comprise a second seal that provides sealing in a radial direction with respect to the engine.

7 . A test assembly configured to determine whether a plurality of seals are present in an aircraft engine, comprising:
a first o-ring; a second o-ring; a cap; and a port configured to couple to a vacuum source.

8 . The test assembly of claim 7 , wherein the first o-ring is configured to provide sealing with respect to an external environment.

9 . The test assembly of claim 7 , wherein the second o-ring is configured to provide for sealing with respect to a portion of a tube that is internal to a wall.

10 . The test assembly of claim 7 , wherein at least one of the first o-ring and the second o-ring is made of fluorocarbon.

11 . The test assembly of claim 7 , wherein the cap is made of metal.

12 . The test assembly of claim 7 , wherein the cap is made of at least one of aluminum or steel.

13 . The test assembly of claim 7 , wherein the cap is configured to seal an internal passage of a tube.

14 . The test assembly of claim 13 , wherein the cap is configured to seal an outer portion of the tube from the atmosphere.

15 . A system associated with an aircraft engine, comprising:
a double-wall tube configured to convey oil; at least two seals associated with the tube; and a test assembly configured to couple to the engine and used to determine whether the at least two seals are present based on an applied vacuum source.

16 . The system of claim 15 , further comprising the vacuum source.

17 . The system of claim 15 , wherein the double-wall tube comprises a first wall and a second wall, and wherein a cavity is formed between the first wall and the second wall, and wherein the test assembly is configured to attempt to pull air through the at least two seals via the cavity.

18 . The system of claim 15 , wherein the double-wall tube is made of at least one of stainless steel, a nickel-chromium based alloy, or titanium.

Assignees

• United Technologies Corp

Inventors

• Socha Pawel
• Matteson Peter S
• Pergantis John
• Valenti Anthony

Classifications

• G01M3/025 Primary

  Details with respect to the testing of engines or engine parts · CPC title

• G01M3/2869

  for seals not incorporated in a pipe joint · CPC title

• G01M15/14

  Testing gas-turbine engines or jet-propulsion engines · CPC title