Tube assembly for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11352896-B2
Application number	US-202016999135-A
Country	US
Kind code	B2
Filing date	Aug 21, 2020
Priority date	Aug 21, 2020
Publication date	Jun 7, 2022
Grant date	Jun 7, 2022

Abstract

A tube assembly for a gas turbine engine includes a rigid tube having first and second ends for connection to first port and second ports on the gas turbine engine. The first and second ports have different orientations providing for different installation vectors. The tube assembly further includes a tube adapter adjustably connected to the second port and a coupling, which, is, in turn, adjustably mounted to a distal end of the tube adapter for connection with the second end of the tube.

First claim

The invention claimed is:

1. A tube assembly for a gas turbine engine, comprising:
a rigid tube having a first and a second end respectively connectable to a first port and a second port on the gas turbine engine, the first port and the second port respectively having first and second installation vectors, the first and second installation vectors being different;
a tube adapter having a proximal end portion adjustably connectable to the second port; and
a coupling adjustably mountable to a distal end portion of the tube adapter, the coupling connectable to the second end of the rigid tube;
wherein the second port has a central axis, the tube adapter rotatable about the central axis of the second port, and wherein the proximal end portion of the tube adapter is adjustably axially insertable into the second port of the gas turbine engine, and wherein the distal end portion of the tube adapter extends at an angle from the proximal end portion so as to define and elbow.

2. The tube assembly as defined in claim 1 , wherein the tube adapter has at least two degrees of freedom.

3. The tube assembly as defined in claim 2 , wherein the at least two degrees of freedom includes a rotation and a translation of the tube adapter relative to the second port of the gas turbine engine.

4. The tube assembly as defined in claim 1 , wherein the coupling has at least one degree of freedom relative to the tube adapter.

5. The tube assembly as defined in claim 4 , wherein the at least one degree of freedom of the coupling is a translation of the coupling along the distal end portion of the tube adapter.

6. The tube assembly as defined in claim 1 , wherein the coupling is a slip-joint fitting.

7. The tube assembly as defined in claim 1 , wherein braze or weld joints are provided to fixedly secure the tube, the coupling and the tube adapter once the tube, the coupling and the tube adapter have been adjustably joined all together.

8. The tube assembly as defined in claim 1 , wherein axially spaced-apart sealing fins are integrally formed on an outer surface of the proximal end portion of the tube adapter.

9. A gas turbine engine service tube assembly comprising:
a service tube having a first end connected to a first port of a gas turbine engine;
a tube adapter adjustably mounted to a second port of the gas turbine engine for alignment with a second end of the service tube, the first port and the second port having different orientations; and
a coupling adjustably mounted to a distal end of the tube adapter, the coupling extendable relative to the distal end of the tube adapter for engagement with the second end of the service tube;
wherein the tube adapter is an elbow having a proximal end portion slidably engaged in an opening defined by the second port, and the distal end portion extending at an angle from the proximal end portion outwardly from the second port, the proximal end portion being rotatably received in the opening.

10. The gas turbine engine service tube assembly as defined in claim 9 , wherein the proximal end portion of the tube adapter is sealingly engaged with an inner wall of the second port.

11. The gas turbine engine service tube assembly as defined in claim 10 , wherein sealing fins are integrally formed on and spaced-apart along an outer surface of the proximal end portion of the tube adapter.

12. The gas turbine engine service tube assembly as defined in claim 9 , wherein the tube adapter has at least two degrees of freedom including a rotation and a translation of the tube adapter relative to the second port of the gas turbine engine.

13. The gas turbine engine service tube assembly as defined in claim 9 , wherein the coupling is adjustably translatable along the distal end portion of the tube adapter.

14. The gas turbine engine service tube assembly as defined in claim 9 , wherein the coupling is a slip-joint fitting.

15. The gas turbine engine service tube assembly as defined in claim 9 , wherein the first port and the second port are respectively provided on an engine case and a bearing housing.

Assignees

• Pratt & Whitney Canada

Inventors

• Miskie Ryan
• Morenko Oleg

Classifications

• F02C7/06

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title

• F01D9/065 Primary

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F05D2230/64

  using positioning or alignment devices for aligning or centring, e.g. pins · CPC title

• F16L13/08 Primary

  Soldered joints · CPC title

• F05D2240/55

  Seals · CPC title