Service tube assembly for a gas turbine engine

1. A service tube assembly for a gas turbine engine of an aircraft, comprising:

a first titanium service tube configured for aerospace applications, the first titanium service tube defining one or more bends;

a first fitting attached to the first titanium service tube, the first fitting having a first abutment surface;

a second titanium service tube configured for aerospace applications, the second titanium service tube defining one or more bends;

a second fitting attached to the second titanium service tube, the second fitting including an adjustable flange having a second abutment surface, the second fitting engaged in a male/female connection with the first fitting, the adjustable flange having a one-piece tubular body directly threadably engaged with a threaded portion of the second fitting to adjustably position the second abutment surface along the second fitting at a location where the second abutment surface abuts the first abutment surface of the first titanium service tube, the second abutment surface of the adjustable flange angularly adjustable about the second fitting in response to a rotation of the one-piece tubular body relative to the second fitting; and

fasteners engageable in registering holes defined in the first and second abutment surfaces, the fasteners clamping the first and second abutment surfaces together, the first and second abutment surfaces having a point of contact disposed radially outwardly from the fasteners relative to a central axis of the service tube assembly, and wherein a radially innermost end of the second abutment surface is in direct contact with a radially innermost end of the first abutment surface.

2. The service tube assembly according to claim 1 , wherein the first abutment surface is part of a fixed flange extending from the first fitting, and wherein the fasteners comprises a pair of fasteners extending through registering holes defined in the first abutment surface of the fixed flange and the second abutment surface of the adjustable flange.

3. The service tube assembly according to claim 2 , wherein the pair of fasteners includes first and second sets of bolts and nuts.

4. The service tube assembly according to claim 2 , wherein the threaded portion includes external threads provided on an outer surface of the second fitting, and wherein the adjustable flange has internal threads threadably engaged with the external threads.

5. The service tube assembly according to claim 4 , wherein the second fitting has a male portion projecting beyond the threaded portion for mating engagement within a female portion of the first fitting.

6. The service tube assembly according to claim 5 , wherein the male portion carries a seal for sealing engagement with an inner surface of the first fitting.

7. The service tube assembly according to claim 6 , wherein the seal includes axially spaced-apart O-rings disposed in corresponding grooves defined on the male portion.

8. The service tube assembly according to claim 5 , wherein the first and second abutment surfaces surround the male portion.

9. The service tube assembly according to claim 1 , wherein the first titanium service tube and the second titanium service tube are oil supply tubes, oil scavenge tubes, air pressure tubes or vent tubes.

10. The service tube assembly according to claim 9 , wherein the first fitting and the second fitting are respectively brazed to the first titanium service tube and the second titanium service tube.

11. The service tube assembly according to claim 1 , wherein the one-piece tubular body of the adjustable flange has an hexagonal end portion for engagement with a torque applying tool.

12. A service tube assembly for a gas turbine engine of an aircraft, comprising:

a first titanium service tube configured for aerospace applications, the first titanium service tube defining one or more bends;

a first fitting attached to an end of the first titanium service tube, the first fitting having a first flange;

a second titanium service tube configured for aerospace applications, the second titanium tube defining one or more bends;

a second fitting attached to an end of the second titanium service tube, the second fitting engageable in a male/female connection with the first fitting, the second fitting having a threaded portion and a second flange, the second flange having a one-piece tubular body with internal threads defined on an inner surface thereof, the internal threads directly threadably engaged with the threaded portion of the second fitting to form a threaded connection, the threaded connection operable to adjust a position of the second flange along the second fitting, the second flange movable to a position in which the second flange abuts the first flange; and

fasteners engageable in registering holes defined in the first and second flanges for clamping the first and second flanges together, the first and second flanges axially abutting each other both radially inwardly and radially outwardly from the fasteners relative to a central axis of the service tube assembly, the registering holes angularly adjustably aligned via the threaded connection between the one-piece tubular body and the second fitting, and wherein a radially innermost end of the second flange is in direct contact with a facing radially innermost end of the first flange.

13. The service tube assembly according to claim 12 , wherein the threaded portion has external threads provided on an outer surface of the second fitting for engagement with the internal threads of the second flange.

14. The service tube assembly according to claim 13 , wherein the second fitting has a male portion projecting beyond the threaded portion for mating engagement within the first fitting.

15. The service tube assembly according to claim 14 , wherein the male portion carries a seal for sealing engagement with an inner surface of the first fitting.

16. The service tube assembly according to claim 15 , wherein the seal includes axially spaced-apart O-ring seals.