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US 12,123,314 B2Granted
Service tube assembly for a gas turbine engine
AssigneePratt & Whitney Canada Corp.
InventorsGuy Lefebvre, Remy Synnott
Life of this patent
Estimating the term…
Abstract
A gas turbine engine has a service tube assembly including an adjustable joint having a flange axially movable along an end fitting having a male/female connection with a mating part. The flange is threadably engaged with the end fitting to provide for the adjustment of the position of the flange along the end fitting.
Claims16
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.
3 more elements
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.
3 more elements
Dependencies are inferred from the claim text.