Coupling system for connecting a gas turbine engine to an aircraft mounted exhaust system
AssigneeAllison Advanced Development Company
InventorRobert G. Siefker
Life of this patent
Estimating the term…
Abstract
The present invention contemplates a mechanical coupling for connecting a gas turbine engine to an aircraft mounted exhaust system. In one embodiment, the coupling includes a collar mounted to the gas turbine engine proximate the gas turbine engine's outlet. The collar having a pair of spaced elongated recesses formed therein. An inner surface of the exhaust system includes a pair of pins extending into the pair of spaced elongated recesses. The inter-engagement of the pins and recesses connect the gas turbine engine with the exhaust system. The pins being moveable within the recesses in response to movement by the gas turbine engine.
Claims25
A combination, comprising:
- a gas turbine engine having an exit adapted for the passage of an exhaust gas;
- an exhaust member in fluid communication with said exit and adapted for receiving the exhaust gas from said exit;
- and
- a coupling system located substantially within a portion of said exhaust member and connecting said exhaust member with said gas turbine engine, said coupling system has an extending portion extending from and fastened to one of said exhaust member and said gas turbine engine and a receiving portion on the other of said exhaust member and said gas turbine engine for receiving said extending portion therein and allowing relative movement between said portions.
A combination, comprising:
- an aircraft;
- a gas turbine engine coupled to said aircraft;
- said gas turbine engine having an outlet for the passage of exhaust gas;
- an exhaust member in fluid communication with said outlet and adapted for receiving at least a portion of the exhaust gas from said outlet;
- and
- a coupling connecting said exhaust member with said gas turbine engine, said coupling having a first portion extending from and fastened to one of said exhaust member and said gas turbine engine and a second receiving portion on the other of said exhaust member and said gas turbine engine for receiving said first portion therein and allowing relative movement between said portions, wherein said coupling is positioned substantially within said exhaust member.
A combination, comprising:
- an aircraft having a gas turbine engine coupled thereto, said gas turbine engine having an outlet adapted for the passage of an exhaust gas;
- an exhaust system in fluid communication with said outlet and adapted for receiving the exhaust gas from said outlet, said exhaust system having an inlet end and an other end;
- a support member extending between said exhaust system and said aircraft, said support member bearing a portion of the weight of said exhaust system;
- and
- coupling means for connecting said inlet end of the exhaust system with said gas turbine engine.
A combination, comprising:
- an aircraft;
- a gas turbine engine coupled to said aircraft by a plurality of mounts, said plurality of mounts allows at least a portion of said gas turbine engine to move more than an insubstantial amount in one direction, said gas turbine engine having an outlet opening adapted for the passage of an exhaust gas;
- an exhaust system having a first end and a second end positioned in fluid communication with said outlet opening and adapted for receiving at least a portion of the exhaust gas;
- a mechanical support member coupled to said aircraft and said exhaust system for supporting at least a portion of the weight of said exhaust system, said support member spaced from said first end towards said second end;
- and
- a coupling device connecting said first end of said exhaust system with said gas turbine engine, said coupling having a pair of pins coupled to and located within said exhaust system and a pair of spaced elongated recesses coupled with a portion of said gas turbine, said pair of pins interengaging with said pair of elongated recesses to support said first end of the exhaust system and allow said exhaust system to move with said gas turbine engine.
Dependencies are inferred from the claim text.