Methods and apparatus for operating gas turbine engines
AssigneeGeneral Electric Company
InventorsSrinivasa Range Gowda, Kevin Sean Early, Steven Martens
Life of this patent
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Abstract
A method of assembling a gas turbine engine includes coupling an annular exhaust duct to the gas turbine engine, coupling a plurality of chevrons to the annular exhaust duct, and coupling a chevron actuation system to the annular exhaust duct such that selective operation of the chevron actuation system repositions the plurality of chevrons to adjust an amount convergence of the annular exhaust duct.
Claims18
A method of assembling a gas turbine engine, said method comprising:
- coupling an annular exhaust duct to the gas turbine engine;
- coupling a plurality of chevrons to the annular exhaust duct;
- and
- coupling a chevron actuation system to the annular exhaust duct such that a band extends around an outer periphery of the annular exhaust duct, wherein the band facilitates repositioning the plurality of chevrons to selectively adjust an amount convergence of said annular exhaust duct.
A method of operating a gas turbine engine that includes an annular exhaust duct and a plurality of chevrons coupled to the annular exhaust duct, said method comprising:
- coupling a chevron actuation system to the annular exhaust duct including a band fabricated from a shape memory alloy that has a memorized activation configuration and such that the plurality of chevrons are oriented in a first configuration;
- and
- heating the shape memory alloy such that the plurality of chevrons are reconfigured from the first configuration to an activation configuration.
A gas turbine engine comprising:
- an annular exhaust duct comprising an aft end, said annular exhaust duct for discharging exhaust from an aft end of said gas turbine engine;
- a plurality of circumferentially adjoining chevrons extending from said duct aft end;
- and
- a chevron actuation system coupled to said annular exhaust duct for controlling relative movement of said plurality of chevrons, said chevron actuation system comprising a band fabricated from a shape memory alloy material.
A gas turbine engine comprising:
- an annular exhaust duct comprising an aft end, said annular exhaust duct for discharging exhaust from an aft end of said gas turbine engine;
- and
- a plurality of circumferentially adjoining chevrons extending from said duct aft end, said plurality of circumferentially adjoining chevrons extend from an annular band fabricated from a shape memory alloy material.
Dependencies are inferred from the claim text.