Nacelle thrust reverser compression rod supporting system
AssigneeRohr, Inc.
InventorsJinqiu Lu, Frank Zabatta, Travis Michael Frazier, Karina Alejandra Hernandez
Life of this patent
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Abstract
An aircraft nacelle arrangement includes a compression rod disposed between a first nacelle half and a second nacelle half, wherein the first nacelle half and the second nacelle half are rotatable about a hinge between a closed position and an open position, a compression rod disposed between the first nacelle half and the second nacelle half, and a mounting bracket coupled to an exhaust nozzle flange of the aircraft engine, wherein the compression rod extends through the mounting bracket.
Claims20
An aircraft nacelle arrangement, comprising:
- a first half comprising a first engagement feature, and a second half comprising a second engagement feature, wherein the first half and the second half are rotatable about a hinge between a closed position in which the first half and the second half enclose a portion of an aircraft engine, and an open position in which the first half and the second half are separated and allow access to the portion of the aircraft engine;
- a compression rod comprising a first end and a second end, wherein in response to the aircraft nacelle arrangement being in the closed position, the first end is in contact with the first engagement feature and the second end is in contact with the second engagement feature;
- and
- a first mounting bracket coupled to an exhaust nozzle flange of the aircraft engine, wherein the compression rod extends through the first mounting bracket.
An arrangement for an aircraft nacelle, comprising:
- a turbine engine;
- an exhaust assembly coupled to the turbine engine, the exhaust assembly extends aft ward from the turbine engine;
- an exhaust nozzle flange, whereby the exhaust assembly is coupled to the turbine engine;
- a compression rod disposed radially from the exhaust nozzle flange;
- and
- a first mounting bracket coupled to the exhaust nozzle flange, wherein the compression rod extends through the first mounting bracket.
A method for installing a compression rod, comprising:
- coupling a first mounting bracket to an exhaust nozzle flange of an aircraft engine;
- and
- disposing the compression rod to extend through the first mounting bracket.
Dependencies are inferred from the claim text.