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US 7,546,738 B2Granted
Turbine engine nozzle
AssigneeUnited Technologies Corporation
InventorDonald W. Peters
Life of this patent
Estimating the term…
Abstract
A turbine engine nozzle assembly has an upstream flap and a downstream flap pivotally coupled thereto for relative rotation about a hinge axis. An actuator linkage is coupled to the flaps for actuating the nozzle between a number of throat area conditions. First and second mode struts respectively restrict rotation of the downstream flap in first and second directions.
Claims13
A turbine engine nozzle subassembly comprising:
- an upstream flap;
- a downstream flap pivotally coupled to the upstream flap for relative rotation about a hinge axis;
- an actuator linkage coupled to at least one of the upstream flap and the downstream flap for actuating the upstream and downstream flaps between a plurality of throat area conditions;
- a first mode strut restricting rotation of the downstream flap in a first direction;
- and
- a second mode strut restricting rotation of the downstream flap in a second direction opposite the first direction.
3 more elements
A turbine engine nozzle comprising:
- a static structure;
- a plurality of flap subassemblies each comprising:
- an upstream flap pivotally coupled to the static structure for relative rotation about an axis essentially fixed relative to the static structure;
- and
- a downstream flap pivotally coupled to the upstream flap for relative rotation about a hinge axis;
- and
- means for providing a low mode exit area to jet area ratio that is less sensitive to changes in jet area than is a high mode exit area to jet area ratio.
4 more elements
Dependencies are inferred from the claim text.