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US 10,240,561 B2Granted
Aerodynamic track fairing for a gas turbine engine fan nacelle
AssigneeUnited Technologies Corporation
InventorMark Zsurka
Life of this patent
Estimating the term…
Abstract
A gas turbine engine includes an aerodynamic track fairing adjacent to a convergent-divergent nozzle, the aerodynamic track fairing including a localized curvature along an outside edge. The aerodynamic track fairing is configured to offset a circumferential pressure gradient otherwise introduced in part by a transition between the convergent-divergent nozzle with the aerodynamic track fairing.
Claims12
A gas turbine engine comprising:
- a convergent-divergent nozzle including an outlet having a trailing edge;
- and
- an aerodynamic track fairing adjacent to said convergent-divergent nozzle, said aerodynamic track fairing defining a compound edge extending aft from the trailing edge, the aerodynamic fairing including an aft portion that extends toward an aft end of said aerodynamic track fairing to define a primary curvature and a forward portion extending between the trailing edge and said aft portion, the forward portion of the compound edge defining a substantially reverse curvature relative to said primary curvature thereby minimizing a pressure gradient between said convergent-divergent nozzle and said aerodynamic track fairing;
- wherein a width of the aerodynamic fairing at the forward portion is less than a width of the aerodynamic track fairing at the aft portion.
1 more element
Dependencies are inferred from the claim text.