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US 2020/0325849 A1Published application
Dual function cascade integrated variable area fan nozzle and thrust reverser
AssigneeRaytheon Technologies Corporation
InventorRichard M. Marshall
Life of this patent
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Abstract
A gas turbine engine system according to an exemplary aspect of the present disclosure may include a core engine defined about an axis, a fan driven by the core engine about the axis to generate bypass flow, and at least one integrated mechanism in communication with the bypass flow. The at least one integrated mechanism includes a variable area fan nozzle (VAFN) and thrust reverser, and a plurality of positions to control bypass flow.”
Claims23
A gas turbine engine comprising:
- a core engine defined about an axis;
- a fan driven by said core engine about said axis to generate bypass flow, wherein the bypass flow defines a bypass ratio greater than about six (6);
- and
- at least one integrated mechanism in communication with the bypass flow, the at least one integrated mechanism including a variable area fan nozzle (VAFN) and a thrust reverser, the integrated mechanism including a plurality of positions to control bypass flow.
1 more element
A gas turbine engine comprising:
- a core engine defined about an axis, said core engine including at least a low pressure turbine which defines a pressure ratio that is greater than about five (5);
- a fan couple to be driven by said core engine about said axis to generate a bypass flow;
- and
- at least one integrated mechanism in communication with the bypass flow, the at least one integrated mechanism including a variable area fan nozzle (VAFN) and a thrust reverser, the integrated mechanism including a plurality of positions to control bypass flow, wherein the integrated mechanism includes a section common to the thrust reverser and VAFN.
1 more element
Dependencies are inferred from the claim text.