Aircraft nozzle
AssigneeROLLS-ROYCE plc
InventorJack F COLEBROOKE
Life of this patent
Estimating the term…
Abstract
A flap for a variable area exhaust nozzle of a gas turbine engine, having a support structure and a gas shield having a plurality of gas shield segments connected to the support structure and adjacently arranged along a longitudinal direction of the flap corresponding to flow through the nozzle. Each of the gas shield segments has a flowpath section arranged to cooperate with a corresponding flowpath section of an adjacent gas shield segment to define a flowpath surface of the gas shield to bound flow through the nozzle. The gas shield segments are configured to permit the respective flowpath section to move longitudinally relative the support structure in response to thermal expansion of the gas shield.
Claims12
A flap for a variable area exhaust nozzle of a gas turbine engine, comprising a support structure and a gas shield having a plurality of gas shield segments connected to the support structure and adjacently arranged along a longitudinal direction of the flap corresponding to flow through the nozzle;
- wherein:
- each of the gas shield segments comprises a flowpath section arranged to cooperate with a corresponding flowpath section of an adjacent gas shield segment to define a flowpath surface of the gas shield to bound flow through the nozzle;
- and
- each of the gas shield segments is configured to permit the respective flowpath section to move longitudinally relative the support structure in response to thermal expansion of the gas shield;
- wherein each gas shield segment comprises arm sections including tabs that are welded to the support structure to anchor the gas shield segments to the support structure.
Dependencies are inferred from the claim text.