Bypass duct with angled drag links
AssigneeUnited Technologies Corporation
InventorsSteven H. Zysman, Edward F. Migliaro, JR.
Life of this patent
Estimating the term…
Abstract
A gas turbine engine includes an engine core outer casing and a fan nacelle spaced radially outwardly relative to the engine core outer casing to define a bypass duct. A plurality of drag links is used to pivot blocker doors into a flow blocking position in the bypass duct when a thrust reverser is deployed. The plurality of drag links is located within the bypass duct in an area of non-uniform flow defined by a plurality of local airflow angles. Each drag link is individually configured to align with one of the local flow angles.
Claims21
A gas turbine engine comprising:
- an engine core outer casing;
- a fan nacelle spaced radially outwardly relative to the engine core outer casing to define a bypass duct;
- and
- a plurality of drag links that cause blocker doors to pivot into a flow blocking position in the bypass duct when a thrust reverser is deployed, and wherein the plurality of drag links are located within the bypass duct in an area of non-uniform flow defined by a plurality of local airflow angles, and wherein each drag link is individually configured to align with one of the local flow angles.
A gas turbine engine comprising:
- an engine core outer casing;
- a fan nacelle spaced radially outwardly relative to the engine core outer casing to define a bypass duct;
- a plurality of drag links that cause blocker doors to pivot into a flow blocking position in the bypass duct when a thrust reverser is deployed, and wherein each drag link comprises a link body having a first end pivotally connected to the engine core outer casing at a first pivot attachment and a second end pivotally attached to one of the blocker doors at a second pivot attachment;
- and
- wherein the plurality of drag links are located within the bypass duct in an area of non-uniform flow defined by a plurality of local airflow angles, and wherein each link body is individually configured to align with one of the local flow angles.
A method of assembling a gas turbine engine comprising the steps of:
- (a) providing an engine core outer casing, a fan nacelle spaced radially outwardly relative to the engine core outer casing to define a bypass duct, and a plurality of drag links that cause blocker doors to pivot into a flow blocking position in the bypass duct when a thrust reverser is deployed;
- (b) predicting local airflow angles within the bypass duct;
- and
- (c) individually configuring each drag link to align with one of the local airflow angles when installed within the bypass duct of the gas turbine engine.
Dependencies are inferred from the claim text.