Patent ID: 9657686
Date: 2017-05-23
CPC Classifications: F02K

Claim:
1. A method of creating reverse thrust in an aircraft having a gas turbine, the gas turbine comprising a nacelle with a thrust reverser system, the thrust reverser system comprising a plurality of ducts, each duct defining a channel having an inlet and an outlet, each duct comprising a flow directing device, located at the outlet and having an opening positioned at an inner wall of a fan air duct, and a valve operatively coupling the inlet to a high pressure output of a gas turbine, the valve being configured to conduct a high pressure air flow from the high pressure output to the inlet in response to a predetermined condition, the nacelle further comprising a cascade array located radially outward from the fan air duct, wherein the plurality of ducts are circumferentially disposed along the fan air duct within a common axial plane, wherein each outlet of the plurality of ducts are coupled to the fan air duct, wherein each flow directing device is circumferentially discrete, and wherein each flow directing device is configured to distribute the high pressure air flow across a respective portion of a width of the cascade array, the method comprising: directing the high pressure airflows through the flow directing devices in response to a predetermined condition, wherein the flow directing devices are configured to conduct the high pressure airflows into the fan air duct to form a wall of air; and inhibiting the flow of bypass air in the fan air duct using the wall of air to direct the flow of bypass air radially outward, with respect to a centerline of the gas turbine, through the cascade array to create reverse thrust.