Abstract: A first cascade segment of a thrust reverser system has a first cascade segment flow area and is associated with a first lateral sector. A second cascade segment has a second cascade segment flow area and is associated with a second lateral sector. The second cascade segment flow area may be at least 1.2 times the first cascade segment flow area. The first lateral sector has a first leakage flow area and a first total flow area that is equal to a sum of at least the first cascade segment flow area and the first leakage flow area. The second lateral sector has a second leakage flow area and a second total flow area that is equal to a sum of at least the second cascade segment flow area and the second leakage flow area. The second total flow area may be within 10% of the first total flow area.

Abstract: A bullnose ramp is disclosed. In various embodiments, the bullnose ramp includes a forward portion, the forward portion characterized by a first profile; an aft portion, the aft portion characterized by a second profile; and a transition portion positioned proximate an intersection between the forward portion and the aft portion, the transition portion defining a change in slope between the first profile and the second profile.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a forward thrust duct and a thrust reverser system. The thrust reverser system includes a thrust reverser duct, a bullnose ramp and a plurality of protrusions. The bullnose ramp is adapted to provide a transition from the forward thrust duct to the thrust reverser duct when the thrust reverser system is in a deployed configuration. The protrusions are bonded or formed integral with the bullnose ramp. Each of the protrusions is adapted to interact with boundary layer fluid flowing along the bullnose ramp from the forward thrust duct into the thrust reverser duct when the thrust reverser system is in a deployed configuration.

Abstract: An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes a thrust reverser system. The thrust reverser system includes a cascade structure and a scoop. The cascade structure is configured with a plurality of flow passages. Each of the flow passages extends through the cascade structure. The flow passages include a first flow passage. The scoop is configured to direct fluid into at least the first flow passage. The scoop includes a serrated leading edge.

Abstract: A first cascade segment of a thrust reverser system has a first cascade segment flow area and is associated with a first lateral sector. A second cascade segment has a second cascade segment flow area and is associated with a second lateral sector. The second cascade segment flow area may be at least 1.2 times the first cascade segment flow area. The first lateral sector has a first leakage flow area and a first total flow area that is equal to a sum of at least the first cascade segment flow area and the first leakage flow area. The second lateral sector has a second leakage flow area and a second total flow area that is equal to a sum of at least the second cascade segment flow area and the second leakage flow area. The second total flow area may be within 10% of the first total flow area.

Abstract: An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes a thrust reverser system. The thrust reverser system includes a cascade structure and a scoop. The cascade structure is configured with a plurality of flow passages. Each of the flow passages extends through the cascade structure. The flow passages include a first flow passage. The scoop is configured to direct fluid into at least the first flow passage. The scoop includes a serrated leading edge.

Abstract: A bullnose ramp is disclosed. In various embodiments, the bullnose ramp includes a forward portion, the forward portion characterized by a first profile; an aft portion, the aft portion characterized by a second profile; and a transition portion positioned proximate an intersection between the forward portion and the aft portion, the transition portion defining a change in slope between the first profile and the second profile.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a forward thrust duct and a thrust reverser system. The thrust reverser system includes a thrust reverser duct, a bullnose ramp and a plurality of protrusions. The bullnose ramp is adapted to provide a transition from the forward thrust duct to the thrust reverser duct when the thrust reverser system is in a deployed configuration. The protrusions are bonded or formed integral with the bullnose ramp. Each of the protrusions is adapted to interact with boundary layer fluid flowing along the bullnose ramp from the forward thrust duct into the thrust reverser duct when the thrust reverser system is in a deployed configuration.