Boundary layer ingestion integration into aft fuselage
AssigneeThe Boeing Company
InventorsAngelina M. Conti, Patrick G. Harvey, Krunal B. Mistry, Kimberly A. Rink, Ted K. Rothaupt
Life of this patent
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Abstract
Systems and methods for integrating Boundary Layer Ingestion (BLI) apparatus into an aircraft (1). The longerons (34) in the aft fuselage (18) may be extended to support an aft propulsor (20). The aft propulsor may be a turbofan or turboelectric propulsion system (46). An upper longeron (34a) may support a tail section (14) of an aircraft. The aft fuselage skin (22) is contoured to permit boundary layer airflow to enter an intake fan (24) of the aft propulsor.
Claims20
An apparatus comprising:
- an extended longeron (34) extending aft from a fuselage (10);
- a second extended longeron (34) extending aft from the fuselage;
- a third extended longeron (34) extending aft from the fuselage;
- and
- wherein the three extended longerons are spaced with substantially 120 degrees of angular separation about a central axis, wherein the three extended longerons support an aft propulsor with structural members (38) extending radially from the three extended longerons to a bearing (40) on a central shaft (42) coupled to the aft propulsor;
- the aft propulsor (20) having an inner diameter that is smaller than an outer diameter of the fuselage and further comprising an intake fan (24);
- and
- a connection point (32) between the extended longeron and an aft fuselage skin (22) and wherein the aft fuselage skin is contoured to enable the flow of boundary layer air into the intake fan of the aft propulsor.
A method for integrating Boundary Layer Ingestion (BLI) apparatus into an aircraft, the method comprising:
- coupling an extended longeron to an aft fuselage (601);
- coupling a second extended longeron to the aft fuselage (601);
- coupling a third extended longeron to the aft fuselage (601);
- and
- wherein the three extended longerons are spaced with substantially 120 degrees of angular separation about a central axis;
- and
- wherein the three extended longerons support an aft propulsor by coupling structural members extending radially from the three extended longerons to a bearing on a central shaft coupled to the aft propulsor (612) and wherein the aft propulsor has an inner diameter that is smaller than an outer diameter of the aft fuselage;
- and
- connecting aft fuselage skin to the three extended (603) wherein the aft fuselage skin is contoured to enable the flow of boundary layer air into an intake fan of the aft propulsor.
An aircraft (1) comprising:
- a fuselage (10);
- an extended longeron (34) extending aft from the fuselage;
- a second extended longeron (34) extending aft from the fuselage;
- a third extended longeron (34) extending aft from the fuselage;
- and
- wherein the three extended longerons are spaced with substantially 120 degrees of angular separation about a central axis;
- and
- wherein the three extended longerons support an aft propulsor with structural members (38) extending radially from the three extended longerons to a bearing (40) on a central shaft (42) coupled to the aft propulsor;
- the aft propulsor (20) having an inner diameter that is smaller than an outer diameter of the fuselage and further comprising an intake fan (24);
- and
- a connection point (32) between the extended longeron and an aft fuselage skin (22) and wherein the aft fuselage skin is contoured to enable the flow of boundary layer air into the intake fan of the aft propulsor.
Dependencies are inferred from the claim text.