公开(公告)号：WO1996040554A1

公开(公告)日：1996-12-19

申请号：PCT/IB1996000927

申请日：1996-06-03

Applicant: SUNDSTRAND CORPORATION

Inventor： SUNDSTRAND CORPORATION ,  KROLL, William, B. ,  CURRAN, Patrick, D.

IPC: B64C23/06

CPC classification number: B64C23/065 ,  Y02T50/164

Abstract: An aircraft (10) including a stowable, wingtip mounted, vortex turbine (30) for dissipating or extracting energy from a lift induced vortex (28) emanating from the aircraft (10) is provided. The vortex turbine (30) includes a first and a second array (38, 40) of blades (32a, b) (34a, b) extending respectively from a first and a second hub section (32, 34). Hub sections (32, 34) may be independently pivoted about a common axis of rotation (36) to a stowed position for landing, take-off, or ground operation, whereat none of the blades (32a, b) (34a, b) extend below a minimum ground clearance of the aircraft, or beyond a maximum horizontal extension of the wing (16). In flight, the hub sections (32, 34) may be deployed and the pitch of the blades adjusted to maximize dissipation of the lift induced vortex (28), thereby minimizing drag and providing improved safety for other aircraft flying through the wake of the aircraft (10) producing the vortex (28). The hub sections (32, 34) may also be locked together to form a turbine wheel (46) having a circumferentially symmetrical array of blades. The turbine wheel (46) is rotatable about the axis of rotation (36) for extracting usable energy from the lift induced vortex (28) and/or free stream air passing through the turbine wheel (46).

Abstract translation: 提供一种包括用于从飞行器（10）发出的提升引起的涡流（28）耗散或提取能量的可收起的翼尖安装的涡轮机（30）的飞机（10）。 涡轮涡轮（30）包括分别从第一和第二毂部（32,34）延伸的叶片（32a，b）（34a，b）的第一和第二阵列（38,40）。 枢轴部分（32,34）可以围绕共同的旋转轴线（36）独立地枢转到用于着陆，起飞或地面操作的收起位置，在那里不会有叶片（32a，b）（34a，b） 延伸到飞机的最小离地间隙之下，或超出机翼（16）的最大水平延伸。 在飞行中，枢转部分（32,34）可以被展开，并且叶片的桨距被调节以最大化提升感应涡流（28）的耗散，从而最小化阻力并为飞行器通过飞行器尾流提供改进的安全性 （10）产生涡流（28）。 毂部分（32,34）也可以被锁定在一起以形成具有周向对称的叶片阵列的涡轮机叶轮（46）。 涡轮机叶轮（46）可围绕旋转轴线（36）旋转，用于从提升引起的涡流（28）和/或通过涡轮机叶片（46）的自由流空气提取可用的能量。