公开(公告)号：US3558084A

公开(公告)日：1971-01-26

申请号：US3558084D

申请日：1968-06-05

Applicant: ROBERT B COTTON

Inventor： COTTON ROBERT B

IPC: B64F1/06 ,  F01D1/02 ,  F01D1/08

CPC classification number: F01D1/026 ,  B64F1/06 ,  F01D1/08

Abstract: A gas flow turbine for use in conjunction with a jet engine includes a series of radially disposed blades mounted about a periphery of a circular support wheel. The edges of the blades are substantially free of obstruction to minimize impediment to the flow of gas directed against them. This causes the turbine wheel to derive a substantial thrust from the gas flowing against it without materially impeding such flow. A convenient form of such turbine includes slightly curved blades centrally mounted in cantilever manner to a rotatable disc with their ends extending therefrom. Despite the minimal reaction imparted to the wheel by the gases, substantial energy is derived from the gases discharged from a jet engine without materially reducing the engine''s efficiency. The turbine''s energy may be advantageously utilized for a multitude of purposes including general augmentation of jet engine thrust, particularly for improving efficiency of launching thrust and auxiliary uses in conjunction with jet engine exhaust including electric power generation.