公开(公告)号：US20190186418A1

公开(公告)日：2019-06-20

申请号：US16326717

申请日：2017-08-28

Applicant: Bingham Robert A.

Inventor： Orlorunfemi Jacob Azundah

IPC: F02K5/00 ,  B64D27/24 ,  B64D27/16

CPC classification number: F02K5/00 ,  B64C2201/04 ,  B64D27/16 ,  B64D27/24 ,  B64D2027/026 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/4031

Abstract: A multi-hybrid aircraft engine that includes a primary compressor 1, a multiplier 199 comprising a drive block, a driven block, driven block pistons 54, and primary shafts 78 and 41; an output shaft 105, and a speed regulator 167. The multi-hybrid aircraft engine is configured such that the primary compressor 1 is fluidly connected to the drive block 46 which is mechanically connected to the driven block 57. The primary compressor 1 pumps compressible fluid to the drive block 46 through the speed regulator 167 to drive the drive block 46, which in turn, drives the primary shafts 78 and 41. The primary shafts 78 and 41 drive the driven block 57, which pumps fluid via the driven block pistons 54, to the drive block 46 through the speed regulator 167 to increase the flow rate of compressible fluid within the multi-hybrid aircraft engine. Furthermore, the driven block 57 provides a shaft 68 that is connected to sets of planetary gears 62 connected to an output shaft 105 that drives a propeller 186.