Abstract

A disk engine and system configured to provide high power at a reduced axial length is disclosed herein. The disk engine includes a radial compressor, a compressor discharge manifold positioned circumferentially about compressor, a combustion chamber positioned within the discharge manifold and a radial turbine positioned radially inward of the combustion chamber.

Document Type

Patent

Status

Issued

Issue Date

6-25-2024

Patent Number

US 12018613 [ 12,018,613 ] ; US 12018613B1

CPC Classification

F 02 C 7/12

Application number

17/846633

Assignees

United States of America as represented by the Secretary of the Air Force, Wright-Patterson AFB

Filing Date

6-22-2022

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