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

8-16-2022

Patent Number

US 11415046 B1 [ 11,415,046 ]

CPC Classification

F02C3/08; F02C3/05

Application number

16/8667,00

Assignees

Government of the United States, as represented by the Secretary of the Air Force, Wright-Patterson AFB, OH (US)

Filing Date

5-5-2020

Share

COinS