The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Sep. 12, 2017

Filed:

May. 10, 2012
Applicant:

Slobodan Tepic, Zurich, CH;

Inventor:

Slobodan Tepic, Zurich, CH;

Assignee:

AELLA SA, Zurich, CH;

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F01D 1/34 (2006.01); F01D 1/36 (2006.01); F02C 3/05 (2006.01); F04D 5/00 (2006.01); F04D 17/16 (2006.01); F02C 3/36 (2006.01);
U.S. Cl.
CPC ...
F01D 1/34 (2013.01); F01D 1/36 (2013.01); F02C 3/05 (2013.01); F02C 3/365 (2013.01); F04D 5/001 (2013.01); F04D 17/161 (2013.01); Y02T 50/672 (2013.01);
Abstract

The invention is directed to a turbo-engine, particularly internal combustion engine, comprising a housing and therein a bladeless turbine section () of the stacked disc- or Tesla-type construction, wherein the turbine section () has a plurality of closely spaced discs () arranged for common rotation about a rotation axis in the housing, said turbine section () is adapted for passing with tangential flow components a working fluid stream from a radially inner region to a radially outer region of said turbine section () while adopting energy from said working fluid stream for rotating the discs (). Preferably, the turbo-engine further comprises a compressor section () of the stacked disc- or Tesla-type construction having a plurality of closely spaced discs () arranged for common rotation about said rotation axis and a combustion zone (), wherein said compressor section () being arranged coaxially with—and radially inwardly of the turbine section () with the combustion zone () provided radially between the compressor section and the turbine section.


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