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:
Jul. 29, 2025

Filed:

Jan. 18, 2022
Applicant:

Mitsubishi Heavy Industries Engine & Turbocharger, Ltd., Sagamihara, JP;

Inventors:

Bipin Gupta, Tokyo, JP;

Takeru Chiba, Tokyo, JP;

Hiroshi Nakagawa, Sagamihara, JP;

Takashi Yoshimoto, Sagamihara, JP;

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F01D 17/16 (2006.01); F02B 37/24 (2006.01);
U.S. Cl.
CPC ...
F01D 17/16 (2013.01); F01D 17/165 (2013.01); F02B 37/24 (2013.01); F05D 2220/40 (2013.01); F05D 2240/128 (2013.01); F05D 2260/60 (2013.01);
Abstract

Provided are a variable geometry turbine and a turbocharger with the same. The variable geometry turbine is provided with a turbine impeller, a housing, a plurality of nozzle vanes, and a link mechanism. Inside the housing, a link compartment in which the link mechanism is accommodated is formed, the link compartment being separated from a nozzle flow path by a hub-side member having a hub side surface defining the nozzle flow path. The link mechanism and each of the plurality of nozzle vanes are coupled together via a nozzle shaft penetrating through the hub-side member. The hub-side member has at least one communication hole providing communication between the nozzle flow path and the link compartment. When each of the plurality of nozzle vanes is fully opened, the opening of the at least one communication hole on the nozzle flow path side is formed on the inner side radially of the turbine impeller than the leading edge of each of the plurality of nozzle vanes.


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