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. 10, 2019

Filed:

Jul. 09, 2014
Applicant:

Siemens Aktiengesellschaft, München, DE;

Inventor:

Humberto A. Zuniga, Casselberry, FL (US);

Assignee:
Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F01D 5/18 (2006.01); F01D 25/12 (2006.01); F28F 13/12 (2006.01);
U.S. Cl.
CPC ...
F01D 5/187 (2013.01); F01D 5/186 (2013.01); F01D 25/12 (2013.01); F28F 13/12 (2013.01); F05D 2220/32 (2013.01); F05D 2240/303 (2013.01); F05D 2250/32 (2013.01); F05D 2250/711 (2013.01); F05D 2260/201 (2013.01); F05D 2260/22141 (2013.01); F28F 2210/02 (2013.01);
Abstract

An internal cooling system () including an impingement jet strike channel system () for increasing the effectiveness of impingement jets () is disclosed. The impingement jet strike channel system () may include an impingement jet strike cavity () offset from one or more impingement orifices (). A plurality of impingement jet strike channels () may extend radially outward from the impingement jet strike cavity () forming a starburst pattern of impingement jet strike channels () and may be formed by a plurality of ribs () that each separate adjacent impingement jet strike channels (). The ribs () forming the impingement jet strike channels () may be split one or more times into multiple channels to increase the number of stagnation points () to increase the cooling capacity. The impingement jet strike channel system () may be used within components, such as, but not limited to, gas turbine engines (), including vane inserts, airfoil leading edge cooling systems, platforms, advanced transitions, acoustic resonators, ring segments and the like.


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