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. 19, 2017

Filed:

Apr. 03, 2013
Applicant:

Hamilton Sundstrand Corporation, Windsor Locks, CT (US);

Inventor:

Peter Bizzarro, Canton, CT (US);

Assignee:

HAMILTON SUNDSTRAND CORPORATION, Windor Locks, CT (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
B64D 13/08 (2006.01); F02C 6/08 (2006.01); F02C 7/143 (2006.01); F28F 9/02 (2006.01); F28F 19/00 (2006.01); B64D 13/06 (2006.01); F28D 21/00 (2006.01);
U.S. Cl.
CPC ...
B64D 13/08 (2013.01); F02C 6/08 (2013.01); F02C 7/143 (2013.01); F28D 21/0001 (2013.01); F28F 9/02 (2013.01); F28F 19/00 (2013.01); B64D 2013/0651 (2013.01); F28D 2021/0021 (2013.01); F28F 2250/06 (2013.01); Y02T 50/675 (2013.01);
Abstract

A precooler for an aircraft engine system includes a precooler core and a precooler inlet to direct a compressor bleed flow into the precooler core to cool the compressor bleed flow. The precooler further includes a precooler outlet to direct the compressor bleed flow from the precooler to a selected component of the aircraft engine system and a precooler bleed port through which a portion of the compressor bleed flow is diverted to a secondary component of the aircraft engine system. The precooler bleed port is oriented such that flow entering the precooler bleed port must substantially reverse direction from a direction of the compressor bleed flow through the precooler.


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