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:
Dec. 11, 2018

Filed:

Aug. 03, 2015
Applicant:

United Technologies Corporation, Hartford, CT (US);

Inventor:

Flavien L. Thomas, Moodus, CT (US);

Assignee:

United Technologies Corporation, Farmington, CT (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F01D 11/00 (2006.01); F01D 5/02 (2006.01); F01D 5/14 (2006.01); F01D 9/04 (2006.01); F04D 29/54 (2006.01); F04D 29/32 (2006.01);
U.S. Cl.
CPC ...
F01D 11/008 (2013.01); F01D 5/02 (2013.01); F01D 5/143 (2013.01); F01D 5/147 (2013.01); F01D 9/041 (2013.01); F04D 29/324 (2013.01); F04D 29/544 (2013.01); F04D 29/545 (2013.01); F01D 11/005 (2013.01); F05D 2220/32 (2013.01); F05D 2230/60 (2013.01); F05D 2240/12 (2013.01); F05D 2240/24 (2013.01); F05D 2240/55 (2013.01); F05D 2240/80 (2013.01); F05D 2250/70 (2013.01); F05D 2260/961 (2013.01); Y02T 50/673 (2013.01);
Abstract

An airfoil array for a gas turbine engine comprises a plurality of airfoils spaced circumferentially apart from each other about an engine center axis. Each airfoil is associated with a platform. An endwall extends circumferentially about the engine center axis, and is defined by adjacent platforms. Each pair of adjacent platforms are separated from each other by a gap. An endwall contour shape extends from a first location on one side of the gap to a second location on an opposite of the gap. The endwall contour shape is the same for all adjacent platforms. A gas turbine engine and a method of forming an airfoil array for a gas turbine engine are also disclosed.


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