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. 09, 2019

Filed:

Apr. 18, 2016
Applicant:

General Electric Company, Schenectady, NY (US);

Inventors:

Harjit Hura, Cincinnati, OH (US);

Paul Hadley Vitt, Liberty Township, OH (US);

Brian David Keith, Cincinnati, OH (US);

Jonathan Ong, Munich, DE;

Assignee:

General Electric Company, Schenectady, NY (US);

Attorneys:
Primary Examiner:
Int. Cl.
CPC ...
F01D 9/02 (2006.01); F02C 3/04 (2006.01); F02C 7/20 (2006.01); F01D 5/14 (2006.01); F01D 9/06 (2006.01); F04D 29/54 (2006.01); F04D 29/58 (2006.01);
U.S. Cl.
CPC ...
F01D 9/023 (2013.01); F01D 5/143 (2013.01); F01D 5/145 (2013.01); F01D 9/02 (2013.01); F01D 9/065 (2013.01); F02C 3/04 (2013.01); F02C 7/20 (2013.01); F04D 29/545 (2013.01); F04D 29/584 (2013.01); F05D 2220/32 (2013.01); Y02T 50/671 (2013.01); Y02T 50/673 (2013.01);
Abstract

A transition duct includes fairings with transition duct flow passage and hollow fairing airfoils extending between outer and inner walls of fairings and means for smoothing pressure gradients along inner wall. One means is a contracting duct flow area of flow passage from leading edge of fairing airfoil to about 30% of fairing chord. Leading edges of fairing airfoil intersect outer walls aft of regions of high curvature of outer walls. Leading edges may curve axially aftwardly and radially into fairing airfoils and transition duct flow passage between radially outer and inner walls from radially outer and inner intersection points. Transition duct downstream second area/upstream first area may be greater than about 1.35. Turbine center frame may include outer ring coupled to central hub with struts extending through hollow airfoils.


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