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. 25, 2018

Filed:

Oct. 20, 2015
Applicant:

General Electric Company, Schenectady, NY (US);

Inventors:

Benjamin Scott Huizenga, Cincinnati, OH (US);

Kevin Robert Feldmann, Mason, OH (US);

Robert Alan Frederick, West Chester, OH (US);

Robert Charles Groves, II, West Chester, OH (US);

Kirk Douglas Gallier, Liberty Township, OH (US);

Timothy Francis Andrews, Sharonville, OH (US);

Darrell Senile, Oxford, OH (US);

Assignee:

General Electric Company, Schenectady, NY (US);

Attorneys:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F01D 11/00 (2006.01); F01D 5/28 (2006.01); F16J 15/08 (2006.01); F16J 15/06 (2006.01); F01D 25/12 (2006.01); F01D 9/04 (2006.01); F01D 9/02 (2006.01);
U.S. Cl.
CPC ...
F01D 11/005 (2013.01); F01D 5/284 (2013.01); F01D 9/041 (2013.01); F01D 9/047 (2013.01); F01D 25/12 (2013.01); F16J 15/061 (2013.01); F16J 15/0887 (2013.01); F01D 9/023 (2013.01); F05D 2220/32 (2013.01); F05D 2240/57 (2013.01); F05D 2250/71 (2013.01); F05D 2300/6033 (2013.01);
Abstract

A gas turbine engine arcuate leaf seal assembly includes arcuate leaf seal extending radially and circumferentially between adjacent first and second turbine components. Upper and lower leaf seal portions of leaf seal are in radially spaced apart arcuate upper and lower grooves in the first and second turbine components respectively. The seal includes an arcuate body and a circumferential retention tab extending radially away from body and disposed in a notch in a wall of grooves. Seal may have a thickness between 3 mils and 35 mils and/or torsional stiffness between 0.015 and 0.15 lb/in. Turbine components may be radially adjacent turbine nozzle upper and lower components. The upper or lower component may be made of a ceramic matrix composite material. Annular cooling air plenum including flow cavities in inner support ring segments may be in lower component and in flow communication with hollow fairing airfoils.


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