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:
Nov. 03, 2020

Filed:

Nov. 28, 2017
Applicant:

General Electric Company, Schenectady, NY (US);

Inventors:

Alan Joseph Parvis, Loveland, OH (US);

Dane Michael Dale, Cincinnati, OH (US);

Ryan Christian Goff, Union, KY (US);

Assignee:

General Electric Company, Schenectady, NY (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F01D 9/04 (2006.01); F01D 5/06 (2006.01); F01D 9/06 (2006.01); F01D 5/18 (2006.01); F01D 25/24 (2006.01);
U.S. Cl.
CPC ...
F01D 9/041 (2013.01); F01D 5/06 (2013.01); F01D 5/188 (2013.01); F01D 9/065 (2013.01); F01D 25/24 (2013.01); F05D 2220/32 (2013.01); F05D 2230/60 (2013.01); F05D 2260/201 (2013.01); F05D 2300/6033 (2013.01);
Abstract

Shrouds and shroud segments for gas turbine engines are provided. In one exemplary aspect, a gas turbine engine includes a first rotor blade stage and a second rotor blade stage. The gas turbine engine also includes a shroud formed from a plurality of shroud segments that each have a body and a vane extending from the body. The vane is disposed within the flow path between the first rotor blade stage and the second rotor blade stage to form at least a portion of a nozzle stage. Further, the body of the shroud segment defines an outer wall of the flow path and spans from the first rotor blade stage to the second rotor blade stage. An impingement baffle segment couples the shroud segment with a casing of the gas turbine engine.


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