US 11,773,739 B2
Curved seal for adjacent gas turbine components
Neelesh Nandkumar Sarawate, Niskayuna, NY (US); Jonathan Dwight Berry, Simpsonville, SC (US); Russell Pierson DeForest, Simpsonville, SC (US); Kevin Weston McMahan, Greenville, SC (US); Victor John Morgan, Simpsonville, SC (US); Ibrahim Klara Sezer, Greenville, SC (US); and Deepak Trivedi, Halfmoon, NY (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Jun. 25, 2021, as Appl. No. 17/358,691.
Application 17/358,691 is a continuation of application No. 16/012,380, filed on Jun. 19, 2018, granted, now 11,047,248.
Prior Publication US 2021/0324754 A1, Oct. 21, 2021
This patent is subject to a terminal disclaimer.
Int. Cl. F01D 11/00 (2006.01); F16J 15/08 (2006.01); F23R 3/46 (2006.01)
CPC F01D 11/005 (2013.01) [F16J 15/0887 (2013.01); F23R 3/46 (2013.01); F05D 2240/35 (2013.01); F05D 2240/55 (2013.01); F23R 2900/00012 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A flexible seal for sealing between two adjacent gas turbine components, the flexible seal comprising:
a forward end, an aft end axially separated from the forward end, and an intermediate portion extending from the forward end to the aft end, the intermediate portion defining a continuous curve in the circumferential direction from the forward end to the aft end, such that the aft end is circumferentially offset from the forward end, wherein the two adjacent gas turbine components are integrated combustor nozzles.