US 11,994,039 B2
Shroud for a gas turbine engine
Kirk Douglas Gallier, Cincinnati, OH (US); and Charles William Craig, III, West Chester, OH (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed on Apr. 1, 2022, as Appl. No. 17/711,405.
Application 17/711,405 is a continuation of application No. 16/593,094, filed on Oct. 4, 2019, granted, now 11,306,617.
Application 16/593,094 is a continuation of application No. 15/212,337, filed on Jul. 18, 2016, granted, now 10,450,897, issued on Oct. 22, 2019.
Prior Publication US 2022/0356815 A1, Nov. 10, 2022
Int. Cl. F01D 9/04 (2006.01); F01D 11/00 (2006.01); F01D 25/24 (2006.01)
CPC F01D 25/246 (2013.01) [F01D 9/042 (2013.01); F01D 11/005 (2013.01); F05D 2300/6033 (2013.01); Y02T 50/60 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A gas turbine engine defining a longitudinal axis and comprising:
a rotor blade stage comprising multiple rotor blades spaced circumferentially with respect to the longitudinal axis;
a nozzle stage adjacent the rotor blade stage and comprising a nozzle with an outer nozzle end;
a shroud extending between a forward end and an aft end with respect to the longitudinal axis, with the forward end spaced radially outward from the multiple rotor blades, and with the outer nozzle end extending radially outward beyond an outer surface of the shroud;
a shroud seal positioned between the nozzle stage and the shroud; and
at least one stop spaced from the shroud, the at least one stop defining at least one of an axial position or a circumferential position for the nozzle relative to the shroud.