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US 11,994,039 B2Granted
Shroud for a gas turbine engine
AssigneeGeneral Electric Company
InventorsKirk Douglas Gallier, Charles William Craig, III
Life of this patent
Estimating the term…
Abstract
A gas turbine engine having a rotor blade stage with a plurality of circumferentially spaced rotors, a nozzle stage adjacent the rotor blade stage and including an outer nozzle end, at least one stop, and a shroud. The shroud having a forward end positioned radially outward from the circumferentially spaced rotor blades, and an aft end axially aft of the forward end. The at least one stop confronting at least a portion of the outer nozzle end.
Claims17
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.
3 more elements
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 casing circumferentially surrounding the rotor blade stage and the nozzle stage;
- 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 coupled to the casing, the at least one stop defining at least one of an axial position or a circumferential position for the nozzle relative to the shroud.
4 more elements
Dependencies are inferred from the claim text.