Shroud for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-2022356815-A1
Application number	US-202217711405-A
Country	US
Kind code	A1
Filing date	Apr 1, 2022
Priority date	Jul 18, 2016
Publication date	Nov 10, 2022
Grant date	—

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.

First claim

1 - 20 . (canceled)

21 . A gas turbine engine defining a longitudinal axis, the gas turbine engine comprising:
a rotor blade stage, the rotor blade stage including a plurality of circumferentially spaced rotor blades with respect to the longitudinal axis, each rotor blade having a tip; a nozzle stage adjacent the rotor blade stage, and including an outer nozzle end; at least one stop confronting at least a portion of the outer nozzle end and configured to axially or circumferentially position the nozzle stage; a shroud having:
a forward end positioned radially outward from each tip of the circumferentially spaced rotor blades; and
an aft end positioned axially aft of the forward end with respect to the longitudinal axis,
wherein the outer nozzle end extends radially outward beyond an outer surface of the shroud.

22 . The gas turbine engine of claim 21 , wherein the outer nozzle end includes a flange extending across at least a portion of the outer nozzle end.

23 . The gas turbine engine of claim 22 , wherein the at least one stop directly contacts at least a portion of the flange.

24 . The gas turbine engine of claim 22 , wherein the flange includes a flared cross section when viewed along a circumferential plane intersecting the flange.

25 . The gas turbine engine of claim 22 , wherein the flange includes a U-shaped cross section when viewed along a radial plane intersecting the flange.

26 . The gas turbine engine of claim 21 , wherein the at least one stop includes a first stop confronting a first portion of the outer nozzle end and a second stop confronting a second portion, different from the first portion, of the outer nozzle end.

27 . The gas turbine engine of claim 26 , wherein the first stop is configured to axially position the nozzle stage and the second stop is configured to circumferentially position the nozzle stage.

28 . The gas turbine engine of claim 26 , wherein the first stop extends from the second stop.

29 . The gas turbine engine of claim 21 , further comprising an outer casing encasing at least a portion of the shroud.

30 . The gas turbine engine of claim 29 , wherein the at least one stop extends radially inwardly, with respect to the longitudinal axis, from the outer casing.

31 . The gas turbine engine of claim 21 , further comprising a shroud seal provided between the nozzle stage and the shroud.

32 . The gas turbine engine of claim 31 , wherein the shroud seal is provided between the outer nozzle end and the shroud.

33 . The gas turbine engine of claim 31 , further comprising a pocket formed within a portion of one of either the nozzle or the shroud, wherein the seal is at least partially positioned within the pocket.

34 . A shroud for an airfoil assembly having an airfoil with an outer end, the airfoil assembly configured to rotate about a rotational axis, the shroud comprising:
a forward end; and an aft end positioned axially aft of the forward end with respect to the rotational axis, the outer end of the airfoil assembly extending through the aft end such that the outer end extends radially outward beyond a radially outer surface of the shroud; wherein at least one stop confronts at least a portion of the outer end and is configured to axially or circumferentially position the airfoil assembly with respect to the rotational axis.

35 . The shroud of claim 34 , wherein the outer end includes a flange extending across at least a portion of the outer end.

36 . The shroud of claim 35 , wherein the at least one stop directly contacts at least a portion of the flange.

37 . The shroud of claim 34 , wherein the at least one stop includes a first stop confronting a first portion of the outer end and a second stop confronting a second portion, different from the first portion, of the outer end.

38 . The shroud of claim 37 , wherein the first stop is configured to axially position the airfoil assembly and the second stop is configured to circumferentially position the airfoil assembly with respect to the rotational axis.

39 . The shroud of claim 37 , wherein the first stop extends from the second stop.

40 . The shroud of claim 34 , wherein an outer casing encases at least a portion of the shroud and wherein the at least one stop extends radially inwardly from the outer casing, with respect to the rotational axis.

Assignees

• Gen Electric

Inventors

• Gallier Kirk Douglas
• Craig Iii Charles William

Classifications

• F01D9/042

  fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246) · CPC title

• F01D11/005

  Sealing means between non relatively rotating elements · CPC title

• F01D25/246 Primary

  Fastening of diaphragms or stator-rings · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title