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EP-4741639-A1 - GAS TURBINE ENGINE STATOR VANE STAGE

EP4741639A1EP 4741639 A1EP4741639 A1EP 4741639A1EP-4741639-A1

Abstract

A gas turbine engine (20) includes a compressor section (28), a combustion section (30), and a turbine section (32). The turbine section has a rotor stage (40) disposed adjacent an annular stator vane stage (42). The annular stator vane stage includes annular inner (50) and outer radial shrouds (52), stator vanes (48), and a retaining ring (72). The stator vanes are circumferentially spaced apart from one another, extending between the shrouds. The inner radial shroud is mechanically engaged with a first engine support structure (54) at a first position axially forward of the plurality of stator vanes, and the outer radial shroud is mechanically engaged with a second engine support (64) structure at a second position axially forward of the plurality of stator vanes. The annular stator vane stage includes a flange (66) extending outward from the outer radial shroud that is contiguous with the retaining ring.

Inventors

  • SANZARI, LORENZO
  • DI PAOLA, FRANCO

Assignees

  • Pratt & Whitney Canada Corp.

Dates

Publication Date
20260513
Application Date
20251110

Claims (15)

  1. A gas turbine engine (20), comprising; a compressor section (28); a combustion section (30); and a turbine section (32) disposed aft of the combustion section (30), the turbine section (32) having a rotor stage (40) disposed adjacent an annular stator vane stage (42); wherein the annular stator vane stage (42) includes an annular inner radial shroud (50), an annular outer radial shroud (52), a plurality of stator vanes (48), and a retaining ring (72), wherein the plurality of stator vanes (48) are circumferentially spaced apart from one another and extending between the inner radial shroud (50) and the outer radial shroud (52), wherein: the inner radial shroud (50) is mechanically engaged with a first engine support structure (54) at a first position axially forward of the plurality of stator vanes (48), and the outer radial shroud (52) is mechanically engaged with a second engine support structure (64) at a second position axially forward of the plurality of stator vanes (48); and the annular stator vane stage (42) further includes a flange (66) extending radially outward from the outer radial shroud (52), and the flange (66) is contiguous with the retaining ring (72) in a manner that permits radial movement of the flange (66) relative to the retaining ring (72).
  2. The gas turbine engine (20) of claim 1, wherein the flange (66) includes an aft seal surface (66B) that extends radially.
  3. The gas turbine engine (20) of claim 2, wherein the retaining ring (72) includes a forward seal surface (76), and the aft seal surface (66B) of the flange (66) is contiguous with the forward seal surface (76), and forms a seal therebetween.
  4. The gas turbine engine (20) of claim 3, wherein the forward seal surface (76) and the aft seal surface (66B) each have a surface configuration that facilitates a sliding contact therebetween, optionally, wherein the forward seal surface (76) and the aft seal surface (66B) are parallel to one another.
  5. The gas turbine engine (20) of claim 3 or 4, wherein the retaining ring (72) includes an inner radial segment (72A), an outer radial segment (72B), and a connecting segment (72C) extending between the inner radial segment (72A) and the outer radial segment (72B), and the inner radial segment (72A) includes the forward seal surface (76), optionally, wherein the connecting segment (72C) extends linearly between the inner radial segment (72A) and the outer radial segment (72B).
  6. The gas turbine engine (20) of claim 5, wherein the turbine section (32) is centered on an engine axial centerline (22) and wherein the connecting segment (72C) is disposed at an acute angle relative to the engine axial centerline (22).
  7. The gas turbine engine (20) of any preceding claim, wherein the retaining ring (72) is a casting.
  8. The gas turbine engine (20) of any preceding claim, wherein the annular stator vane stage (42) includes a plurality of first lugs (60) extending radially outward from the outer radial shroud (52) at the second position, the first lugs (60) are circumferentially spaced apart from one another, and the first lugs (60) are mechanically engaged with the second engine support structure (64).
  9. The gas turbine engine (20) of claim 8, wherein the first lugs (60) are mechanically engaged with first mating features (62) of the second engine support structure (64), and the first lugs (60) and the first mating features (62) are configured to allow radial growth of the stator vane stage (42).
  10. The gas turbine engine (20) of any preceding claim, wherein the outer radial shroud (52) includes a first aft portion that extends away from the plurality of stator vanes (48) and the first aft portion of the outer radial shroud (52) is cantilevered; and/or wherein the inner radial shroud (50) includes a second aft portion that extends away from the plurality of stator vanes (48) and the second aft portion of the inner radial shroud (50) is cantilevered.
  11. The gas turbine engine (20) of any of claims 5 to 10, wherein the retaining ring (72) further includes a plurality of second lugs (82) extending radially outward from the outer radial segment (72B), wherein the second lugs (82) are circumferentially spaced apart from one another, and the second lugs (82) are mechanically engaged with the second engine support structure (64).
  12. The gas turbine engine (20) of any preceding claim, wherein the annular stator vane stage (42) is a unitary annular construct.
  13. The gas turbine engine (20) of any preceding claim, wherein the annular inner radial shroud (50) is configured as a first continuous ring, and the annular outer radial shroud (52) is configured as a second continuous ring.
  14. The gas turbine engine (20) of any preceding claim, wherein the inner radial shroud (50) includes an attachment flange (56) disposed at the first position.
  15. The gas turbine engine (20) of claim 14, wherein the annular stator vane stage (42) is configured to be mounted at the attachment flange (56) at the first position, and at the plurality of lugs (60) disposed at the second position axially forward of the plurality of stator vanes (48), and cantilevered aft of the first position and the second position.

Description

BACKGROUND OF THE INVENTION 1. Technical Field The present disclosure relates gas turbine engines in general and to gas turbine engine stator vane stages in particular. 2. Background Information Turbine vanes or stators are stationary airfoils positioned within the engine's turbine section, situated between stages of turbine blades. The stator vanes typically precede the rotor blades and are configured to direct the flow of combustion-generated hot gases. In some instances, a stator vane stage may include a plurality of stator vanes that extend between an inner annular member referred to as an inner shroud and an outer annular member referred to as an outer shroud. Typically, the outer shroud features both axial and radial retention mechanisms that secure it to a surrounding structure. Stator vanes, especially those closest to the combustion section of the engine, are subjected to intense heat from the core gas flow passing through the stator vane stage. These stator vanes are often subject to significant thermal stresses as they are constrained by the relatively cooler inner and outer shrouds. The high-temperature stator vanes are restricted in their ability to expand or grow due to the surrounding cooler inner and outer shrouds. What is needed is a turbine stator vane stage with an improved ability to accommodate thermal growth and thereby mitigate thermal stresses. SUMMARY According to one aspect of the present invention, there is provided a gas turbine engine that includes a compressor section, a combustion section, and a turbine section. The turbine section is disposed aft of the combustion section and has a rotor stage disposed adjacent an annular stator vane stage. The annular stator vane stage includes an annular inner radial shroud, an annular outer radial shroud, a plurality of stator vanes, and a retaining ring. The plurality of stator vanes are circumferentially spaced apart from one another, extending between the inner and outer radial shrouds. The inner radial shroud is mechanically engaged with a first engine support structure at a first position axially forward of the plurality of stator vanes, and the outer radial shroud is mechanically engaged with a second engine support structure at a second position axially forward of the plurality of stator vanes. The annular stator vane stage further includes a flange extending radially outward from the outer radial shroud, and the flange is contiguous with the retaining ring in a manner that permits radial movement of the flange relative to the retaining ring. Optionally, and in accordance with the above, the flange may include an aft seal surface that extends radially. Optionally, and in accordance with any of the above, the retaining ring may include a forward seal surface, and the aft seal surface of the flange is contiguous with the forward seal surface, and forms a seal therebetween. Optionally, and in accordance with any of the above, the forward seal surface and the aft seal surface each may have a surface configuration that facilitates a sliding contact therebetween. Optionally, and in accordance with any of the above, the forward seal surface and the aft seal surface may be parallel one another. Optionally, and in accordance with any of the above, the retaining ring may include an inner radial segment, an outer radial segment, and a connecting segment extending between the inner radial segment and the outer radial segment, and the inner radial segment may include the forward seal surface. Optionally, and in accordance with any of the above, the connecting segment may extend linearly between the inner radial segment and the outer radial segment. Optionally, and in accordance with any of the above, the turbine section may be centered on an engine axial centerline, and the connecting segment may be disposed at an acute angle relative to the engine axial centerline. Optionally, and in accordance with any of the above, the retaining ring may be a casting. Optionally, and in accordance with any of the above, the annular stator vane stage may include a plurality of first lugs extending radially outward from the outer radial shroud at the second position axially forward of the plurality of stator vanes. The first lugs may be circumferentially spaced apart from one another, and may be mechanically engaged with the second engine support structure. Optionally, and in accordance with any of the above, the first lugs may be mechanically engaged with first mating features of the second engine support structure, and the first lugs and the first mating features may be configured to allow radial growth of the stator vane stage. Optionally, and in accordance with any of the above, the outer radial shroud may include a first aft portion that extends away from the plurality of stator vanes and the first aft portion of the outer radial shroud may be cantilevered. Optionally, and in accordance with any of the above, the inner radial shroud may include a second af