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EP-4321732-B1 - TURBINE NOZZLE WITH PLANAR SURFACE ADJACENT SIDE SLASH FACE

EP4321732B1EP 4321732 B1EP4321732 B1EP 4321732B1EP-4321732-B1

Inventors

  • Kittleson, Jacob John

Dates

Publication Date
20260506
Application Date
20230627

Claims (9)

  1. A nozzle (124, 124A, 124B) for a turbine system (110), the nozzle (124, 124A, 124B) comprising: an airfoil (140) including a tip (162) and a root (164); and an endwall (142, 144) connected to the airfoil (140) at one of the tip (162) and the root (164), the endwall (142, 144) including: a first side slash face (172, 182) at a first circumferential edge (190, 490) of the endwall (142, 144), a second side slash face (174, 184) at a second, opposing circumferential edge (192, 492) of the endwall (142, 144) from the first circumferential edge (190, 490), an inner surface (300, 400) extending between the first and second side slash faces (172, 174; 182, 184), the inner surface (300, 400) including a first planar surface portion (330, 430) adjacent to the first side slash face (172, 182) and a second planar surface portion (332, 432) adjacent to the second side slash face (174, 184) and an arcuate surface portion (334, 434) extending between the first and second planar surface portions (330, 332; 430, 432), and a seal pocket (212A, 212B; 412A, 412B) defined axially in each side slash face (172, 174; 182, 184), wherein the seal pockets (212A, 212B; 412A, 412B) are configured to receive a seal (210, 410) positioned therein for spanning a gap (224) between adjacent nozzles (124A, 124B), and wherein each seal pocket (212A, 212B; 412A, 412B) has a circumferential extent, characterized in that the first and second planar surface portions (330, 332; 430, 432) adjacent the first side slash face (172, 182) and the second side slash face (174, 184) each extend circumferentially from a respective circumferential edge (190, 192) of the respective side slash face (172, 174; 182, 184) to a circumferential location radially aligned with the circumferential extent of the respective seal pocket (212A, 212B; 412A, 412B) or to a greater extent than the circumferential extent of the respective seal pocket (212A, 212B; 412A, 412B).
  2. The nozzle (124, 124A, 124B) of claim 1, wherein each planar surface portion (330, 332; 430, 432) is angled in a non-parallel manner relative to the seal pocket (212A, 212B; 412A, 412B).
  3. The nozzle (124, 124A, 124B) of claim 1, wherein the endwall (142, 144) further comprises at least one passage (220, 420) extending through each of the first and second side slash faces (172, 174; 182, 184) between the respective seal pocket (212A, 212B; 412A, 412B) and the respective planar surface portion (330, 332; 430, 432).
  4. The nozzle (124, 124A, 124B) of claim 1, wherein the endwall (142, 144) includes an inner endwall (142) and the inner surface (300) is convexly arcuate.
  5. The nozzle (124, 124A, 124B) of claim 1, wherein the endwall (142, 144) includes an outer endwall (144) and the inner surface (400) is concavely arcuate.
  6. The nozzle (124, 124A, 124B) of claim 1, wherein the endwall (142, 144) extends greater than 7° of a circumferential circular extent of the hot gas path (120), and each planar surface portion (330, 332; 430, 432) extends no more than 1° of the circumferential circular extent of the hot gas path (120).
  7. The nozzle (124, 124A, 124B) of claim 1, wherein each planar surface portion (330, 332; 430, 432) extends circumferentially in a range of 5 to 50 millimeters from the circumferential edge (190, 192) of a respective side slash face (172, 174).
  8. The nozzle (124, 124A, 124B) of claim 1, wherein each planar surface portion (330, 332; 430, 432) extends axially an entire extent of the respective side slash face (172, 174; 182, 184).
  9. A nozzle assembly (128, 132, 136) for a turbine system (110), the nozzle assembly (128, 132, 136) comprising: a plurality of nozzles (124, 124A, 124B) disposed in an annular array and defining a hot gas path (120), each of the plurality of nozzles (124, 124A, 124B) defined according to anyone of the preceding claims.

Description

TECHNICAL FIELD The disclosure relates generally to gas turbine systems and, more particularly, to a turbine nozzle having an endwall having an inner surface with a planar surface portion adjacent a side slash face. BACKGROUND Gas turbine systems include nozzle assemblies, each including a plurality of nozzles disposed in an annular array and collectively defining a hot gas path. Adjacent nozzles in a nozzle assembly have gaps between adjacent side slash faces that are sealed with a seal to prevent ingestion of the working fluid. Ingestion of the working fluid, such as hot combustion gases, can lead to premature maintenance of the nozzles. EP 3 693 545 A1 discloses a nozzle assembly for a turbine system, comprising a plurality of nozzles disposed in an annular array and defining a hot gas path, each of the plurality of nozzles having the features of the preamble of independent claim 1. BRIEF DESCRIPTION All aspects, examples, and features mentioned below can be combined in any technically possible way. An aspect of the invention provides a nozzle for a turbine system, the nozzle comprising: an airfoil including a tip and a root; and an endwall connected to the airfoil at one of the tip and the root, the endwall including: a first side slash face at a first circumferential edge of the endwall; a second side slash face at a second, opposing circumferential edge of the endwall from the first circumferential edge; and an inner surface extending between the first and second side slash faces, the inner surface including a first planar surface portion adjacent to the first side slash face and a second planar surface portion adjacent to the second side slash face and an arcuate surface portion extending between the first and second planar surface portions. The endwall further comprises a seal pocket defined axially in each side slash face, wherein the seal pockets are configured to receive a seal positioned therein for spanning a gap between adjacent nozzles. Each seal pocket has a circumferential extent, wherein the first and second planar surface portions adjacent the first side slash face and the second side slash face each extend circumferentially from a respective circumferential edge of the respective side slash face to a circumferential location radially aligned with the circumferential extent of the respective seal pocket or to a greater extent than the circumferential extent of the respective seal pocket. Another aspect of the invention includes the preceding aspect, and each planar surface portion is angled in a non-parallel manner relative to the seal pocket. Another aspect of the invention includes any of the preceding aspects, and each planar surface portion extends axially an entire extent of the respective seal pocket. Another aspect of the invention includes any of the preceding aspects, and the endwall further comprises a first seal pocket defined axially in the first slash face and a second seal pocket defined axially in the second slash face, and at least one passage extending through each of the first and second side slash faces between the respective seal pocket and the respective planar surface. Another aspect of the invention includes any of the preceding aspects, and the endwall includes an inner endwall connected to the tip of the airfoil, and the inner surface is convexly arcuate. Another aspect of the invention includes any of the preceding aspects, and the endwall includes an outer endwall connected to the root of the airfoil, and the inner surface is concavely arcuate. Another aspect of the invention includes any of the preceding aspects, and the endwall extends greater than 7° of a circumferential circular extent of the hot gas path, and each planar surface portion extends no more than 2° of the circumferential circular extent of the hot gas path. Another aspect of the invention includes any of the preceding aspects, and each planar surface portion extends circumferentially in a range of 5 to 50 millimeters from the circumferential edge of a respective side slash face. An aspect of the invention includes a nozzle assembly for a turbine system, the nozzle assembly comprising: a plurality of nozzles disposed in an annular array and defining a hot gas path, each of the plurality of nozzles being defined according to anyone of the preceding aspects. Two or more aspects described in this disclosure, including those described in this summary section, may be combined to form implementations not specifically described herein. The details of one or more implementations are set forth in the accompanying drawings and the description below. Other features, objects and advantages will be apparent from the description and drawings, and from the claims. BRIEF DESCRIPTION OF THE DRAWINGS These and other features of this disclosure will be more readily understood from the following detailed description of the various aspects of the disclosure taken in conjunction with the accompanying drawings that dep