Hybrid nozzle segment assemblies for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-2016290147-A1
Application number	US-201514672380-A
Country	US
Kind code	A1
Filing date	Mar 30, 2015
Priority date	Mar 30, 2015
Publication date	Oct 6, 2016
Grant date	—

Abstract

A nozzle segment assembly for a gas turbine engine may generally include inner and outer ring support segments and a nozzle fairing positioned between the inner and outer ring support segments. The nozzle fairing may be formed from a ceramic matrix composite (CMC) material and may include both an outer endwall and an inner endwall. In addition, the nozzle fairing may include a strut vane extending between the inner and outer endwalls. The nozzle segment assembly may also include a metallic strut extending through the strut vane between the outer and inner ring supports and at least one secondary vane configured to be received through at least one of the outer endwall or the inner endwall of the nozzle fairing such that the at least one secondary vane extends between the inner and outer endwalls at a location adjacent to the strut vane.

First claim

What is claimed is:

1 . A nozzle segment assembly for a gas turbine engine, the nozzle segment assembly comprising:
an outer ring support segment and an inner ring support segment; a nozzle fairing positioned between the inner and outer ring support segments, the nozzle fairing being formed from a ceramic matrix composite (CMC) material, the nozzle fairing including an outer endwall configured to be positioned adjacent to the outer ring support segment and an inner endwall configured to be positioned adjacent to the inner ring support segment, the nozzle fairing further comprising a strut vane extending between the inner and outer endwalls; a metallic strut extending through the strut vane between the outer and inner ring supports; and at least one secondary vane configured to be received through at least one of the outer endwall or the inner endwall of the nozzle fairing such that the at least one secondary vane extends between the inner and outer endwalls at a location adjacent to the strut vane.

2 . The nozzle segment assembly of claim 1 , wherein the outer endwall defines an outer slot and the inner endwall defines an inner slot, wherein separate portions of the at least one secondary vane are configured to be received within the outer and inner slots.

3 . The nozzle segment assembly of claim 2 , wherein the at least one secondary vane extends radially between an outer vane end and an inner vane end, the at least one secondary vane being configured to extend through the inner and outer slots such that the outer vane end extends radially outwardly from the outer endwall and the inner vane end extend radially inwardly from the inner endwall.

4 . The nozzle segment assembly of claim 3 , wherein the outer vane end is configured to be received within a vane recess defined in the outer ring support.

5 . The nozzle segment assembly of claim 4 , wherein the at least one secondary vane comprises a mounting tab extending from the outer vane end, the mounting tab defining a through-hole configured to receive a mounting pin for coupling the at least one secondary vane to the outer ring support.

6 . The nozzle segment assembly of claim 3 , wherein the inner vane end is configured to be received within a vane recess defined in the inner ring support.

7 . The nozzle segment assembly of claim 6 , wherein the inner vane end is configured to be coupled within the recess.

8 . The nozzle segment assembly of claim 1 , wherein the inner and outer endwalls and the strut vane are formed integrally as a single unitary component.

9 . The nozzle segment assembly of claim 1 , wherein the metallic strut extends radially inwardly from the outer ring support through the strut vane.

10 . The nozzle segment assembly of claim 9 , wherein the outer ring support segment comprises an outer band segment, the metallic strut and the outer band segment being formed integrally as a single unitary component.

11 . The nozzle segment assembly of claim 9 , wherein the metallic strut extends radially inwardly from the outer ring support to a tip end, the tip end being configured to be received within a strut recess defined in the inner ring support segment.

12 . The nozzle segment assembly of claim 1 , wherein a gap is defined between an inner surface of the strut vane and an outer surface of the strut when the strut is received within the strut vane.

13 . The nozzle segment assembly of claim 12 , wherein the gap is configured to receive a cooling medium for cooling at least one of the strut vane or the strut.

14 . A gas turbine engine, comprising:
a compressor; a combustor in flow communication with the compressor; and a turbine configured to receive combustion products from the combustor, the turbine including a turbine nozzle having an annular array of nozzle segment assemblies, each of the nozzle segment assemblies comprising:
an outer ring support segment and an inner ring support segment;
a nozzle fairing positioned between the inner and outer ring support segments, the nozzle fairing being formed from a ceramic matrix composite (CMC) material, the nozzle fairing including an outer endwall configured to be positioned adjacent to the outer ring support segment and an inner endwall configured to be positioned adjacent to the inner ring support segment, the nozzle fairing further comprising a strut vane extending between the inner and outer endwalls;
a metallic strut extending through the strut vane between the outer and inner ring supports; and
at least one secondary vane configured to be received through at least one of the outer endwall or the inner endwall of the nozzle fairing such that the at least one secondary vane extends between the inner and outer endwalls at a location adjacent to the strut vane.

15 . The gas turbine engine of claim 14 , wherein the outer endwall defines an outer slot and the inner endwall defines an inner slot, wherein separate portions of the at least one secondary vane are configured to be received within the outer and inner slots.

16 . The gas turbine engine of claim 15 , wherein the at least one secondary vane extends radially between an outer vane end and an inner vane end, the at least one secondary vane being configured to extend through the inner and outer slots such that the outer vane end extends radially outwardly from the outer endwall and the inner vane end extend radially inwardly from the inner endwall.

17 . The gas turbine engine of claim 16 , wherein the outer vane end is configured to be received within a vane recess defined in the outer ring support, the at least one secondary vane comprising a mounting tab extending from the outer vane end, the mounting tab defining a through-hole configured to receive a mounting pin for coupling the at least one secondary vane to the outer ring support.

18 . The gas turbine engine of claim 16 , wherein the inner vane end is configured to be received within a vane recess defined in the inner ring support.

19 . The gas turbine engine of claim 14 , wherein the inner and outer endwalls and the strut vane are formed integrally as a single unitary component.

20 . The gas turbine engine of claim 14 , wherein the metallic strut extends radially inwardly from the outer ring support through the strut vane to a tip end, the tip end being configured to be received within a strut recess defined in the inner ring support segment.

Assignees

• Gen Electric

Inventors

• Weaver Matthew Mark

Classifications

• Y02T50/60

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

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title