Turbine nozzles with slip joints impregnated by oxidation-resistant sealing material and methods for the production thereof

Patent metadata

Field	Value
Publication number	US-9970307-B2
Application number	US-201414219622-A
Country	US
Kind code	B2
Filing date	Mar 19, 2014
Priority date	Mar 19, 2014
Publication date	May 15, 2018
Grant date	May 15, 2018

Abstract

Embodiments of a turbine nozzle having slip joints impregnated by an oxidation-resistant sealing material are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the method includes providing a support ring, a slip joint ring substantially concentric with the support ring and radially spaced apart therefrom, and a plurality of vanes fixedly coupled to the support ring. The plurality of vanes extends radially from the support ring into a plurality of circumferentially-spaced slots provided in the slip joint ring to form a plurality of slip joints therewith. The plurality of slip joints are impregnated with a silicon-modified aluminide sealing material. The silicon-modified aluminide sealing material impedes gas flow into the radial slip joints during operation of the turbine nozzle, while also fracturing to permit relative radial movement between the plurality of vanes and the slip joint ring along the plurality of slip joints.

First claim

What is claimed is:

1. A method for manufacturing a turbine nozzle, comprising:
providing a support ring, a slip joint ring substantially concentric with the support ring and radially spaced apart therefrom, and a plurality of vanes fixedly coupled to the support ring and extending radially therefrom into a plurality of circumferentially-spaced slots in the slip joint ring to form a plurality of slip joints therewith; and
impregnating the plurality of slip joints with a silicon-modified aluminide sealing material, the silicon-modified aluminide sealing material impeding gas flow into the radial slip joints during operation of the turbine nozzle, while fracturing to permit relative radial movement between the plurality of vanes and the slip joint ring along the plurality of slip joints;
wherein the plurality of circumferentially-spaced slots comprises non-penetrating depressions formed in a circumferential surface of the slip joint ring; and
wherein the silicon-modified aluminide sealing material is applied in sufficient volume to fill annular spaces in the plurality of slip joints, while leaving unfilled radial gaps between terminal ends of the plurality of vanes and floor portions of the non-penetrating depressions, the unfilled radial gaps sized and shaped to accommodate relative radial movement between the turbine nozzle vanes and the slip joint ring during operation of the turbine nozzle.

2. The method of claim 1 wherein impregnating comprises applying the silicon-modified aluminide sealing material in slurry form around the plurality of slip joints such that the silicon-modified aluminide sealing material flows into the plurality of slip joints by capillary action during the impregnation process.

3. The method of claim 2 wherein the silicon-modified aluminide sealing material comprises a metallic powder dissolved in a liquid carrier, the metallic powder composed of at least 50 weight percent aluminum and at least 10 weight percent silicon.

4. The method of claim 1 further comprising slidably attaching the plurality of vanes to the slip joint ring utilizing radial retention pins extending through the floor portions of the non-penetrating depressions, the radial retention pins permitting relative radial movement between the vane and the slip joint ring, while retaining the vanes in the event of airfoil burn-through.

5. The method of claim 4 wherein slidably attaching comprises:
inserting the radial retention pins through aligning radial bores provided in the slip joint ring and in the plurality of vanes; and
bonding the radial retention pins to at least one of the slip joint ring and the plurality of vanes.

6. The method of claim 1 further comprising applying a platinum aluminide bond coat over the surfaces of plurality of vanes and surfaces of the slip joint ring defining the plurality of circumferentially-spaced slots prior to impregnating the plurality of slip joints with the silicon-modified aluminide sealing material.

7. The method of claim 1 wherein providing comprises:
assembling the support ring, the slip joint ring, and the plurality of vanes into the turbine nozzle; and
bonding the plurality of vanes to the support ring after assembling the support ring, the slip joint ring, and the plurality of vanes into the turbine nozzle and prior to impregnating the plurality of slip joints with the silicon-modified aluminide sealing material.

8. The method of claim 7 wherein the support ring, the slip joint ring, and the plurality of vanes into the turbine nozzle are each separately cast prior to assembly into the turbine nozzle.

9. The method of claim 7 wherein bonding comprises brazing the plurality of vanes to the support ring.

10. The method of claim 7 further comprising applying a bond coat over surfaces of the slip joint ring and the plurality of vanes prior to assembling the support ring, the slip joint ring, and the plurality of vanes into the turbine nozzle.

11. The method of claim 7 further comprising applying a thermal barrier coating over selected surfaces of the support ring, the slip joint ring, and the plurality of vanes, the thermal barrier coating terminating substantially adjacent the silicon-modified aluminide sealing material.

12. A method for manufacturing a turbine nozzle, comprising:
assembling the turbine nozzle from a support ring, a slip joint ring having a plurality of slots provided therein, and a plurality of vanes extending from the support ring into the plurality of slots provided in the slip joint ring to define a plurality of slip joints;
prior to assembling the turbine nozzle, forming a first platinum aluminide bond coat on surfaces of the slip joint ring defining the plurality of slots and forming a second platinum aluminide bond coat on terminal end portions of the plurality of vanes;
bonding the plurality of vanes to the support ring; and
after bonding the plurality of vanes to the support ring, forming annular seals within the plurality of slip joints and around the terminal end portions of the plurality of vanes, forming comprising:
dispensing a slurry containing an oxidation-resistant sealing material around the plurality of slip joints in sufficient volume to allow the slurry to flow into the plurality of slip joints by capillary action and contact the first and second platinum aluminide bond coats, while leaving unfilled radial gaps adjacent terminal end portions of the plurality of vanes accommodating relative radial movement between the turbine nozzle vanes and the slip joint ring during operation of the turbine nozzle; and
heat treating the turbine nozzle to thermally decompose organic materials from the slurry and diffuse the oxidation-resistant sealing material into the first and second platinum aluminide bond coats.

13. The method of claim 12 wherein the oxidation-resistant sealing material comprises a silicon-enriched aluminide material.

14. The method of claim 12 further comprising slidably attaching the plurality of vanes to the slip joint ring utilizing a plurality of radial retention pins, each radial retention pin extending substantially perpendicular to the longitudinal axis of the turbine nozzle.

15. A turbine nozzle, comprising:
a support ring;
a slip joint ring substantially concentric with the support ring and radially spaced apart therefrom, the slip joint ring having a plurality of circumferentially-spaced slots therein;
a plurality of vanes fixedly coupled to the support ring and extending radially therefrom into the plurality of circumferentially-spaced slots;
a plurality of radial slip joints formed between the plurality of vanes and the plurality of circumferentially-spaced slots; and
a silicon-modified aluminide sealing material impregnated into the plurality of radial slip joints, the silicon-modified aluminide sealing material impeding gas flow into the radial slip joints during operation of the turbine nozzle, while fracturing to permit relative radial movement between the plurality of vanes and the slip joint ring;
wherein the plurality of circumferentially-spaced slots comprises non-penetrating depressions formed in a circumferential surface of the slip joint ring and having floor portions; and
wherein the silicon-modified aluminide sealing material fills annular spaces in the plurality of slip joints to sealingly enclose unfilled radial gaps located between terminal ends of the plurality of vanes and the floor portions of the non-penetrating depressions, the unfilled radial gaps sized and shaped to accommodate relative radial movement between the turbine nozzle vanes and the slip joint ring during operation of the turb

Assignees

• Honeywell Int Inc

Inventors

• Kanjiyani Shezan
• Tucker Bradley Reed
• Wali Natalie
• Hicks Daniel
• Macelroy Bill

Classifications

• F01D9/041 Primary

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

• F01D17/162

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• B23K1/0018

  Brazing of turbine parts · CPC title

• B23K2201/001

  Operations & Transport · mapped topic

• F01D5/28

  Selecting particular materials; {Particular measures relating thereto;} Measures against erosion or corrosion · CPC title