Clamped vane arc segment having load-transmitting features

Patent metadata

Field	Value
Publication number	US-10072516-B2
Application number	US-201514838407-A
Country	US
Kind code	B2
Filing date	Aug 28, 2015
Priority date	Sep 24, 2014
Publication date	Sep 11, 2018
Grant date	Sep 11, 2018

Abstract

A vane arc segment includes a radially inner and outer platforms and an airfoil mechanically clamped between the platforms. The airfoil has an airfoil section that extends radially between radially inner and outer fairing platforms. At least one of the fairing platforms includes forward and aft sides, circumferential sides, and a gas path side and an opposed radial side. The radial side includes a plurality of protrusions that have faces that are oriented substantially normal to, respectively, radial, tangential, and axial load transmission directions of the airfoil such that the faces, respectively, primarily bear radial, tangential, and axial load transmissions of the airfoil.

First claim

What is claimed is:

1. A vane arc segment comprising:
radially inner and outer platforms; and
an airfoil mechanically clamped between the platforms, the airfoil has an airfoil section that extends radially between radially inner and outer fairing platforms, at least one of the fairing platforms includes forward and aft sides, circumferential sides, and a gas path side and an opposed radial side, and the radial side includes a plurality of protrusions that have faces that are oriented substantially normal to, respectively, radial, tangential, and axial load transmission directions of the airfoil such that the faces, respectively, bear radial, tangential, and axial load transmissions of the airfoil; and
wherein the plurality of protrusions includes first and second rails that extend circumferentially along the extent of the forward and aft sides.

2. The vane arc segment as recited in claim 1 , wherein the plurality of protrusions include a tab that extends axially from the first rail.

3. The vane arc segment as recited in claim 2 , wherein the tab extends along a central tab axis that is substantially perpendicular to the first rail such that the tab has circumferential tab faces that are oriented substantially normal to the tangential load transmission direction.

4. The vane arc segment as recited in claim 3 , wherein the tab includes a radial tab face that is oriented substantially normal to the radial load transmission direction.

5. The vane arc segment as recited in claim 1 , wherein the first and second rails are axially offset from, respectively, edges of the forward and aft sides.

6. The vane arc segment as recited in claim 1 , wherein the first and second rails include radial rail faces that are oriented substantially normal to the radial load transmission direction and axial rail faces that are oriented substantially normal to the axial load transmission direction.

7. The vane arc segment as recited in claim 1 , wherein the airfoil section includes a hollow interior and a rib that extends in the hollow interior and protrude from the hollow interior.

8. The vane arc segment as recited in claim 7 , wherein the rib includes axial rib faces that are oriented substantially normal to the axial load transmission direction.

9. The vane are segment as recited in claim 8 , wherein the rib includes a radial rib face that is oriented substantially normal to the radial load transmission direction.

10. The vane arc segment as recited in claim 1 , wherein the plurality of protrusions includes a first elongated tab that extends in radial alignment with a convex side of the airfoil section.

11. The vane arc segment as recited in claim 10 , wherein the first elongated tab includes a radial tab face that is oriented substantially normal to the radial load transmission direction.

12. The vane arc segment as recited in claim 10 , wherein the plurality of protrusions includes a second elongated tab that is substantially perpendicular to the first elongated tab.

13. The vane arc segment as recited in claim 1 , wherein the plurality of protrusions includes first and second mateface rails that extend axially along the circumferential sides, and a tab that extends circumferentially toward the airfoil section from one of the first and second mateface rails.

14. The vane arc segment as recited in claim 13 , wherein the tab includes a radial tab face that is oriented substantially normal to the radial load transmission direction and an axial tab face that is oriented substantially normal to the axial load transmission direction.

15. A vane assembly comprising:
a plurality of vane arc segments that are arrangeable into an annular configuration, each of the vane arc segments includes:
radially inner and outer platforms, and
an airfoil mechanically clamped between the platforms, the airfoil has an airfoil section that extends radially between radially inner and outer fairing platforms, at least one of the fairing platforms includes forward and aft sides, circumferential sides, and a gas path side and an opposed radial side, and the radial side includes a plurality of protrusions that have faces that are oriented substantially normal to, respectively, radial, tangential, and axial load transmission directions of the airfoil such that the faces, respectively, bear radial, tangential, and axial load transmissions of the airfoil wherein the plurality of protrusions includes first and second rails that extend circumferentially along the extent of the forward and aft sides.

16. A gas turbine engine comprising:
a core engine that includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, and a vane assembly that includes a plurality of vane arc segments arranged in an annular configuration in a core gas path of the core engine, each of the vane arc segments includes:
radially inner and outer platforms, and
an airfoil mechanically clamped between the platforms, the airfoil has an airfoil section that extends radially between radially inner and outer fairing platforms, at least one of the fairing platforms includes forward and aft sides, circumferential sides, and a gas path side and an opposed radial side, and the radial side includes a plurality of protrusions that have faces that are oriented substantially normal to, respectively, radial, tangential, and axial load transmission directions of the airfoil such that the faces, respectively, bear radial, tangential, and axial load transmissions of the airfoil, wherein the plurality of protrusions includes first and second rails that extend circumferentially along the extent of the forward and aft sides.

Assignees

• United Technologies Corp

Inventors

• Carr Jesse M
• Dube Bryan P

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F01D9/042

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

• F01D9/041 Primary

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

• F02C3/04

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

• F01D25/28

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title