Turbine engines with ceramic vanes and methods for manufacturing the same

Patent metadata

Field	Value
Publication number	US-10605086-B2
Application number	US-201213681675-A
Country	US
Kind code	B2
Filing date	Nov 20, 2012
Priority date	Nov 20, 2012
Publication date	Mar 31, 2020
Grant date	Mar 31, 2020

Abstract

A vane assembly includes first and second annular metal rings configured to accept a compressed gas flow therebetween. The first and second annular rings each include a cutout portion. The assembly further includes a ceramic matrix composite vane configured as an airfoil having a blunt rounded nose and a flattened and tapered tail. A first radial end of the vane is rigidly disposed on the first annular ring and a second radial end of the vane is slidably disposed within the cutout portion of the second annular ring such that the vane is encompassed by the first and second annular rings. The vane includes a hollow through opening portion extending radially therethrough. Still further, the assembly includes a metallic elongated member disposed within and extending through the hollow portion of vane and through the cutout portion of the first annular ring.

First claim

The invention claimed is:

1. A vane assembly comprising:
first and second annular metal rings configured to accept a compressed gas flow therebetween, wherein the first and second annular rings each include a cutout portion;
a ceramic matrix composite (CMC) vane configured as an airfoil having a blunt rounded nose and a flattened and tapered tail, wherein a first radial end of the CMC vane is rigidly disposed on the first annular ring but not into the cutout portion of the first annular ring and a second radial end of the CMC vane is slidably disposed within and through the cutout portion of the second annular ring such that the CMC vane is encompassed by the first and second annular rings, wherein the CMC vane is freely slidable within the cutout portion of the second annular ring in the radial direction, wherein the CMC vane includes a hollow through opening portion extending radially therethrough, wherein the second radial end of the CMC vane comprises an extension portion, wherein the extension portion has a cross-sectional area in the plane perpendicular to the radial direction that is smaller in area as compared to the cross-sectional area of the CMC vane taken in the plane perpendicular to the radial direction, and wherein the extension portion is configured to fit within the cutout portion of the second annular ring; and
a metallic elongated member disposed within and extending through the hollow portion of the CMC vane and through the cutout portion of the first annular ring, wherein the elongated member is held in position between a first attachment portion disposed radially inward from the first annular ring and coupled thereto and a second attachment portion disposed radially outward from the second annular ring and coupled thereto, wherein the elongated member extends radially outward beyond the second radial end of the CMC vane to couple with the second attachment portion,
wherein the elongated member is capable of accepting an axial load from the CMC vane when an external force impinges axially against the CMC vane, but wherein the elongated member remains free to slide radially along the CMC vane and is not rigidly coupled to the CMC vane.

2. The vane assembly of claim 1 , wherein upon thermal expansion or contraction of the CMC vane, the CMC vane moves radially relative to the elongated member.

3. The vane assembly of claim 1 , wherein the elongated member is a metallic rod.

4. The vane assembly of claim 3 , wherein the rod includes a hollow portion to allow cooling air to flow therethrough.

5. The vane assembly of claim 4 , wherein the rod includes a plurality of openings along its length to allow the cooling air to enter into the hollow portion of the CMC vane.

6. The vane assembly of claim 1 , comprising a plurality of CMC vanes disposed between the first annular ring and the second annular ring.

7. The vane assembly of claim 1 , wherein the cutout portion of the second ring and a radial cross section of an extension portion of the CMC vane have corresponding shapes.

8. The vane assembly of claim 1 , wherein the axial load is provided by compressed air flow impinging axially against the CMC vane.

9. The vane assembly of claim 1 , wherein the elongated member does not provide any clamping force between the first and second rings, thereby avoiding any compressive radial loads on the CMC vane.

10. The vane assembly of claim 1 , wherein the first and second annular rings are comprised of a nickel superalloy.

11. The vane assembly of claim 1 , wherein the elongated member is configured to fit within and through the extension portion.

12. A vane assembly comprising:
first and second concentric rings configured to accept a compressed gas flow therebetween, wherein the first ring includes a cutout portion and the second ring includes a cutout portion, wherein the cutout portion of the second ring is larger in area than the cutout portion of the first ring, and wherein the first ring is coupled to and supported by a first attachment portion disposed radially inward from the first ring and the second ring is coupled to and supported by a second attachment portion disposed radially outward from the second ring;
a ceramic matrix composite (CMC) vane configured as an airfoil, wherein a first radial end of the CMC vane is rigidly disposed on the first ring but not into the cutout portion of the first ring and a second radial end of the CMC vane is slidably disposed within and through the cutout portion of the second ring without contacting the second attachment portion, wherein the CMC vane is freely slidable within the cutout portion of the second annular ring in the radial direction, wherein the CMC vane includes a hollow portion extending radially therethrough, wherein the second radial end of the CMC vane comprises an extension portion, wherein the extension portion has a cross-sectional area in the plane perpendicular to the radial direction that is smaller in area as compared to the cross-sectional area of the CMC vane taken in the plane perpendicular to the radial direction, and wherein the extension portion is configured to fit within the cutout portion of the second annular ring; and
an elongated member disposed within and extending through the hollow portion of the CMC vane, and also extending through the cutout portion of the first ring so as to contact with the first attachment portion and extending through the cutout portion of the second ring radially outward beyond the second radial end of the CMC vane so as to contact with the second attachment portion,
wherein the elongated member is capable of accepting an axial load from the CMC vane when an external force impinges axially against the CMC vane, but wherein the elongated member remains free to slide radially along the CMC vane and is not rigidly coupled to the CMC vane, and
wherein the elongated member does not provide any clamping force between the first and second rings, thereby avoiding any compressive radial loads on the CMC vane.

13. The vane assembly of claim 12 , wherein the first and second rings are comprised of a metal.

14. The vane assembly of claim 12 , wherein the elongated member is comprised of a metal.

15. The vane assembly of claim 12 , wherein the axial load is provided by compressed air flow impinging axially against the CMC vane.

Assignees

• Honeywell Int Inc

Inventors

• Zurmehly George E
• Ortiz Milton
• Poon Kin
• Vinup Michael
• Riahi Ardeshir

Classifications

• Y10T29/49316

  Impeller making · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D5/284

  Selection of ceramic materials · CPC title

• F01D5/12 Primary

  Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic