Turbine vane with heat shield

Patent metadata

Field	Value
Publication number	US-2016265384-A1
Application number	US-201615058885-A
Country	US
Kind code	A1
Filing date	Mar 2, 2016
Priority date	Mar 11, 2015
Publication date	Sep 15, 2016
Grant date	—

Abstract

A gas turbine engine may include a body and a turbine-vane ring coupled to the body. The turbine-vane ring may include a plurality of turbine-vane assemblies.

First claim

What is claimed is:

1 . A turbine-vane assembly comprising
a vane unit including an inner flange, an outer flange located in spaced-apart radial relation to the inner flange, and a vane extending between and interconnecting the inner and outer flanges and a heat shield including an inner-flange shield coupled to the inner flange, an outer-flange shield coupled to the outer flange, and a vane shield coupled to the vane and arranged to extend between and interconnect the inner and outer flange shields.

2 . The turbine-vane assembly of claim 1 , wherein the heat shield comprises ceramic matrix composite.

3 . The turbine-vane assembly of claim 2 , wherein the vane shield is joined to the inner-flange shield by a first co-processing bond and the vane shield is joined to the outer-flange shield by a second co-processing bond.

4 . The turbine-vane assembly of claim 3 , wherein the vane shield is located on a pressure side of the vane.

5 . The turbine-vane assembly of claim 4 , wherein the inner-flange shield is in spaced-apart relation to the inner flange, the vane shield is in spaced-apart relation to the pressure side of the vane, and the outer-flange shield is in spaced-apart relation to the outer flange.

6 . The turbine-vane assembly of claim 3 , wherein the vane shield includes a vane shield body and a vane shield inner-flange edge and the vane shield inner-flange edge is located at the first co-processing bond and comprises a first plurality of teeth, the inner-flange shield includes an inner-flange shield body and an inner-flange shield vane edge and the inner-flange shield vane edge is located at the first co-processing bond and comprises a second plurality of teeth, and the first plurality of teeth and the second plurality of teeth are configured to fit together.

7 . The turbine-vane assembly of claim 6 , wherein each tooth in the first plurality of teeth and the second plurality of teeth has a substantially rectangular shape.

8 . The turbine-vane assembly of claim 3 , wherein the vane shield includes a vane shield body, a vane shield inner-flange edge, and a first vane shield tab extending from the vane shield inner-flange edge, the inner-flange shield includes an inner-flange shield body, an inner-flange shield vane edge, and an inner-flange shield tab extending from the inner-flange shield vane edge, a first cavity is formed in the first vane shield tab and a second cavity is formed in the inner-flange shield tab, the first and second cavities are aligned and configured to receive a pin therein, and the first co-processing bond is located at the intersection of the cavities and the pin.

9 . The turbine-vane assembly of claim 3 , wherein the vane shield includes a vane shield body, a vane shield inner-flange edge, and a first vane shield lip extending between the vane shield body and the vane shield inner-flange edge, the first vane shield lip is thicker than the vane shield inner-flange edge and the first vane shield lip is thicker than a portion of the vane shield body, the inner-flange shield includes an inner-flange shield body and an inner-flange shield vane edge, the inner-flange shield vane edge engages the vane shield inner-flange edge and the first vane shield lip, and the first co-processing bond is located at the intersection of the inner-flange shield vane edge and the vane shield inner-flange edge and at the intersection of the first vane shield lip and the inner-flange shield vane edge.

10 . The turbine-vane assembly of claim 3 , wherein the inner-flange shield includes an inner-flange shield body, an inner-flange shield vane edge, and an inner-flange shield lip extending between the inner-flange shield body and the inner-flange shield vane edge, the inner-flange shield lip is thicker than the inner-flange shield vane edge, the vane shield includes a vane shield body and a vane shield inner-flange edge, the vane shield inner-flange edge engages the inner-flange shield vane edge and the inner-flange shield lip, and the first co-processing bond is located at the intersection of the vane shield inner-flange edge and the inner-flange shield vane edge and at the intersection of the inner-flange shield lip and the vane shield inner-flange edge.

11 . The turbine-vane assembly of claim 3 , wherein the vane shield includes a vane shield body, a vane shield inner-flange edge, and a first plurality of cavities formed in the vane shield body, the inner-flange shield includes an inner-flange shield body and an inner-flange shield vane edge, the first plurality of cavities formed in the vane shield body are each configured to receive a pin, the pins engage the vane shield edge, the vane shield body, and the inner-flange shield vane edge, a plurality of fairings engage the vane shield body, the inner-flange shield vane edge, and at least one of the pins, and the first co-processing bond is located at the intersection of the pins and the vane shield body, the intersection of the pins and the vane shield inner-flange edge, the intersection of the pins and the inner-flange shield vane edge, the intersection of the pins and the plurality of fairings, the intersection of the plurality of fairings and the vane shield body, and the intersection of the plurality of fairings and the inner-flange shield vane edge.

12 . The turbine-vane assembly of claim 1 , wherein the vane shield is located in spaced-apart relation to the vane to define a first passage therebetween.

13 . The turbine-vane assembly of claim 12 , further comprising a plurality of spacing nubs located between the vane shield and the vane.

14 . The turbine-vane assembly of claim 12 , wherein the inner flange is located in spaced-apart relation to the inner-flange shield to define a second passage therebetween.

15 . The turbine-vane assembly of claim 14 , wherein the outer flange is located in spaced-apart relation to the outer-flange shield to define a third passage therebetween.

16 . The turbine-vane assembly of claim 1 , wherein the inner-flange shield is coupled to the inner flange in a fixed position relative to the inner flange, the outer-flange shield is coupled to the outer flange in a fixed position relative to the outer flange, and the vane shield is coupled to the vane in a fixed position relative to the vane.

17 . The turbine-vane assembly of claim 1 , wherein the heat shield comprises a single fiber preform and a ceramic matrix deposited onto the preform to cause the vane shield, the inner-flange shield, and the outer-flange shield to be formed integrally.

18 . The turbine-vane assembly of claim 1 , wherein the vane unit is configured to provide means for receiving a portion of an adjacent heat shield included in an adjacent turbine-vane assembly to support and stabilize the adjacent heat shield included in the adjacent turbine-vane assembly.

19 . A turbine assembly comprising
an airfoil unit including a first flange and an airfoil coupled to the first flange to move therewith and extend away from the first flange and a heat shield including an airfoil shield extending away from the first flange and extending along one of a pressure side of the airfoil and a suction side of the airfoil to cause the other of the pressure side and suction side of the airfoil to be exposed.

20 . The turbine assembly of claim 19 , wherein the airfoil unit is a vane unit and the airfoil is a vane.

Assignees

• Rolls Royce Corp

Inventors

• Walston Jeffrey A
• Sippel Aaron D
• Schetzel Tara G
• Thomas David J
• Shi Jun
• Belcher Brad D

Classifications

• F01D5/282

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• F01D5/284

  Selection of ceramic materials · CPC title

• F01D5/143

  Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour · CPC title

• F05D2240/81

  Cooled platforms · CPC title

• F05D2240/15

  Heat shield · CPC title