Support ring with thermal heat shield for case flange

1. A heat shield vane support having a structure including at least one of a cylindrical portion and a frustoconical portion with an outboard diameter and an inboard diameter extending about an axis and extending axially between a forward face and an aft face, comprising:

a flange extending circumferentially about the aft face radially inward from the inboard diameter;

a plurality of anti-rotation features distributed circumferentially about the inboard diameter extending radially inward from the inboard diameter and extending axially with respect to the cylindrical portion between a forward edge and an aft edge; and

a plurality of teeth distributed circumferentially about the forward face and extending axially from the forward face,

wherein the plurality of anti-rotation features comprises a first thickness defined between a first channel and a second channel, wherein the first channel and the second channel are cut radially outboard from the inboard diameter toward the outboard diameter, wherein the first channel and the second channel extend axially over a portion of the inboard diameter of the cylindrical portion and parallel the axis.

2. The heat shield vane support of claim 1 , wherein a flow discouraging rail extends circumferentially about the aft face radially outward from the outboard diameter.

3. The heat shield vane support of claim 1 , wherein the plurality of anti-rotation features comprise a clocking feature proximate the forward edge of the plurality of anti-rotation features, wherein the clocking feature defines a second thickness, wherein the second thickness is less than the first thickness, wherein the clocking feature describes a stepped transition between the first thickness and the second thickness.

4. The heat shield vane support of claim 1 , wherein a plurality of tooling features distributed circumferentially about the outboard diameter extend radially from the outboard diameter.

5. The heat shield vane support of claim 4 , wherein each tooling feature in the plurality of tooling features extend from a portion of the outboard diameter defined radially outward of the plurality of anti-rotation features.

6. The heat shield vane support of claim 1 , wherein the flange comprises a port.

7. The heat shield vane support of claim 1 , wherein the flange comprises a gasket support ring at a distal end of the flange from the inboard diameter, wherein the gasket support ring extends circumferentially about the distal end of the flange and axially aft of the flange.

8. A gas turbine engine comprising:

a compressor section configured to compress a gas;

a combustor section aft of the compressor section configured to combust the gas and comprising a diffuser case having a diffuser case flange, a torque takeout ring, and a compression ring aft of the torque takeout ring;

a turbine section aft of the combustor section configured to extract work from the combusted gas, the turbine section having a turbine case coupled to the diffuser case at an interface between the diffuser case flange and a turbine case flange; and

a heat shield vane support radially inward of the interface between the diffuser case flange and the turbine case flange, the heat shield vane support having a structure including at least one of a cylindrical portion and a frustoconical portion with an outboard diameter and an inboard diameter extending about an axis and extending axially between a forward face and an aft face, comprising:

a flange extending circumferentially about the aft face radially inward from the inboard diameter;

a plurality of anti-rotation features distributed circumferentially about the inboard diameter extending radially inward from the inboard diameter and extending axially with respect to the cylindrical portion between a forward edge and an aft edge; and

a plurality of teeth distributed circumferentially about the forward face and extending axially from the forward face,

wherein the plurality of anti-rotation features comprises a first thickness defined between a first channel and a second channel, wherein the first channel and the second channel are cut radially outboard from the inboard diameter toward the outboard diameter, wherein the first channel and the second channel extend axially over a portion of the inboard diameter of the cylindrical portion and parallel the axis.

9. The gas turbine engine of claim 8 , wherein a flow discouraging rail extends circumferentially about the aft face radially outward from the outboard diameter.

10. The gas turbine engine of claim 9 , wherein the plurality of anti-rotation features comprise a clocking feature proximate the forward edge of the plurality of anti-rotation features, wherein the clocking feature defines a second thickness, wherein the second thickness is less than the first thickness, wherein the clocking feature describes a stepped transition between the first thickness and the second thickness.

11. The gas turbine engine heat shield vane support of claim 8 , wherein a plurality of tooling features distributed circumferentially about the outboard diameter extend radially from the outboard diameter.

12. The gas turbine engine of claim 11 , wherein each tooling feature in the plurality of tooling features extend from a portion of the outboard diameter defined radially outward of the plurality of anti-rotation features.

13. The gas turbine engine of claim 8 , wherein the flange comprises a port.

14. The gas turbine engine of claim 8 , wherein the flange comprises a gasket support ring at a distal end of the flange from the inboard diameter, wherein the gasket support ring extends circumferentially about the distal end of the flange and axially aft of the flange.

15. The gas turbine engine of claim 8 , wherein each of the plurality of teeth are disposed within a notch of the torque takeout ring.

16. The gas turbine engine of claim 8 , wherein a first interference between the compression ring and the outboard diameter tends to retain the heat shield vane support axially with respect to the diffuser case flange.

17. The gas turbine engine of claim 8 , wherein a yoke of a vane is disposed about each of the plurality of anti-rotation features, wherein a second interference between the yoke and each of the plurality of anti-rotation features inhibits rotation of the vane about a radial axis of the vane.

18. A method of assembling a vane assembly, the method comprising:

inserting a heat shield vane support having a structure including at least one of a cylindrical portion and a frustoconical portion with an outboard diameter and an inboard diameter extending about an axis and extending axially between a forward face and an aft face into a bypass duct of a diffuser case having a diffuser case flange, wherein the forward face is proximate a torque takeout ring, wherein the diffuser case flange lies between the forward face and the aft face and radially outward of the outboard diameter;

inserting each of a plurality of teeth extending from the forward face through each of a plurality of notches of the torque takeout ring;

compressing the cylindrical portion of the heat shield vane support and generating an interference retaining the heat shield vane support axially with respect to the diffuser case flange; and

disposing a yoke of a vane about each of a plurality of anti-rotation features of the heat shield vane support distributed circumferentially about the inboard diameter, wherein the plurality of anti-rotation features extend radially inward from the inboard diameter and extend axially with respect to the cylindrical portion between a forward edge and an aft edge,

wherein the plurality of anti-rotation features comprises a first thickness defined between a first channel and a second channel, wherein the first channel and the second channel are cut radially outboard from the inboard diameter toward the outboard diameter, wherein the first channel and the second channel extend axially over a portion of the inboard diameter of the cylindrical portion and parallel the axis.