Ceramic matrix composite heat shield for use in a turbine vane and a turbine shroud ring

Patent metadata

Field	Value
Publication number	US-11073039-B1
Application number	US-202016752175-A
Country	US
Kind code	B1
Filing date	Jan 24, 2020
Priority date	Jan 24, 2020
Publication date	Jul 27, 2021
Grant date	Jul 27, 2021

Abstract

A turbine section of a gas turbine engine includes a vane assembly that redirects hot gases in the turbine section, a turbine shroud that extends around a turbine wheel to keep the hot gases from avoiding interaction with the turbine wheel, and a heat shield that provides parts of the vane assembly and the turbine shroud. The heat shield comprises ceramic matrix composite materials and is formed as a one piece component. The heat shield includes a vane portion that protects other vane assembly parts, a seal segment portion that protects other turbine shroud parts, and a forward turn-up and an aft turn-up. The forward turn-up and the aft turn-up couple the heat shield to other parts of the turbine section.

First claim

What is claimed is:

1. A turbine section of a gas turbine engine, the turbine section comprising
a turbine case shaped to surround a central axis of the turbine section,
a carrier segment comprising metallic materials and extending partway around the central axis, the carrier segment including a main body coupled to the case, a forward shield mount arranged along a forward side of the main body, and an aft shield mount arranged along an aft side of the main body,
a vane assembly including a support spar comprising metallic materials, the support spar coupled to the main body of the carrier segment and extending radially inward from the main body of the carrier segment toward the central axis,
a turbine wheel including a disk mounted for rotation about the central axis and a plurality of blades coupled to the periphery of the disk for rotation therewith about the central axis,
a turbine shroud located co-axially with and radially outward of the turbine wheel to block gases moving along a primary gas path from moving over the blades of the turbine wheel without interacting with the turbine blades, the turbine shroud including a turbine shroud portion of the carrier segment, and
a heat shield comprising ceramic matrix composite materials included as part of the vane assembly and the turbine shroud, the heat shield formed as a one piece component that is shaped to include (i) a vane portion having an outer platform and an airfoil that protect the support spar of the vane assembly, (ii) a seal segment portion that protects the turbine shroud portion of the carrier segment so as to provide the vane assembly and the turbine shroud without a gap between the outer platform of the vane assembly and the turbine shroud, and (iii) a forward turn-up extending radially outward from a forward edge of the outer platform and an aft turn-up extending radially outward from an aft edge of the seal segment portion, the forward turn-up and the aft turn-up coupling the heat shield to the carrier segment.

2. The turbine section of claim 1 , wherein
the forward shield mount is rigidly attached to the forward side of the main body of the carrier segment, and
the aft shield mount is rigidly attached to the aft side of the main body of the carrier segment.

3. The turbine section of claim 2 , wherein
the forward turn-up is configured to couple to the forward shield mount, and
the aft turn-up is configured to couple to the aft shield mount.

4. The turbine section of claim 3 , wherein
the forward shield mount extends at least partway over a circumferential extent of the forward turn-up,
the aft shield mount extends at least partway over a circumferential extent of the aft turn-up,
the forward shield mount includes a first forward wall and a first aft wall defining a forward shield mount trench that at least partially surrounds a forward tip portion of the forward turn-up when the forward turn-up is coupled to the forward shield mount,
the aft shield mount includes a second forward wall and a second aft wall defining an aft shield mount trench that at least partially surrounds an aft tip portion of the aft turn-up when the aft turn-up is coupled to the aft shield mount,
a first width of the forward shield mount trench in an axial direction of the gas turbine engine is greater than a first thickness of the forward tip portion so as to form a first axial gap between the forward tip portion and the first aft wall, and
a second width of the aft shield mount trench in the axial direction is greater than a second thickness of the aft tip portion so as to form a second axial gap between the aft turn-up and the second aft wall.

5. The turbine section of claim 4 , wherein
a radial extent of the forward shield mount trench is greater than a radial extent of the forward tip portion so as to form a first radial gap between a top surface of the forward tip portion and a top wall of the forward shield mount trench, and
a radial extent of the aft shield mount trench is greater than a radial extent of the aft tip portion so as to form a second radial gap between a top surface of the aft tip portion and a top wall of the aft shield mount trench.

6. The turbine section of claim 4 , further comprising
a first axial load rail arranged on the first aft wall between the forward tip portion and the first aft wall, and
a second axial load rail arranged on the second aft wall between the aft tip portion and the second aft wall,
wherein the forward tip portion and the aft tip portion are configured to engage the first axial load rail and the second axial load rail, respectively, when the gases moving along the primary gas path exert a force on the forward turn-up and the aft turn-up, respectively.

7. The turbine section of claim 4 , further comprising
at least one forward pin extending through the first forward wall, the forward tip portion, and the first aft wall in the axial direction,
at least one aft pin extending through the second forward wall, the aft tip portion, and the second aft wall in the axial direction,
wherein the at least one forward pin and the at least one aft pin are configured to transfer aerodynamic loads from the forward turn-up and the aft turn-up to the forward shield mount and the aft shield mount, respectively, when the gases moving along the primary gas path exert a force on the forward turn-up and the aft turn-up, respectively.

8. The turbine section of claim 1 , wherein
the heat shield further includes a protrusion extending radially away from the outer platform towards the carrier segment,
the protrusion surrounds at least a portion of an outer surface of the support spar that extends between the carrier segment and the outer platform so as to form a gap between an inner surface of the protrusion and the outer surface of the support spar.

9. The turbine section of claim 8 , further comprising
at least one of an axial load pad, a circumferential load pad, and at least one radial load pin,
wherein:
the axial load pad is arranged on the carrier segment and extends radially inward towards the outer platform so as to be axially adjacent to the protrusion, the axial load pad configured to interact with an outer protrusion wall of the protrusion so as to transfer aerodynamic loads from the heat shield to the carrier segment when the gases moving along the primary gas path exert a force on the heat shield;
the circumferential load pad is arranged on the carrier segment and extends radially inward towards the outer platform so as to be circumferentially adjacent to the protrusion, the circumferential load pad configured to interact with the outer protrusion wall so as to transfer aerodynamic loads from the heat shield to the carrier segment when the gases moving along the primary gas path exert a force on the heat shield; and
the at least one radial load pin extends through the protrusion into at least one wing of the carrier segment, the at least one wing arranged on the carrier segment and extending radially inward past a top portion of the protrusion.

10. The turbine section of claim 1 , wherein the heat shield further includes an inner platform formed as one piece with the vane portion, the seal segment portion, and the forward and aft turn-ups.

11. The turbine section of claim 10 , wherein
the vane assembly includes a sealing retainer disposed on an inner radially end of the support spar opposite the main body of the carrier segment, and
the sealing retainer is configured to engage with the inner platform in order to seal a radially inner end of the vane assembly.

12. A turbine section of a gas turbine engine, the turbine section comprising
a carrier segment compr

Assignees

• Rolls Royce Pic
• Rolls Royce High Temperature Composites Inc
• Rolls Royce Plc

Inventors

• Whittle Michael J
• Abbott Michael J

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D11/08 Primary

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F05D2230/64

  using positioning or alignment devices for aligning or centring, e.g. pins · CPC title

• F01D5/284

  Selection of ceramic materials · CPC title