Reinforced film floatwall for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-12352441-B2
Application number	US-202318371929-A
Country	US
Kind code	B2
Filing date	Sep 22, 2023
Priority date	Sep 22, 2023
Publication date	Jul 8, 2025
Grant date	Jul 8, 2025

Abstract

An assembly for a combustor for a gas turbine engine, including: a plurality of heat shield panels attached to at least one combustor liner, each one of the plurality of heat shield panels including a panel portion and a first forward rail and a second rearward rail each extending from an outer surface of the panel portion, the panel portion including an inner surface opposite of the outer surface, the panel portion also includes a forward end and a rearward end, the forward end of the panel portion is axially forward of the rearward end of an adjacent heat shield panel of the plurality of heat shield panels such that a gap is defined between the outer surface of the panel portion of one heat shield panel of the plurality of heat shield panels and an inner surface of the panel portion of an adjacent heat shield panel of the plurality of heat shield panels, the panel portion also includes a plurality of apertures extending from the outer surface to the inner surface; and a plurality of cooling pins extending upwardly and away from the outer surface towards a surface of the at least one combustor liner.

First claim

What is claimed is:

1. An assembly for a combustor for a gas turbine engine, comprising:
a plurality of heat shield panels attached to at least one combustor liner, each one of the plurality of heat shield panels including a panel portion and a first forward rail and a second rearward rail each extending from an outer surface of the panel portion, the panel portion including an inner surface opposite of the outer surface, the panel portion also includes a forward end and a rearward end, the forward end of the panel portion is axially forward of the rearward end of an adjacent heat shield panel of the plurality of heat shield panels such that a gap is defined between the outer surface of the panel portion of one heat shield panel of the plurality of heat shield panels and an inner surface of the panel portion of an adjacent heat shield panel of the plurality of heat shield panels, the panel portion also includes a plurality of apertures extending from the outer surface to the inner surface; a plurality of cooling pins extending upwardly and away from the outer surface towards a surface of the at least one combustor liner, the plurality of cooling pins being located rearward of the second rearward rail; a plurality of effusion holes extending from the outer surface of the panel portion to the inner surface of the panel portion, the plurality of effusion holes extending from the outer surface of the panel portion to the inner surface of the panel portion in an area between the first forward rail and a second rearward rail, the plurality of effusion holes including effusion outlets located in the inner surface of the panel portion; and wherein the plurality of cooling pins are not located forward of the second rearward rail such that slot cooling is provided to the inner surface of the panel portion forward of the first forward rail and effusion cooling is provided to the inner surface of the panel portion rearward of the first forward rail and forward of the second rearward rail, and film cooling is provided to the inner surface of the panel portion rearward of the second rearward rail.

2. The assembly as in claim 1 , wherein the at least one combustor liner is formed from any one the following metals: nickel (Ni), aluminum (Al), titanium (Ti), steel, cobalt (Co) and/or an alloy of one the foregoing metals.

3. The assembly as in claim 1 , wherein the plurality of heat shield panels form a shingled and/or stepped hollow dual-walled structure.

4. The assembly as in claim 1 , wherein the at least one combustor liner is formed from a ceramic matrix composite (CMC) material.

5. The assembly as in claim 1 , wherein the plurality of heat shield panels and the at least one combustor liner extend circumferentially about a central longitudinal axis of a gas turbine engine.

6. The assembly as in claim 1 , wherein the plurality of heat shield panels are removably mounted to the at least one combustor liner by one or more attachment mechanisms.

7. The assembly as in claim 6 , wherein the one or more attachment mechanisms are integrally formed with a respective one of the plurality of heat shield panels.

8. The assembly as in claim 1 , wherein the combustor defines a combustion chamber, the combustion chamber includes a combustion area within the combustion chamber, the plurality of heat shield panels partially enclose the combustion area within the combustion chamber of the combustor.

9. The assembly as in claim 1 , wherein the first forward rail is located rearward from the forward end and the second rearward rail is located forward from the rearward end.

10. The assembly as in claim 9 , wherein the first forward rail is located closer to the forward end than the second rearward rail and the second rearward rail is located closer to the rearward end than the first forward rail.

11. The assembly as in claim 1 , wherein the first forward rail and the second rearward rail are formed integrally with each heat shield panel of the plurality of heat shield panels such that they are formed as a single unitary structure.

12. The assembly as in claim 1 , wherein the first forward rail and the second rearward rail are interconnected by side rails that extend axially along the panel portion.

13. The assembly as in claim 12 , wherein the side rails are located at peripheral edge portions of the panel portion.

14. The assembly as in claim 1 , wherein the at least one combustor liner has a staggered surface of varying heights to which the plurality of heat shield panels are secured.

15. The assembly as in claim 1 , wherein the second rearward rail extends further from the outer surface of the panel portion in a radial direction than the first forward rail such that when each one of the plurality of heat shield panels is secured to the at least one liner the panel portion is inclined with respect to the at least one liner such that the rearward end of the panel portion is further from the liner than the forward end of the panel portion.

16. The assembly as in claim 1 , wherein the plurality of cooling pins do not extend all the way to an inner surface of the at least one combustor liner.

17. A gas turbine engine, comprising:
a compressor section;
a combustor fluidly connected to the compressor section;
a turbine section fluidly connected to the combustor, the combustor comprising:
an assembly, comprising:
a plurality of heat shield panels attached to at least one combustor liner, each one of the plurality of heat shield panels including a panel portion and a first forward rail and a second rearward rail each extending from an outer surface of the panel portion, the panel portion including an inner surface opposite of the outer surface, the panel portion also includes a forward end and a rearward end, the forward end of the panel portion is axially forward of the rearward end of an adjacent heat shield panel of the plurality of heat shield panels such that a gap is defined between the outer surface of the panel portion of one heat shield panel of the plurality of heat shield panels and an inner surface of the panel portion of an adjacent heat shield panel of the plurality of heat shield panels, the panel portion also includes a plurality of apertures extending from the outer surface to the inner surface; a plurality of cooling pins extending upwardly and away from the outer surface towards a surface of the at least one combustor liner, the plurality of cooling pins being located rearward of the second rearward rail; a plurality of effusion holes extending from the outer surface of the panel portion to the inner surface of the panel portion, the plurality of effusion holes extending from the outer surface of the panel portion to the inner surface of the panel portion in an area between the first forward rail and a second rearward rail, the plurality of effusion holes including effusion outlets located in the inner surface of the panel portion; and wherein the plurality of cooling pins are not located forward of the second rearward rail such that slot cooling is provided to the inner surface of the panel portion forward of the first forward rail and effusion cooling is provided to the inner surface of the panel portion rearward of the first forward rail and forward of the second rearward rail, and film cooling is provided to the inner surface of the panel portion rearward of the second rearward rail.

18. The gas turbine engine as in claim 17 , wherein the plurality of heat shield panels and the at least one combustor liner extend circumferentially about a central longitudinal axis of a gas turbine engine

Assignees

• Rtx Corp

Inventors

• Joshi Dibesh D
• Dillard Gary J
• Cheung Albert K
• Kramer Stephen K

Classifications

• F23R3/60

  Support structures; Attaching or mounting means · CPC title

• F05D2260/22141

  using fins or ribs · CPC title

• F05D2260/202

  by film cooling · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title