Gas turbine engine article with cooling holes for mitigating recession

Patent metadata

Field	Value
Publication number	US-11959396-B2
Application number	US-202217970662-A
Country	US
Kind code	B2
Filing date	Oct 21, 2022
Priority date	Oct 22, 2021
Publication date	Apr 16, 2024
Grant date	Apr 16, 2024

Abstract

A gas turbine engine article includes a silicon-containing ceramic wall that has an external combustion gaspath side and an internal side that borders a cooling air cavity. The external combustion gaspath side has an associated combustion gas flow direction there along. An array of cooling holes extends through the silicon-containing ceramic wall and connects the internal side with the external combustion gaspath side. The cooling holes are oriented to discharge cooling air to the external gaspath side in a direction counter to the combustion gas flow direction.

First claim

What is claimed is:

1. A gas turbine engine article comprising:
a silicon-containing ceramic wall having an external combustion gas path side and an internal side that borders a cooling air cavity, the external combustion gas path side having an associated combustion gas flow direction along the external combustion gas path side; and
an array of cooling holes extending through the silicon-containing ceramic wall and connecting the internal side with the external combustion gas path side, the cooling holes being oriented to discharge cooling air to the external combustion gas path side in a direction counter to the combustion gas flow direction, each of the cooling holes being comprised of a metering hole section of constant cross-sectional area and a surface breakout section that diverges from the metering hole section, the array including at least a first row of the cooling holes and a second row of the cooling holes, the surface breakout section of each of the cooling holes of the first row having a crescent geometry, and the surface breakout section of each of the cooling holes of the second row having a lobed geometry.

2. The gas turbine engine article as recited in claim 1 , wherein the silicon-containing ceramic wall is situated relative to a gas turbine central axis, and each of the cooling holes has a forward angle relative to the gas turbine central axis of less than 80° and greater than 30°.

3. The gas turbine engine article as recited in claim 1 , wherein the lobed geometry is a two-lobe geometry.

4. The gas turbine engine article as recited in claim 3 , wherein the two-lobe geometry has first and second lobes that are connected to each other at a neck region defined by opposed concave edges of the surface breakout section.

5. The gas turbine engine article as recited in claim 3 , wherein the two-lobe geometry has first and second lobes that are connected to each other at a neck region defined by opposed concave and convex edges of the surface breakout section.

6. The gas turbine engine article as recited in claim 1 , wherein the cooling holes are arranged in the array with a ratio of ligament length to cooling hole diameter of 2:1 to 8:1.

7. The gas turbine engine article as recited in claim 1 , wherein the cooling holes of the second row are offset from the cooling holes of the first row such that each cooling hole in the second row is intermediate two closest ones of the cooling holes of the first row.

8. A gas turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the combustor, at least one of the turbine section or the combustor having an article that includes:
a silicon-containing ceramic wall having an external combustion gas path side and an internal side that borders a cooling air cavity, the external combustion gas path side having an associated combustion gas flow direction along the external combustion gas path side, and
an array of cooling holes extending through the silicon-containing ceramic wall and connecting the internal side with the external combustion gas path side, the cooling holes being oriented to discharge cooling air to the external combustion gas path side in a direction counter to the combustion gas flow direction, each of the cooling holes being comprised of a metering hole section of constant cross-sectional area and a surface breakout section that diverges from the metering hole section, the cooling holes being arranged in the array with a ligament length to cooling hole diameter of 2:1 to 8:1, the array including at least a first row of the cooling holes and a second row of the cooling holes, the surface breakout section of each of the cooling holes of the first row having a crescent geometry, and the surface breakout section of each of the cooling holes of the second row having a lobed geometry.

9. The gas turbine engine as recited in claim 8 , wherein the cooling holes of the second row are offset from the cooling holes of the first row such that each cooling hole in the second row is intermediate two closest ones of the cooling holes of the first row.

10. A method of mitigating silicon recession, the method comprising:
providing a gas turbine engine article in a gas turbine engine, the gas turbine engine article includes a silicon-containing ceramic wall that has an external combustion gas path side and an internal side that borders a cooling air cavity, and an array of cooling holes that extend through the silicon-containing ceramic wall and that connect the internal side with the external combustion gas path side, wherein there is a combustion gas flow across the external combustion gas path side along an associated combustion gas flow direction; and
emitting cooling air from the array of cooling holes in a direction counter to the combustion gas flow direction, the cooling air cooling the external combustion gas path side-, shielding the external combustion gas path side from the combustion gas flow, and locally reducing velocity of the combustion gas flow to mitigate silicon recession, each of the cooling holes being comprised of a metering hole section of constant cross-sectional area and a surface breakout section that diverges from the metering hole section, the cooling holes being arranged in the array with a ligament length to cooling hole diameter of 2:1 to 8:1, the array including at least a first row of the cooling holes and a second row of the cooling holes, the surface breakout section of each of the cooling holes of the first row has a crescent geometry, and the surface breakout section of each of the cooling holes of the second row has a lobed geometry.

Assignees

• Raytheon Tech Corp
• Rtx Corp

Inventors

• Martin Thomas J
• Srinivasan Gajawalli V
• Croteau Paul F
• Kennedy Matthew B

Classifications

• F23R3/005

  Combined with pressure or heat exchangers · CPC title

• F05D2300/2283

  of silicon · CPC title

• F05D2300/2261

  of silicon · CPC title

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F05D2240/81

  Cooled platforms · CPC title