Combustor panels for gas turbine engines
Methods for manufacturing combustor panels of gas turbine engines and combustor panels are described. The methods include defining a particle deposit near-steady state for at least a portion of a combustor panel, the particle deposit near-steady state representative of a build-up of particles on the at least a portion of the combustor panel during use, generating a template based on the defined particle deposit near-steady state, wherein the template includes one or more augmentation elements based on the representative of build-up of particles, and forming a combustor panel based on the template, wherein the formed combustor panel includes one or more augmentation elements defined in the template.
1. A method of manufacturing a combustor panel of a gas turbine engine comprising:
scanning and obtaining a particle deposit near-steady state for a plurality of pre-used combustor panels, the particle deposit near-steady state representative of a build-up of particles on at least a portion of each pre-used combustor panel during use, wherein the scanning comprises at least one of CT scanning, topology scanning, and 3D scanning;
averaging the obtained particle deposit near-steady state of the plurality of pre-used combustor panels;
generating a template based on the averaged particle deposit near-steady state, wherein the template includes one or more augmentation elements based on the representative of build-up of particles; and
forming a combustor panel based on the template, wherein the formed combustor panel includes one or more augmentation elements defined in the template.
2. The method of claim 1 , wherein at least one combustor panel of the plurality of pre-used combustor panels is obtained from a test rig including a test combustor panel, wherein the test combustor panel is one of the pre-used combustor panels.
3. The method of claim 1 , wherein at least one pre-used combustor panel is obtained from a gas turbine engine wherein the obtained combustor panel was used in a combustor of the gas turbine engine during use.
4. The method of claim 1 , wherein the augmentation elements are integrally formed with the formed combustor panel and formed of the same material as the formed combustor panel.
5. The method of claim 1 , wherein the formed combustor panel is formed using an additive manufacturing process.
6. The method of claim 1 , wherein the one or more augmentation elements comprise one or more of dune shapes and mound shapes.
7. The method of claim 1 , wherein the formed combustor panel is formed using a casting process.
8. The method of claim 1 , wherein the particle deposit near-steady state is a state of particle aggregation on a cold side of the combustor panel during operation in which no additional particle aggregation occurs.
9. The method of claim 1 , wherein the averaging comprises a stacking operation of multiple scans of different pre-used combustor panels.
10. The method of claim 1 , wherein the averaging comprises a defining a normal distribution of the particle deposit near-steady state of the plurality of pre-used combustor panels.
11. The method of claim 1 , wherein the averaging comprises performing a weighted averaging of particle deposit near-steady state features.
12. The method of claim 1 , wherein the plurality of pre-used combustor panels are each manufactured to a same specification prior to use.
13. The method of claim 1 , wherein the plurality of pre-used combustor panels are sourced from at least two different sources.
14. The method of claim 13 , wherein the different sources include at least one of gas turbine engines, test rigs, test combustor sections, or combustor panel simulation.
15. The method of claim 1 , wherein each pre-used combustor panel is obtained from the same gas turbine engine.
16. The method of claim 1 , wherein at least one pre-used combustor panel is obtained from a first gas turbine engine and at least one pre-used combustor panel is obtained from a second gas turbine engine different from the first gas turbine engine.
17. A method of manufacturing a combustor panel of a gas turbine engine comprising:
obtaining a particle deposit near-steady state for a plurality of pre-used combustor panels, the particle deposit near-steady state representative of a build-up of particles on at least a portion of each pre-used combustor panel during use;
averaging the obtained particle deposit near-steady state of the plurality of pre-used combustor panels, wherein the averaging comprises a defining a normal distribution of the particle deposit near-steady state of the plurality of pre-used combustor panels and wherein variations of greater than 2 sigma of the particle deposit near-steady state from the plurality of pre-used combustor panels are ignored in the normal distribution;
generating a template based on the averaged particle deposit near-steady state, wherein the template includes one or more augmentation elements based on the representative of build-up of particles; and
forming a combustor panel based on the template, wherein the formed combustor panel includes one or more augmentation elements defined in the template.
18. The method of claim 17 , wherein at least one combustor panel of the plurality of pre-used combustor panels is obtained from at least one of:
a test rig including a test combustor panel, wherein the test combustor panel is one of the pre-used combustor panels, and
a gas turbine engine wherein the obtained combustor panel was used in a combustor of the gas turbine engine during use.
19. The method of claim 17 , wherein the augmentation elements are integrally formed with the formed combustor panel and formed of the same material as the formed combustor panel.
20. The method of claim 17 , wherein the averaging comprises at least one of:
a stacking operation of multiple scans of different pre-used combustor panels, and
a weighted averaging of particle deposit near-steady state features.