Combustor panel mounting systems and methods
Combustors of gas turbine engines having a combustor shell having a first end and a second end opposite the first end, a first securing element positioned at the first end of the combustor shell, a second securing element positioned at the second end of the combustor shell, a plurality of high temperature material panels fixedly secured by the first securing element at the first end and the second securing element at the second, wherein a panel gap is formed between edges of adjacent high temperature material panels of the plurality of high temperature material panels, and a seal divider extending from the first end to the second end and positioned on the combustor shell and arranged to seal the panel gap between adjacent first and second high temperature material panels.
1. A combustor of a gas turbine engine comprising:
a combustor shell having a first end and a second end opposite the first end;
a first securing element positioned at the first end of the combustor shell;
a second securing element positioned at the second end of the combustor shell;
a plurality of high temperature material panels fixedly secured by the first securing element at the first end and the second securing element at the second, wherein a panel gap is formed between edges of adjacent high temperature material panels of the plurality of high temperature material panels; and
a seal divider extending from the first end to the second end and positioned on the combustor shell and arranged to seal the panel gap between adjacent first and second high temperature material panels, wherein the seal divider biases the first and second high temperature material panels into secure engagement with the first and second securing elements.
2. The combustor of claim 1 , further comprising a plurality of biasing elements located away from the edges of the high temperature material panels, the biasing elements biasing the high temperature material panels to secure engagement with the first and second securing elements.
3. The combustor of claim 2 , wherein the biasing elements are integrally formed from the combustor shell.
4. The combustor of claim 2 , wherein the combustor shell includes at least one cooling hole located proximate each biasing element to provide cooling thereto.
5. The combustor of claim 1 , wherein the seal divider biases the first and second high temperature material panels into secure engagement with the first and second securing elements.
6. The combustor of claim 1 , wherein the combustor shell includes at least one cooling hole located proximate the seal divider to provide cooling thereto.
7. The combustor of claim 1 , wherein the high temperature material panels are formed from non-ductile materials.
8. The combustor of claim 1 , wherein the high temperature material panels are formed from ceramic matrix composite.
9. The combustor of claim 1 , wherein the first securing element is integrally formed with the combustor shell.
10. The combustor of claim 1 , wherein the combustor shell includes at least one cooling hole proximate the first securing element to provide cooling thereto.
11. The combustor of claim 1 , wherein the second securing element clips or slides into place to engage with both the high temperature material panels and the combustor shell at the second end.
12. A method of securing high temperature material panels to a combustor shell of a gas turbine engine, the method comprising:
engaging a first high temperature material panel to a first securing element positioned at a first end of a combustor shell;
positioning and engaging a second high temperature material panel to the first securing element at the first end and adjacent the first high temperature material panel;
locating a seal divider in a panel gap between the first and second high temperature material panels; and
securely engaging the first and second high temperature material panels to the combustor shell with a second securing element at a second end of the combustor shell wherein the seal divider biases the first and second high temperature material panels into secure engagement with the first and second securing elements.
13. The method of claim 12 , further comprising positioning a plurality of biasing elements located away from the edges of the high temperature material panels, the biasing elements biasing the high temperature material panels into secure engagement with the first and second securing elements.
14. The method of claim 13 , wherein the biasing elements are integrally formed from the combustor shell or fixedly attached to the combustor shell.
15. The method of claim 12 , wherein the high temperature material panels are formed from non-ductile materials.
16. The method of claim 12 , wherein the high temperature material panels are formed from ceramic matrix composite.
17. The method of claim 12 , further comprising integrally forming the first securing element with the combustor shell.
18. The method of claim 12 , wherein the second securing element clips or slides into place to engage with both the high temperature material panels and the combustor shell at the second end.