T-head bolts or hollow flanged bushing with one thread or grooved end in a multi-liner arrangement
A gas turbine engine combustor panel assembly includes a shell defining an outer periphery of a combustion chamber with an outer skin with a first plurality of holes, a combustor panel including a first end, a second plurality of holes extending through an inner face to an inner void, to an outer face with a third plurality of holes to allow fluid flow from the first plurality of holes to the combustion chamber, a plurality of bolt holes, a second end with an internal combustion chamber section extending axially from a central axis and from a panel wall of the combustor panel. The assembly includes a sheet metal seal plate abutting the plurality of bolt holes and the interface, and a plurality of bolts extending along a central axis and interfacing with the plurality of bolt holes to connect the combustor panel and shell.
1. A gas turbine engine combustor panel assembly comprising:
a shell defining an outer periphery of a combustion chamber, the shell having an outer skin with a first plurality of holes;
a combustor panel, the combustor panel comprising:
a first end including a second plurality of holes on an inner face of the combustor panel extending through the inner face to an inner void then to an outer face of the combustor panel with a third plurality of holes configured to allow fluid flow from the first plurality of holes to the combustion chamber, and a plurality of bolt holes, wherein the inner void is a space defined by the inner face of the combustor panel, the outer face of the combustor panel and a plurality of bolts;
a second end comprising an internal combustion chamber section extending axially from a central axis and from a panel wall of the combustor panel;
a sheet metal seal plate abutting the plurality of bolt holes and an interface of the combustor panel; and
the plurality of bolts configured to extend along a central axis and interface with the plurality of bolt holes to connect the combustor panel to the shell.
2. The gas turbine engine combustor panel assembly of claim 1 , wherein the plurality of bolts are T-head bolts further comprising a T-head bolt head and a bolt body, and the plurality of bolt holes are oblong and configured to fit the T-head bolt head in a first orientation.
3. The gas turbine engine combustor panel assembly of claim 1 , wherein the plurality of bolts are flanged bushings further comprising a flanged head, a bolt shoulder, and a bolt body, and the plurality of bolt holes further comprise a key hole end larger than the flanged head, and a locking end smaller than the flanged head.
4. The gas turbine engine combustor panel assembly of claim 1 , further comprising raised elements on the inner face of the combustor panel configured to trap debris from fluid flow entering the second plurality of holes.
5. The gas turbine engine combustor panel assembly of claim 1 , wherein the combustor panel is made of a densified, laminated ceramic matrix composite (CMC) material.
6. The gas turbine engine combustor panel assembly of claim 5 , wherein the densified, laminated ceramic matrix composite material is composed of silicon carbide (SiC) fiber plies and a silicon carbide (SiC) matrix.
7. The gas turbine engine combustor panel assembly of claim 1 , wherein the combustor panel is actively cooled.
8. The gas turbine engine combustor panel assembly of claim 1 , wherein the second plurality of holes are oriented at an angle from the inner face of the combustor panel.
9. The gas turbine engine combustor panel assembly of claim 8 , further comprising raised elements on the inner face of the combustor panel and oriented at an angle from the inner face of the combustor panel.
10. The gas turbine engine combustor panel assembly of claim 1 , wherein an area of the inner void is configured to provide an air gap between the inner face and outer face of the combustor panel.
11. The gas turbine engine combustor panel assembly of claim 1 , wherein the first plurality of holes are oriented at an angle from an inner face of the outer skin.
12. The gas turbine engine combustor panel assembly of claim 1 , wherein cooling fluid is configured to be directed into the first plurality of holes.
13. A combustor panel arrangement for use in a combustor in a gas turbine engine, comprising:
a shell defining a combustion chamber, the shell having an outer skin with a first plurality of holes and further comprising:
a first combustor panel with a first end including a second plurality of holes on an inner face of the first combustor panel through to a first inner void then to an outer face of the first combustor panel, and configured to allow fluid flow from the first plurality of holes to the combustion chamber, a first plurality of bolt holes, and a second end comprising an internal combustion chamber section extending axially from a central axis and from a panel wall of the combustor panel, wherein the first inner void is a space defined by the inner face of the first combustor panel, the outer face of the first combustor panel and a first plurality of bolts;
a second combustor panel with a first end including a second plurality of holes on an inner face of the second combustor panel through to a second inner void then to an outer face of the second combustor panel, and configured to allow fluid flow from the first plurality of holes to the combustion chamber, a second plurality of bolt holes, and a second end comprising an internal combustion chamber section extending axially from a central axis and from a panel wall of the combustor panel, wherein the second inner void is a space defined by the inner face of the second combustor panel, the outer face of the second combustor panel and a second plurality of bolts;
the first plurality of bolts configured to extend along a central axis and interface with the first plurality of bolt holes to connect the first combustor panel to the shell;
a sheet metal seal plate abutting the plurality of bolt holes and an interface of at least one of the combustor panels; and
the second plurality of bolts configured to extend along a central axis and interface with the second plurality of bolt holes to connect the second combustor panel to the shell, wherein the panel wall of the first combustor panel and the panel wall of the second combustor panel abut to each other.
14. The combustor panel arrangement of claim 13 , wherein at least one of the combustor panels is made of a densified laminated ceramic matrix composite (CMC) material.
15. The combustor panel arrangement of claim 14 , wherein the densified, laminated ceramic matrix composite material is composed of silicon carbide (SiC) fiber plies and a silicon carbide (SiC) matrix.
16. The combustor panel arrangement of claim 13 , wherein at least one of the combustor panels is actively cooled.
17. The combustor panel arrangement of claim 13 , wherein the second plurality of holes of at least one of the combustor panels are oriented at an angle from the inner face of the combustor panel.
18. The combustor panel arrangement of claim 13 , wherein an area of the first inner void and an area of the second inner void are configured to provide an air gap between the inner face and outer face of the combustor panels that define the first inner void area and the second inner void area, respectively.
19. The combustor panel arrangement of claim 13 , wherein the second plurality of holes on the inner face of at least one of the combustor panels are oriented at an angle from an inner face of the outer skin.
20. The combustor panel arrangement of claim 13 , wherein cooling fluid is configured to be directed into the second plurality of holes on the inner face of at least one of the combustor panels.