Liner apparatus and method of inspecting and/or cleaning a liner annular region
A liner for a gas turbine engine is provided that includes an outer wall, an inner wall, and a plurality of structural elements disposed between the inner wall and the outer wall. The outer wall is spaced apart from the inner wall and is disposed radially outside of the inner wall. The outer wall and inner wall form an annular structure having a circumference, and an annular region disposed between the first interior surface of the outer wall and the second interior surface of the inner wall. Each of the structural elements is attached to the outer wall and the inner wall. The outer wall includes at least one inspection port extending through the outer wall configured for access to the annular region disposed between the first interior surface of the outer wall and the second interior surface of the inner wall.
1. A liner for a gas turbine engine, comprising:
an outer wall;
an inner wall;
wherein the outer wall is spaced apart from the inner wall and is disposed radially outside of the inner wall, the outer wall and inner wall forming an annular structure having a circumference, and an annular region disposed between a first interior surface of the outer wall and a second interior surface of the inner wall; and
a plurality of structural elements disposed between the inner wall and the outer wall, and each of the plurality of structural elements is attached to the outer wall and the inner wall;
wherein the outer wall includes at least one inspection port extending through the outer wall configured for access to the annular region disposed between the first interior surface of the outer wall and the second interior surface of the inner wall; and
wherein the plurality of structural elements extend around the circumference of the annular structure, and define a plurality of independent annular sub-regions, and each of the plurality of independent annular sub-regions includes the at least one said inspection port disposed in a portion of the outer wall of a respective annular sub-region of the plurality of annular sub-regions;
wherein the at least one inspection port in a respective one of the independent annular sub-regions is a plurality of said inspection ports, each said inspection port having a first area, and the collective first areas is a second area; and
the respective one of the independent annular sub-regions includes an outer wall portion and a plurality of first cooling apertures disposed in the outer wall portion;
wherein the plurality of first cooling apertures disposed within the outer wall portion have a collective third area, and the second area is less than ten percent (10%) of the third area.
2. The liner of claim 1 , wherein each first cooling aperture of the plurality of first cooling apertures has a cooling aperture area and wherein the first area is greater than the second aperture area of any first cooling aperture of the plurality of first cooling apertures.
3. The liner of claim 1 , wherein the at least one inspection port in each of the plurality of independent annular sub-regions is no more than four inspection ports.
4. The liner of claim 1 , wherein the second area is less than six percent (6%) of the third area.
5. The liner of claim 1 , wherein the second area is greater than two percent (2%) of the third area.
6. A gas turbine engine, comprising:
a fan section, a compressor section, a combustor section, and a turbine section; and
a liner disposed aft of the turbine section, the liner including:
an outer wall;
an inner wall;
wherein the outer wall is spaced apart from the inner wall and is disposed radially outside of the inner wall, the outer wall and inner wall forming an annular structure having a circumference, and an annular region disposed between a first interior surface of the outer wall and a second interior surface of the inner wall; and
a plurality of structural elements disposed between the inner wall and the outer wall, and each of the plurality of structural elements is attached to the outer wall and the inner wall;
wherein the outer wall includes at least one inspection port extending through the outer wall configured for access to the annular region disposed between the first interior surface of the outer wall and the second interior surface of the inner wall; and
wherein the plurality of structural elements extend around the circumference of the annular structure, and define a plurality of independent annular sub-regions, and each of the plurality of independent annular sub-regions includes the at least one inspection port disposed in a portion of the outer wall of a respective annular sub-region of the plurality of annular sub-regions;
wherein the at least one inspection port in a respective one of the independent annular sub-regions is a single said inspection port and has a first area; and
the respective one of the independent annular sub-regions includes an outer wall portion and a plurality of first cooling apertures disposed in the outer wall portion;
wherein the plurality of first cooling apertures disposed within the outer wall portion have a collective second area, and the first area is less than ten percent (10%) of the second area.
7. The engine of claim 6 , wherein each first cooling aperture of the plurality of first cooling apertures has a cooling aperture area and wherein the first area is greater than the cooling aperture area of any first cooling aperture of the plurality of first cooling apertures.