Low profile thermally free blind liner hanger attachment for complex shapes

1. A hanger system for connecting components in a gas turbine engine, the hanger system comprising:

a first spaced component;

a T-bar having a shaft portion and a crossbar portion, wherein the shaft portion of the T-bar passes through an aperture in the first spaced component, and the shaft portion of the T-bar defines a desired distance;

a second spaced component arranged adjacent to the crossbar portion of the T-bar at the desired distance from the first spaced component; and

a bracket, wherein the bracket is coupled to the second spaced component independently of the T-bar and substantially encapsulates the crossbar portion of the; and a hanger washer layer arranged between the bracket and the crossbar portion of the T-bar that is a separate component from the bracket and the T-bar.

2. The hanger system of claim 1 , wherein the first spaced component and the second spaced component are separated by a distance determined by the length of the shaft portion of the T-bar.

3. The hanger system of claim 2 , wherein the first spaced component and the second spaced component are non-planar.

4. The hanger system of claim 1 , wherein the bracket includes a cutout larger than the crossbar portion of the T-bar.

5. The hanger system of claim 1 , wherein the bracket includes an indentation that is in direct contact with and is configured to capture the crossbar portion of the T-bar.

6. The hanger system of claim 1 , wherein a wear coating is applied to the second spaced component and the bracket.

7. The hanger system of claim 1 , wherein the bracket is coupled with the second spaced component by welding.

8. The hanger system of claim 1 , wherein the bracket is coupled with the second spaced component using a plurality of bolts.

9. The hanger system of claim 1 , wherein the shaft portion of the T-bar includes a threaded portion on the opposite distal end from the crossbar portion.

10. The hanger system of claim 9 , and further comprising a cap nut configured to screw on to the threading on the shaft portion of the T-bar.

11. The hanger system of claim 10 , and further comprising a washer arranged between and adjacent to both the cap nut and the first spaced component.

12. The hanger system of claim 1 , wherein the crossbar portion is positioned between the second spaced component and the hanger washer layer of the bracket.

13. The hanger system of claim 1 , wherein:

the bracket includes a cutout that is larger than the crossbar portion of the T-bar;

the hanger washer layer includes an indentation that is in direct contact with and is configured to capture the crossbar portion of the T-bar; and

the cutout is perpendicular to the indentation.

14. A method for connecting components in a gas turbine engine, the method comprising:

inserting a T-bar having a crossbar portion and a shaft portion through a first spaced component, the shaft portion having a threaded portion at a distal end opposite the crossbar portion, wherein the shaft portion of the T-bar defines a desired distance;

inserting a hanger washer layer with a slot portion and an indent portion into a bracket;

attaching the bracket to the second spaced component independently of the T-bar;

passing the crossbar portion of the T-bar into the bracket such that the crossbar portion of the T-bar is substantially encapsulated by the bracket;

passing the crossbar portion of the T-bar through the slot portion of the hanger washer layer, and rotating the T-bar such that the crossbar portion of the T-bar is captured by the indent portion; and

threading a nut onto the threaded portion of the T-bar to attach the T-bar to the first spaced component at the desired distance.

15. The method of claim 14 , and further comprising arranging a cap washer between the first spaced component and the nut.

16. The method of claim 14 , and further comprising applying a wear coating to at least one of the second spaced component, the insert layer, and the T-bar.

17. A method of installing a liner in a gas turbine engine, the method comprising:

inserting one of a plurality of hanger washer layers into one of a plurality of bracket components, wherein each of the plurality of hanger washer layers includes a slot portion and an indent portion;

affixing a plurality of bracket components to a liner;

inserting one of a plurality of T-bars into each of the plurality of bracket components such that the crossbar portion of the T-bar is substantially encapsulated by the bracket, each T-bar having a crossbar portion and a shaft portion, and the shaft portion having a threaded section and defining a desired distance;

passing the crossbar portion of each of the plurality of T-bars through the slot portion of the one of the hanger washer layers, and rotating each T-bar such that the crossbar portion of each T-bar is captured by the indent portion;

advancing the liner toward a structural component, such that the shaft portion of each of the T-bars pass through one of a plurality of apertures in the structural component; and

threading a nut onto the threaded section of each of the plurality of T-bars to attach each of the plurality of T-bars to the first spaced component at the desired distance.