Retention clip for a blade outer air seal
One exemplary embodiment of this disclosure relates to a system having a static segment with a circumferentially extending slot. The system further includes a retention clip partially received in the slot, and partially contacting a circumferential end of the static segment.
1. A system, comprising:
a static segment including a fore slot and an aft slot, each of the fore slot and the aft slot extending in a circumferential direction relative to an engine central longitudinal axis;
a first retention clip at least partially received in the fore slot;
a second retention clip at least partially received in the aft slot, wherein the first and second retention clips abut opposite circumferential ends of the static segment, and wherein each of the first and second retention clips exhibits an overall length less than a circumferential length of the static segment;
a support structure, wherein the first and second retention clips each include a main body portion in contact with the support structure; and
wherein a groove is formed in a radially inner-most surface of each of the main body portions, and wherein the support structure includes arms received in a corresponding one of the grooves.
2. The system as recited in claim 1 , wherein the first and second retention clips each include a first projection extending from a respective main body portion and received in a respective one of the fore and aft slots.
3. The system as recited in claim 2 , wherein the first and second retention clips each include a second projection extending further from the main body portion than the first projection and abutting a respective circumferential end of the static segment.
4. The system as recited in claim 1 , wherein one of the grooves and the arms includes a convex surface.
5. The system as recited in claim 1 , wherein the support structure includes a flange, and wherein a face of each of the main body portions abuts the flange.
6. The system as recited in claim 1 , wherein the main body portions each include a notch formed in a radially outer surface thereof, and wherein the support structure includes a tab received in the notch.
7. The system as recited in claim 1 , wherein the support structure provides channels, and wherein the main body portions are sized to correspond to the size of the channels.
8. The system as recited in claim 1 , wherein the first and second retention clips are made of a material selected from the group consisting of (1) a ceramic material, (2) a nickel-based alloy, and (3) a cobalt-based alloy.
9. The system as recited in claim 1 , wherein the static segment is a blade outer air seal (BOAS) segment.
10. The system as recited in claim 1 , wherein:
the static segment includes a radially-facing trough between the fore slot and the aft slot, and
the first and second retention clips are not arranged in the trough.
11. A gas turbine engine, comprising:
a compressor section, a combustor section, and a turbine section;
an engine case provided adjacent at least one of the compressor section and the turbine section;
a blade outer air seal (BOAS segment) having a circumferentially extending slot facing in one of a fore direction and an aft direction relative to a central longitudinal axis of the gas turbine engine; and
a retention clip provided between the BOAS segment and the engine case, the retention clip partially received in the slot and partially contacting a circumferential end of the BOAS segment,
wherein the retention clip includes a first projection extending from a main body portion, the first projection received in the slot, and wherein the retention clip includes a second projection extending further from the main body portion than the first projection, the second projection abutting the circumferential end of the BOAS segment, and wherein an overall length of the retention clip is less than a circumferential length of the BOAS segment.