Ceramic matrix composite seal repair

1 . A gas turbine engine comprising:

a seal support including first and second spaced-apart support flanges, the first and second support flanges having at least one set of support flange pin holes; and

a ceramic matrix composite (CMC) seal including a radially inwardly-facing side and a radially outwardly-facing side, the radially outwardly-facing side having first and second spaced-apart seal flanges comprising two independent sets of support flange pin holes, each of the two independent sets of support flange pin holes including a first pair of aligned pin holes and a second pair of aligned pin holes that are circumferentially spaced from the first pair of aligned pin holes, wherein the CMC seal is affixable to the seal support by alignment of either one of the two independent sets of support flange pin holes with the at least one set of support flange pin holes and receipt of support pins there through.

2 . The gas turbine engine as recited in claim 1 , wherein the one of the two independent sets of support flange pin holes that is in receipt of the support pins includes insert bushings and the other one of the two independent sets of support flange pin holes that is not in receipt of the support pins excludes insert bushings.

3 . The gas turbine engine as recited in claim 1 , wherein the support flange pin holes are elongated slots.

4 . The gas turbine engine as recited in claim 3 , wherein the elongated slots span the two independent sets of support flange pin holes.

5 . The gas turbine engine as recited in claim 4 , further comprising bushings in the support flange pin holes, the bushings slidable in the elongated slots so as to be selectively alignable with either of the two independent sets of support flange pin holes.

6 . The gas turbine engine as recited in claim 4 , further comprising elongated palindrome bushings in the support flange pin holes, the palindrome bushings fitting forwards or backwards into the elongated slots so as to be selectively alignable with either of the two independent sets of support flange pin holes.

7 . The gas turbine engine as recited in claim 1 , wherein the support flange pin holes are of equal hole diameters, and the support flange pin holes are spaced apart from each other by at least one hole diameter.

8 . The gas turbine engine as recited in claim 1 , wherein the at least one set of support flange pin holes includes two independent sets of support flange pin holes, one of the two independent sets of support flange pin holes corresponding to one of the two independent sets of support flange pin holes and the other of the two independent sets of support flange pin holes corresponding to the other of the two independent sets of support flange pin holes.

9 . The gas turbine engine as recited in claim 1 , wherein the support flange pin holes are drilled holes.

10 . The gas turbine engine as recited in claim 1 , wherein the CMC seal includes SiC fibers disposed in a SiC matrix.

11 . The gas turbine engine as recited in claim 1 , further comprising

a compressor section;

a combustor in fluid communication with the compressor section; and

a turbine section in fluid communication with the combustor, the turbine section having blades disposed about a central axis of the gas turbine engine, and the CMC seal is disposed radially outwardly of the blades.

12 . The gas turbine engine as recited in claim 1 , wherein the two independent sets of support flange pin holes are independent such that the CMC seal is affixable with the support pins to the seal support by each of the two independent sets of support flange pin holes without reliance on the other of the two independent sets of support flange pin holes to affix the CMC seal.