Heat shield insert
An insert is disposable between an exterior surface of an annular body and an annular flange and between a support wall supportive of the annular flange and surface features of the exterior surface. The insert includes a forward section sized to fit between and to extend along respective arc-segments of the exterior surface and the annular flange and an aft section. The forward section includes a first end wall abuttable with the support wall, a second end wall and inner and outer diameter surfaces that extend between the first and second end walls for abutment with the exterior surface and the annular flange, respectively. The aft section extends from the second end wall to be engageable with the surface features.
1. A weight-balanced rotor assembly of a gas turbine engine, comprising:
an annular exterior surface comprising surface features comprising a circumferential array of bifurcated tabs defining a circumferential array of tab grooves and a split retaining ring securable between the bifurcated tabs of the circumferential array;
first and second annular walls;
first and second annular flanges supported on the first and second annular walls, respectively;
an annular heat shield fittable between the first and second flanges to surround an intervening section of the exterior surface that includes the surface features; and
an insert comprising:
a forward section abuttable with the first annular wall and sized to fit between the exterior surface and the first flange; and
an aft section extending from the forward section to fit in a corresponding one of the tab grooves of the surface features to axially and circumferentially lock the insert,
wherein an aft face of the aft section is engageable with the split retaining ring.
2. The weight-balanced rotor assembly according to claim 1 , wherein the exterior surface comprises an interface of high pressure compressor and turbine sections of a gas turbine engine.
3. The weight-balanced rotor assembly according to claim 1 , further comprising a forward exterior surface section which smoothly and continuously extends into the first annular wall.
4. The weight-balanced rotor assembly according to claim 1 , wherein the forward section comprises:
a first end wall abuttable with the first annular wall;
a second end wall; and
inner and outer diameter surfaces that extend between the first and second end walls for abutment with the exterior surface and the first flange, respectively.
5. The weight-balanced rotor assembly according to claim 4 , wherein a thickness of the outer diameter surface is less than a length of the first flange.
6. The weight-balanced rotor assembly according to claim 5 , wherein:
a forward edge of the heat shield is configured to fit between the first flange and a forward portion of the aft section, and
a first face of the heat shield is configured to face the second end wall.
7. The weight-balanced rotor assembly according to claim 4 , wherein the inner and outer diameter surfaces have curvatures similar to those of the exterior surface and the first flange.
8. The weight-balanced rotor assembly according to claim 1 , wherein:
the forward section is sized to extend along respective arc-segments of the exterior surface and the first flange, and
the aft section comprises an elongate body which extends along an arc-segment of the forward section.
9. The weight-balanced rotor assembly according to claim 1 , wherein the insert is provided as one or more inserts each having one of two or more weights.
10. The weight-balanced rotor assembly according to claim 9 , wherein the forward section of each of the one or more inserts is formed to define one or more cutouts.
11. A method of weight-balancing a rotor assembly of a gas turbine engine without generating windage, the method comprising:
assembling the rotor assembly to comprise an annular exterior surface comprising surface features comprising a circumferential array of bifurcated tabs defining a circumferential array of tab grooves and a split retaining ring securable between the bifurcated tabs of the circumferential array, first and second annular walls and first and second annular flanges supported on the first and second annular walls, respectively;
spinning the rotor assembly about a rotational axis to identify an unbalanced condition; and
positioning one or more inserts on the rotor assembly to correct the unbalanced condition, each of the one or more inserts comprising a forward section abuttable with the first annular wall and sized to fit between the exterior surface and the first flange and an aft section extending from the forward section to fit into a corresponding one of the tab grooves of the surface features to axially and circumferentially lock the insert wherein an aft face of the aft section is engageable with the split retaining ring.
12. The method according to claim 11 , wherein the assembling further comprises forming a forward exterior surface section which smoothly and continuously extends into the first annular wall.
13. The method according to claim 11 , wherein:
each of the one or more inserts has one of two or more weights, and
the method further comprises selecting each of the one or more inserts in accordance with the one of the two or more weights thereof.