GAS TURBINE ENGINE INNER CASE WITH NON-INTEGRAL VANES
A gas turbine engine includes a circumferential array of vanes slidably supported in an inner case shroud segment. Multiple segments are secured to one another to provide an annular engine static structure section. The inner case shroud segment and the vanes have different material properties than one another.
1 . A gas turbine engine comprising:
a circumferential array of vanes slidably supported in an inner case shroud segment, multiple segments secured to one another to provide an annular engine static structure section, the inner case shroud segment and the vanes having different material properties than one another.
2 . The gas turbine engine according to claim 1 , wherein the annular engine static structure section is a compressor section.
3 . The gas turbine engine according to claim 2 , wherein the compressor section is a high pressure compressor section.
4 . The gas turbine engine according to claim 1 , wherein the inner case shroud segment includes at least two rows of vanes axially spaced from one another.
5 . The gas turbine engine according to claim 4 , wherein the two rows of vanes have different properties than one another.
6 . The gas turbine engine according to claim 5 , wherein inner case shroud segment includes an arcuate groove arranged axially between the two rows of vanes, and a material is adhered to the inner case shroud segment within the arcuate groove.
7 . The gas turbine engine according to claim 5 , wherein an upstream row of vanes includes a lower strength nickel alloy than a downstream row of vanes.
8 . The gas turbine engine according to claim 1 , wherein the annular inner case shroud includes an arcuate slot, and the vanes include hooks received in the arcuate slots.
9 . The gas turbine engine according to claim 7 , comprising a damper or a wear liner arranged in the annular slot between the hooks and the inner case shroud segment.
10 . The gas turbine engine according to claim 1 , wherein the different material properties include different coefficients of thermal expansion.
11 . The gas turbine engine according to claim 1 , wherein the different material properties include different fatigue strengths.
12 . The gas turbine engine according to claim 1 , wherein the different material properties include different manufacturing processes, and wherein the inner case shroud segment is cast and the vanes are forged.
13 . A compressor section of a gas turbine engine, comprising:
a circumferential array of vanes slidably supported in an inner case shroud segment, multiple segments secured to one another to provide an annular engine static structure section, the inner case shroud segment and the vanes having different material properties than one another, the inner case shroud segment includes at least two rows of vanes axially spaced from one another.
14 . The compressor section according to claim 13 , wherein the two rows of vanes have different properties than one another.
15 . The compressor section according to claim 14 , wherein the two rows of vanes have different properties than one another.
16 . The compressor section according to claim 15 , wherein inner case shroud segment includes an arcuate groove arranged axially between the two rows of vanes, and a material is adhered to the inner case shroud segment within the arcuate groove.
17 . The compressor section according to claim 14 , wherein an upstream row of vanes includes a lower strength nickel alloy than a downstream row of vanes.
18 . The compressor section according to claim 13 , wherein the annular inner case shroud includes an arcuate slot, and the vanes include hooks received in the arcuate slots, and a damper is arranged in the annular slot between the hooks and the inner case shroud segment.
19 . The compressor section according to claim 13 , wherein the compressor section is a high pressure compressor section.
20 . The compressor section according to claim 13 , wherein the different material properties include at least one of different coefficients of thermal expansion, different material, different fatigue strengths, or different manufacturing processes.