Segmented stator assembly
A stator assembly for a gas turbine engine includes an arcuate outer shroud, an arcuate inner shroud radially spaced from the outer shroud and a plurality of stator vanes extending from the outer shroud to the inner shroud. A volume of potting is located at the inner shroud and at the outer shroud to retain the plurality of stator vanes thereat. A stator and case assembly includes a case defining a working fluid flowpath and a stator assembly positioned at the case. The stator assembly includes a plurality of stator segments arranged circumferentially about an engine axis, each stator segment including an arcuate outer shroud secured to the case, an arcuate inner shroud, and a plurality of stator vanes extending from the outer to inner shroud. A volume of potting is located at the inner shroud and at the outer shroud to retain the plurality of stator vanes thereat.
1. A stator assembly for a gas turbine engine, comprising:
an arcuate outer shroud;
an arcuate inner shroud radially spaced from the outer shroud;
a plurality of stator vanes extending from the outer shroud to the inner shroud, each of the stator vanes including:
an airfoil portion having a first streamwise width;
an outer leg extending radially outwardly from the airfoil portion, the outer leg having a second streamwise width less than the first streamwise width; and
an inner leg extending radially inwardly from the airfoil portion, the inner leg having a third streamwise width less than the first streamwise width; and
a volume of potting disposed at the inner shroud and at the outer shroud to retain the plurality of stator vanes thereat;
the arcuate outer shroud including:
an axial forward wall;
an axial aft wall; and
a plurality of outer shroud openings in the outer shroud between the axial forward wall and the axial aft wall;
wherein each outer shroud opening of the plurality of outer shroud openings receives a stator vane of the plurality of stator vanes therein;
wherein the axial forward wall and the axial aft wall define an outer shroud channel therebetween, the volume of potting at least partially filling the outer shroud channel wherein the plurality of stator vanes are formed from a composite material.
2. The stator assembly of claim 1 , wherein:
the outer leg is installed into an outer shroud opening of the plurality of outer shroud openings; and
the inner leg is installed into an inner shroud opening in the inner shroud.
3. The stator assembly of claim 2 , wherein the potting comprises:
an outer grommet disposed at each outer shroud opening; and
an inner grommet disposed at each inner shroud opening to retain each stator vane thereat.
4. The stator assembly of claim 1 , wherein each stator vane further includes:
an outer leg opening; and
an inner leg opening;
wherein a retention element extends through each inner leg opening and/or each outer leg opening to secondarily retain the plurality of stator vanes at the inner shroud and/or the outer shroud.
5. The stator assembly of claim 1 , wherein the volume of potting at least partially fills an inner shroud channel.
6. The stator assembly of claim 1 , wherein the plurality of stator vanes is formed from a first material and the outer shroud and/or the inner shroud are formed from a second material different than the first material.
7. The stator assembly of claim 1 , wherein the potting is a rubber material.
8. A stator and case assembly for a gas turbine engine comprising:
a case defining a working fluid flowpath for the gas turbine engine; and
a stator assembly disposed at the case, the stator assembly including a plurality of stator segments arranged circumferentially about an engine axis, each stator segment including:
an arcuate outer shroud secured to the case;
an arcuate inner shroud radially spaced from the outer shroud;
a plurality of stator vanes extending from the outer shroud to the inner shroud, each of the stator vanes including:
an airfoil portion having a first streamwise width;
an outer leg extending radially outwardly from the airfoil portion, the outer leg having a second streamwise width less than the first streamwise width; and
an inner leg extending radially inwardly from the airfoil portion, the inner leg having a third streamwise width less than the first streamwise width; and
a volume of potting disposed at the inner shroud and at the outer shroud to retain the plurality of stator vanes thereat;
the arcuate outer shroud including:
an axial forward wall;
an axial aft wall; and
a plurality of outer shroud openings in the outer shroud between the axial forward wall and the axial aft wall;
wherein each outer shroud opening of the plurality of outer shroud openings receives a stator vane of the plurality of stator vanes therein;
wherein the axial forward wall and the axial aft wall define an outer shroud channel therebetween, the volume of potting at least partially filling the outer shroud channel wherein the plurality of stator vanes are formed from a composite material.
9. The stator and case assembly of claim 8 , wherein:
the outer leg is installed into an outer shroud opening of the plurality of outer shroud openings; and
the inner leg is installed into an inner shroud opening in the inner shroud.
10. The stator and case assembly of claim 9 , wherein the potting comprises:
an outer grommet disposed at each outer shroud opening; and
an inner grommet disposed at each inner shroud opening to retain each stator vane thereat.
11. The stator and case assembly of claim 8 , wherein each stator vane further includes:
an outer leg opening; and
an inner leg opening;
wherein a retention element extends through each inner leg opening and/or each outer leg opening to secondarily retain the plurality of stator vanes at the inner shroud and/or the outer shroud.
12. The stator and case assembly of claim 8 , wherein the volume of potting at least partially fills an inner shroud channel.
13. The stator and case assembly of claim 8 , wherein the plurality of stator vanes is formed from a first material and the outer shroud and/or the inner shroud are formed from a second material different than the first material.
14. The stator and case assembly of claim 8 , wherein the potting is a rubber material.
15. A gas turbine engine, comprising:
a combustor; and
a stator and case assembly in fluid communication with the combustor, the stator and case assembly including:
a case defining a working fluid flowpath for the gas turbine engine; and
a stator assembly disposed at the case, the stator assembly including a plurality of stator segments arranged circumferentially about an engine axis, each stator segment including:
an arcuate outer shroud secured to the case;
an arcuate inner shroud radially spaced from the outer shroud;
a plurality of stator vanes extending from the outer shroud to the inner shroud, each of the stator vanes including:
an airfoil portion having a first streamwise width;
an outer leg extending radially outwardly from the airfoil portion, the outer leg having a second streamwise width less than the first streamwise width; and
an inner leg extending radially inwardly from the airfoil portion, the inner leg having a third streamwise width less than the first streamwise width; and
a volume of potting disposed at the inner shroud and at the outer shroud to retain the plurality of stator vanes thereat;
the arcuate outer shroud including:
an axial forward wall;
an axial aft wall; and
a plurality of outer shroud openings in the outer shroud between the axial forward wall and the axial aft wall;
wherein each outer shroud opening of the plurality of outer shroud openings receives a stator vane of the plurality of stator vanes therein;
wherein the axial forward wall and the axial aft wall define an outer shroud channel therebetween, the volume of potting at least partially filling the outer shroud channel wherein the plurality of stator vanes are formed from a composite material.