Outlet guide vane assembly in gas turbine engine
An outlet guide vane assembly in a gas turbine engine is presented. The outlet guide vane assembly includes an inner shroud and an outlet guide vane having an inner platform. The inner shroud has a flange arranged at aft side that is bolted to a flange of the inner platform arranged at forward side. The inner shroud flange has a protrusion that engages a recess of the inner platform flange forming a form fit connection interface between the inner shroud and the outlet guide vane. The inner platform has shiplaps arranged at two circumferential sides that overlap shiplaps of an adjacent inner platform forming a form fit connection interface between adjacent outlet guide vanes. The outlet guide vane assembly includes a plurality of segments circumferentially arranged. Each segment includes a plurality of outlet guide vanes assembled to an inner shroud.
1. A gas turbine engine comprising:
a compressor section comprising an outlet guide vane assembly;
a mid-frame section arranged downstream of the compressor section, wherein the mid-frame section comprises an inner compressor exit diffuser, wherein a forward side of the inner compressor exit diffuser interfaces with the outlet guide vane assembly; and
a turbine section arranged downstream of the mid-frame section,
wherein the outlet guide vane assembly comprises:
an inner shroud comprising a circular shape and extending axially, and
an outlet guide vane comprising an airfoil radially extending between an airfoil root and an inner platform,
wherein the inner shroud comprises a flange arranged at an aft side and extending radially downwardly,
wherein the inner platform comprises a flange arranged at a forward side and extending radially downwardly, and
wherein the outlet guide vane is connected to the inner shroud at an interface of the inner platform flange and the inner shroud flange such that a radial clearance exists between a tip of a last stage compressor vane and the inner shroud.
2. The gas turbine engine as claimed in claim 1 , wherein the outlet guide vane is connected to the inner shroud using a bolt extending axially in the inner platform flange and the inner shroud flange.
3. The gas turbine engine as claimed in claim 1 , wherein the inner shroud flange comprises a protrusion arranged at an aft side of the inner shroud flange, wherein the inner platform flange comprises a recess arranged at a forward side of the inner platform flange configured to engage the protrusion, and wherein the protrusion and the recess are configured to form a form fit connection interface between the inner shroud and the outlet guide vane.
4. The gas turbine engine as claimed in claim 1 , wherein the outlet guide vane assembly comprises an outlet guide vane assembly segment, and wherein the outlet guide vane assembly segment comprises a plurality of outlet guide vanes connected to the inner shroud.
5. The gas turbine engine as claimed in claim 4 , wherein the outlet guide vane assembly comprises a plurality of outlet guide vane assembly segments arranged circumferentially.
6. The gas turbine engine as claimed in claim 4 , wherein the inner platform comprises shiplaps arranged at two circumferential sides, and wherein the shiplaps are configured to form a form fit connection interface between adjacent outlet guide vanes.
7. The gas turbine engine as claimed in claim 1 , wherein the inner compressor exit diffusor comprises a recess to receive the connected inner platform flange and the inner shroud flange in the recess.
8. An outlet guide vane assembly in a gas turbine engine comprising:
an inner shroud comprising a circular shape and extending axially, and
an outlet guide vane comprising an airfoil radially extending between an airfoil root and an inner platform,
wherein the inner shroud comprises a flange arranged at an aft side and extending radially downwardly,
wherein the inner platform comprises a flange arranged at a forward side and extending radially downwardly, and
wherein the outlet guide vane is connected to the inner shroud at an interface of the inner platform flange and the inner shroud flange such that a radial clearance exists between a tip of a last stage compressor vane and the inner shroud.
9. The outlet guide vane assembly as claimed in claim 8 , wherein the outlet guide vane is connected to the inner shroud using a bolt extending axially in the inner platform flange and the inner shroud flange.
10. The outlet guide vane assembly as claimed in claim 8 , wherein the inner shroud flange comprises a protrusion arranged at an aft side of the inner shroud flange, wherein the inner platform flange comprises a recess arranged at a forward side of the inner platform flange configured to engage the protrusion, and wherein the protrusion and the recess are configured to form a form fit connection interface between the inner shroud and the outlet guide vane.
11. The outlet guide vane assembly as claimed in claim 8 , wherein the outlet guide vane assembly comprises an outlet guide vane assembly segment, and wherein the outlet guide vane assembly segment comprises a plurality of outlet guide vanes connected to the inner shroud.
12. The outlet guide vane assembly as claimed in claim 11 , wherein the outlet guide vane assembly comprises a plurality of outlet guide vane assembly segments arranged circumferentially.
13. The outlet guide vane assembly as claimed in claim 11 , wherein the inner platform comprises shiplaps arranged at two circumferential sides, and wherein the shiplaps are configured to form a form fit connection interface between adjacent outlet guide vanes.
14. A method for assembling an outlet guide vane assembly in a gas turbine engine, wherein the gas turbine engine comprises an inner an inner compressor exit diffuser, wherein a forward side of the inner compressor exit diffuser interfaces the outlet guide vane assembly, the method comprising:
providing an inner shroud comprising a circular shape and extending axially, wherein the inner shroud comprises a flange arranged at an aft side and extending radially downwardly, and
providing an outlet guide vane comprising an airfoil radially extending between an airfoil root and an inner platform, wherein the inner platform comprises a flange arranged at a forward side and extending radially downwardly, and
connecting the outlet guide vane to the inner shroud at an interface of the inner platform flange and the inner shroud flange such that a radial clearance exists between a tip of a last stage compressor vane and the inner shroud.
15. The method as claimed in claim 14 , wherein the outlet guide vane is connected to the inner shroud by axially extending a bolt in the inner platform flange and the inner shroud flange.
16. The method as claimed in claim 14 , wherein the inner shroud flange comprises a protrusion arranged at an aft side of the inner shroud flange, wherein the inner platform flange comprises a recess arranged at a forward side of the inner platform flange, and wherein the method further comprises forming a form fit connection interface between the inner shroud and the outlet guide vane by engaging the protrusion and the recess.
17. The method as claimed in claim 14 , further comprising forming an outlet guide vane assembly segment comprising a plurality of outlet guide vanes connected to the inner shroud.
18. The method as claimed in claim 17 , further comprising forming a plurality of outlet guide vane assembly segments arranged circumferentially.
19. The method as claimed in claim 17 , wherein the inner platform comprises shiplaps arranged at two circumferential sides, and wherein the method further comprises forming a form fit connection interface between adjacent outlet guide vanes at the shiplaps.
20. The method as claimed in claim 14 , wherein the inner compressor exit diffusor comprises a recess, and wherein the method further comprises receiving the connected inner platform flange and the inner shroud flange in the recess and sliding the connected inner platform flange and the inner shroud flange along the recess.