Combustor-vane interface feather seal
A gas turbine engine includes a combustor disposed about an engine central axis and a circumferential row of vanes adjacent an exit region of the combustor. The combustor includes a combustor wall and a combustion chamber. The combustor wall has a lip at the exit region. Each vane includes a platform and an airfoil section extending from the platform. The forward edges of the platforms are adjacent the lip of the combustor wall. The lip defines a first annular slot and the forward edges of the vanes collectively define a second annular slot. The first and second annular slots together define an annular seal slot. An annular feather seal is entrapped in the annular seal slot between the combustor wall and the platform.
1 . A gas turbine engine comprising:
a combustor disposed about an engine central axis and including a combustor wall and a combustion chamber, the combustor wall having a lip at an exit region of the combustion chamber;
a circumferential row of vanes adjacent the exit region, each said vane including a platform and an airfoil section extending from the platform, the platform defining forward and trailing edges and first and second circumferential side edges joining the forward and trailing edges, the forward edge being adjacent the lip of the combustor wall,
the lip defining a first annular slot and the forward edges collectively defining a second annular slot, the first and second annular slots together defining an annular seal slot; and
an annular feather seal entrapped in the annular seal slot between the combustor wall and the platform.
2 . The gas turbine engine as recited in claim 1 , wherein the platform is radially inwards of the airfoil section.
3 . The gas turbine engine as recited in claim 1 , wherein the lip of the combustor abuts the leading edge of the platform.
4 . The gas turbine engine as recited in claim 1 , wherein the annular feather seal is a split ring.
5 . The gas turbine engine as recited in claim 4 , wherein the split ring has overlapping ends.
6 . The gas turbine engine as recited in claim 1 , wherein the first annular slot is defined by radially inner and outer walls of the combustor wall and the second annular slot is defined by radially inner and outer walls of the platform.
7 . The gas turbine engine as recited in claim 6 , wherein the radially outer wall of the first annular slot and the radially outer wall of the second annular slot abut, and the radially inner wall of the first annular slot and the radially inner wall of the second slot are axially spaced apart such that there is a gap there between.
8 . The gas turbine engine as recited in claim 6 , wherein at least one of the radially inner wall of the first annular slot or the radially inner wall of the second annular slot is scalloped.
9 . The gas turbine engine as recited in claim 1 , wherein the seal slot is radially thicker than the annular feather seal.
10 . A gas turbine engine comprising:
a combustor disposed about an engine central axis and including a combustor wall and a combustion chamber, the combustor wall having a lip at an exit region of the combustion chamber;
a vane adjacent the exit region, the vane including a platform and an airfoil section extending along a radial axis from the platform, the platform defining forward and trailing edges and first and second circumferential side edges joining the forward and trailing edges,
the vane having rotational play about the radial axis under aerodynamic loads such that the vane moves relative to the combustor between a seated state in which the forward edge abuts the lip of the combustor wall and an unseated state in which there is a divergent gap between the forward edge and the lip of the combustor,
the lip defining a first slot extending circumferentially and the forward edge defining a second slot extending circumferentially, the first and second slots together defining a seal slot; and
an annular feather seal extending in the seal slot, the annular feather seal being wider than the divergent gap to maintain sealing when the vane is in the unseated state.
11 . The gas turbine engine as recited in claim 10 , wherein the first side of the airfoil section is a suction side, the second side of the airfoil section is a pressure side, the second circumferential side of the platform is located to the second side of the airfoil section, and the divergent gap diverges toward the second circumferential side.
12 . The gas turbine engine as recited in claim 10 , wherein the annular feather seal is a split ring.
13 . The gas turbine engine as recited in claim 12 , wherein the split ring has overlapping ends.
14 . The gas turbine engine as recited in claim 10 , wherein the first slot is defined by first radially inner and outer walls of the combustor wall and the second slot is defined by radially inner and outer walls of the platform.
15 . The gas turbine engine as recited in claim 14 , wherein at least one of the radially inner wall of the first annular slot or the radially inner wall of the second annular slot is scalloped.
16 . The gas turbine engine as recited in claim 14 , wherein the radially outer wall of the first annular slot and the radially outer wall of the second annular slot abut, and the radially inner wall of the first annular slot and the radially inner wall of the second slot are axially spaced apart such that there is a gap there between.
17 . The gas turbine engine as recited in claim 10 , wherein the seal slot is radially thicker than the annular feather seal.
18 . An airfoil comprising:
a vane including a platform and an airfoil section extending from the platform, the platform defining forward and trailing edges and first and second circumferential side edges joining the forward and trailing edges,
the forward edge including a bearing surface for abutting a lip of a combustor wall to provide a seal across an interface between the platform and the combustor wall, and
the forward edge defining a slot arc segment for receiving a portion of an annular feather seal.
19 . The airfoil as recited in claim 18 , wherein the platform is radially inwards of the airfoil section.
20 . The airfoil as recited in claim 18 , wherein the slot arc segment is defined by radially inner and outer walls, and the radially inner wall is scalloped.