Vane arc segment support platform with curved radial channel

A vane arc segment comprising:

• an airfoil piece defining first and second airfoil platforms and an airfoil section extending between the first and second airfoil platforms, the airfoil section having a trailing edge, a leading edge, a pressure side, and a suction side, the first and second airfoil platforms each defining a first airfoil platform circumferential side, a second airfoil platform circumferential side, a forward airfoil platform side, and an aft airfoil platform side, a gaspath side, a non-gaspath side, and the non-gaspath side of at least one of the first or second airfoil platforms having a radial flange projecting there from, the radial flange extending continuously and including a flange first leg portion extending adjacent the trailing edge, a flange second leg portion extending from the flange first leg portion and curving around the suction side, and a flange third leg portion extending from the flange second leg portion toward the forward side,
• a vane support system including first and second support platforms supporting the airfoil piece there between, each of the first and second support platforms defining a support platform forward side, a support platform aft side, a first support platform circumferential side, a second support platform circumferential side, an airfoil side, and a non-airfoil side, and
• the airfoil side of at least one of the first or second support platforms having a radial channel therein, wherein the radial channel is complementary to the radial flange so as to receive the radial flange therein, the radial channel defining a first side proximate the airfoil section and a second side distal from the airfoil section, the radial flange bearing against the second side, and there is an expansion gap between the radial flange and the first side of the radial channel.

A gas turbine engine comprising:

• a compressor section;
• a combustor in fluid communication with the compressor section;
• and
• a turbine section in fluid communication with the combustor, the turbine section having vane arc segments disposed about a central axis of the gas turbine engine, each of the vane arc segments includes:
• an airfoil piece defining first and second airfoil platforms and an airfoil section extending between the first and second airfoil platforms, the airfoil section having a trailing edge, a leading edge, a pressure side, and a suction side, the first and second airfoil platforms each defining a first airfoil platform circumferential side, a second airfoil platform circumferential side, a forward airfoil platform side, an aft airfoil platform side, a gaspath side, a non-gaspath side, and the non-gaspath side of at least one of the first or second support platforms having a radial flange projecting there from, the radial flange extending continuously and including a flange first leg portion extending adjacent the trailing edge, a flange second leg portion extending from the flange first leg portion and curving around the suction side, and a flange third leg portion extending from the flange second leg portion toward the forward side,
• a vane support system including first and second support platforms supporting the airfoil piece there between, each of the first and second support platforms defining a support platform forward side, a support platform aft side, a first support platform circumferential side, a second support platform circumferential side, an airfoil side, and a non-airfoil side,
• the airfoil side of at least one of the first or second support platforms having a radial channel therein, wherein the radial channel is complementary to the radial flange so as to receive the radial flange therein, and
• the radial channel including a radial channel first leg portion extending adjacent the aft support platform side, a radial channel second leg portion extending from the radial channel first leg portion and curving toward the forward support platform side, and a radial channel third leg portion extending from the radial channel second leg portion toward the forward support platform side, wherein the radial channel first leg portion is parallel to the aft support platform side.