Vane arc segment with flange and gusset

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 fairing having first and second fairing platforms and an airfoil section extending therebetween, the airfoil section having a pressure side, a suction side, and an internal cavity,
• the first fairing platform defining suction and pressure side circumferential mate faces, forward and aft faces, a gaspath side, a non-gaspath side, and a flange projecting from the non-gaspath side,
• the flange extending along the suction side circumferential mate face, and
• a rib having a rib section in the internal cavity spanning the pressure side and the suction side and a rib extension section extending from the rib section in the internal cavity and along the non-gaspath side of the first fairing platform, the rib extension intersecting the flange to form a gusset for reinforcing the flange, the rib extension terminating at a fillet between the pressure side of the airfoil section and the first fairing platform.

A vane system comprising:

• a plurality of vane arc segments, each said vane arc segment including,
• an airfoil fairing having first and second fairing platforms and an airfoil section extending therebetween, the airfoil section having a pressure side and a suction side,
• the first fairing platform defining suction and pressure side circumferential mate faces, forward and aft faces, a gaspath side, a non-gaspath side, and a first flange projecting from the non-gaspath side,
• the first flange extending along the suction side circumferential mate face and including a radial flange face,
• a second flange that projects from the non-gaspath side and overhangs the pressure side circumferential mate face, the second flange including a radial bearing face,
• wherein and the radial flange face of a first one of the vane arc segments seals against the radial bearing face of a second, adjacent one of the vane arc segments, and
• the airfoil section defining an internal cavity and including a rib that has a rib section in the internal cavity spanning the pressure side and the suction side and a rib extension section that extends from the rib section in the internal cavity and along the non-gaspath side of the first fairing platform, the rib extension intersecting the first flange to form a gusset for reinforcing the first flange, and the rib extension terminating at a fillet between the pressure side of the airfoil section and the first fairing platform.