Vane arc segment with single-sided platforms

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
• a ceramic matrix composite (CMC) fairing including an airfoil section defining suction and pressure side walls, leading and trailing ends, and inner and outer radial ends, a first single-sided platform at the outer radial end projecting in a first circumferential direction from the suction side wall, and a second single-sided platform at the inner radial end projecting in a second, opposite circumferential direction from the pressure side wall, wherein the first single-sided platform being comprised of a fiber layer extending from the airfoil section at the first radial end and turning into the first single-sided platform, and the second single-sided platform being comprised of the fiber layer extending from the airfoil section at the second radial end and turning into the second single-sided platform,
• the first single-sided platform includes an edge portion that has a contour that is complementary in shape to the pressure side wall of the airfoil section, and aft of the edge portion the first single-sided platform includes a straight portion, the straight portion comprising circumferentially-facing surfaces on both suction and pressure side wall facing sides of the straight portion, aft of the airfoil section.

A vane arc segment comprising:

• a ceramic matrix composite (CMC) fairing including
• an airfoil section defining suction and pressure side walls, leading and trailing ends, and inner and outer radial ends,
• a first single-sided platform at the outer radial end projecting in a first circumferential direction from the suction side wall, and
• a second single-sided platform at the inner radial end projecting in a second, opposite circumferential direction from the pressure side wall,
• wherein the first single-sided platform being comprised of a fiber layer extending from the airfoil section at the first radial end and turning into the first single-sided platform,
• the second single-sided platform being comprised of the fiber layer extending from the airfoil section at the second radial end and turning into the second single-sided platform, and
• the second single-sided platform includes an edge portion that has a contour that is complementary in shape to the suction side wall of the airfoil section, and forward of the edge portion of the second single-sided platform, the second single-sided platform includes a straight portion, the straight portion comprising circumferentially-facing surfaces on both suction and pressure side wall facing sides of the straight portion, forward of the airfoil section.