A platform (410; 510) for an airfoil in a gas turbine engine, the platform (410; 510) comprising: a top wall (411; 511) defining a front end and a back end of the platform (410; 510) and configured to connect to an airfoil of the gas turbine engine; a first connector configured to receive a pin and secure the platform (410; 510) to a rotor of the gas turbine engine; a first sidewall located at the front end and extending from the top wall (411; 511) to the first connector, the first sidewall having a first arm and a second arm, wherein the first arm and the second arm of the first sidewall are curved such that a bowed first sidewall extends from the top wall (411; 511) to the first connector; a second connector (422; 522) configured to receive the pin and secure the platform (410; 510) to the rotor of the gas turbine engine; a second sidewall (434; 534) located at the back end and extending from the top wall (411; 511) to the second connector (422; 522), the second sidewall (434; 534) having a first arm (434a; 534a) and a second arm (434b; 534b), wherein the first arm (434a; 534a) and the second arm (434b; 534b) of the second sidewall (434; 534) are curved such that a bowed second sidewall extends from the top wall (411; 511) to the second connector; and an interior, the interior defined by interior surfaces of the top wall (411; 511), the first and second sidewalls (432; 434; 534) and the first and second connectors (418; 422); and wherein the first arms (432a; 434a; 534a) and the second arms (432b; 434b; 534b) of the first and second sidewalls (432; 434; 534) are bowed outward relative to the interior of the platform (410; 510). a top wall (411; 511) defining a front end and a back end of the platform (410; 510) and configured to connect to an airfoil of the gas turbine engine; a first connector configured to receive a pin and secure the platform (410; 510) to a rotor of the gas turbine engine; a first sidewall located at the front end and extending from the top wall (411; 511) to the first connector, the first sidewall having a first arm and a second arm, wherein the first arm and the second arm of the first sidewall are curved such that a bowed first sidewall extends from the top wall (411; 511) to the first connector; a second connector (422; 522) configured to receive the pin and secure the platform (410; 510) to the rotor of the gas turbine engine; a second sidewall (434; 534) located at the back end and extending from the top wall (411; 511) to the second connector (422; 522), the second sidewall (434; 534) having a first arm (434a; 534a) and a second arm (434b; 534b), wherein the first arm (434a; 534a) and the second arm (434b; 534b) of the second sidewall (434; 534) are curved such that a bowed second sidewall extends from the top wall (411; 511) to the second connector; and an interior, the interior defined by interior surfaces of the top wall (411; 511), the first and second sidewalls (432; 434; 534) and the first and second connectors (418; 422); and wherein the first arms (432a; 434a; 534a) and the second arms (432b; 434b; 534b) of the first and second sidewalls (432; 434; 534) are bowed outward relative to the interior of the platform (410; 510).