FAN FOR A GAS TURBINE ENGINE AN CORRESPONDING METHOD OF SECURING FAN BLADES TO A ROTOR OF A FAN OF A GAS TURBINE ENGINE

摘要

A fan (42) for a gas turbine engine (20) comprises a rotor (84), a hollow fan blade (70) having a cavity (72) which is secured to the rotor, a cover (74) covering the cavity, and a platform (86) independent of the hollow fan blade and secured to the rotor, wherein a portion of the cover is located below a peripheral edge (88) of the platform and the peripheral edge retains the portion of the cover in a desired location. A method of securing fan blades (70) to a rotor (84) of a fan (42) of a gas turbine engine (20), comprises the steps of securing a cover (74) to a hollow fan blade (70) having a cavity (72), wherein the cover encloses the cavity of the hollow fan blade, securing a platform (86) independent of the hollow fan blade to the rotor, and inserting a portion of the hollow fan blade into a slot (82) of the rotor in order to secure the hollow fan blade to the rotor, wherein a portion of the cover is located below a peripheral edge (88) of the platform when the platform and the hollow fan blade are secured to the rotor and wherein the peripheral edge retains the portion of the cover in a desired location.