Turbine rotor blade assembly

A turbine rotor blade assembly in which a plurality of turbine rotor blades are provided in a circumferential direction of a turbine disc, and the plurality of turbine rotor blades are inclined in a predetermined direction during assembly whereas the plurality of turbine rotor blades rise during rotation operation, the turbine rotor blade assembly comprising:

• platforms each including a blade root implanted in a blade groove provided on an outer peripheral surface of the turbine disc;
• profiles rising from the respective platforms;
• and
• shrouds provided at respective front ends of the profiles, wherein
• values A, CF, T, and L are set to satisfy a following expression in two-dimensional coordinates,
• 1.2×105≤(A×CF)/(T×L)≤17×105,
• where
• A is an arm length [mm] of each of the turbine rotor blades, and CF is centrifugal force [kgf] occurring on each of the turbine rotor blades during a rotation operation of the turbine rotor blade assembly, wherein
• the arm length is a distance from a rotation center to a gravity center of each of the turbine rotor blades, and
• the rotation center of each of the turbine rotor blades is a rotation center when each of the turbine rotor blades receives the centrifugal force CF,
• T is a thickness [mm] of each of the shrouds, and L is a lap amount [mm] of the shrouds adjacent to each other, wherein
• the lap amount L=P1−P2, where P1 is a pitch of each of the shrouds in the circumferential direction during assembly, and
• P2 is a pitch of each of the shrouds in the circumferential direction in a rising state of the turbine rotor blade assembly during rotation operation.