# US 10,865,648 B2 · Turbine rotor blade assembly > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,865,648 B2 - Document ID: US10865648B2 - Status: Granted - Kind: B2 - Application number: 16/345,083 - Filed: 2016-12-22 - Published: 2019-08-15 - Granted: 2020-12-15 - Earliest claimed: 2016-12-22 - Assignees: Mitsubishi Heavy Industries Compressor Corporation - Applicants: Mitsubishi Heavy Industries Compressor Corporation - Inventors: Nobuyori Yagi; Shin Yanagisawa; Yuki Nakamura; Kyoichi Ikeno - Web page: https://patentgrep.com/patent/US10865648B2 ## CPC - F01D 5/22: Blade-to-blade connections, {e.g. for damping vibrations} - F01D 5/225: {by shrouding} - F01D 5/3007: {of axial insertion type} - F05D 2220/31: in steam turbines - F05D 2240/30: Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A turbine rotor blade assembly in which values A, CF, T, and L are set to satisfy the following expression in two-dimensional coordinates, 1.2×105≤(A×CF)/(T×L)≤17×105, where (A×CF)/(T×L) is an expression (1), A is an arm length [mm] of each of turbine rotor blades, CF is centrifugal force [kgf] occurring on each of the turbine rotor blades, T is a thickness [mm] of each of shrouds, and L is a lap amount [mm] of the shrouds adjacent to each other. ## Claims ### Claim 1 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. ### Claim 2 (depends on 1) The turbine rotor blade assembly according to claim 1, wherein the values A, CF, T, and L are set to satisfy a following expression in two-dimensional coordinates, T≤8.3×10−6×(A×CF/L) and T≤0.6×10−6×(A×CF/L). ### Claim 3 (depends on 2) The turbine rotor blade assembly according to claim 2, wherein the values A, CF, T, and L are set to satisfy a following expression, T≤4.3×10−6×(A×CF/L) and T≥0.9×10−6×(A×CF/L). ### Claim 4 (depends on 2) The turbine rotor blade assembly according to claim 2, wherein the values A, CF, T, and L are set to satisfy a following expression, T≤3.3×10−6×(A×CF/L) and T≥2.0×10−6×(A×CF/L). ### Claim 5 (depends on 2) The turbine rotor blade assembly according to claim 2, wherein the turbine rotor blades are operated at a number of rotations of 4000 rpm to 8000 rpm. ### Claim 6 (depends on 2) The turbine rotor blade assembly according to claim 2, wherein the profile of each of the turbine rotor blades has a height of 20 mm to 80 mm. ### Claim 7 (depends on 2) The turbine rotor blade assembly according to claim 2, wherein a gravity center of each of the profiles is offset from a center of the corresponding blade root to rear side or front side to which the turbine rotor blades are inclined during the assembly. ### Claim 8 (depends on 1) The turbine rotor blade assembly according to claim 1, wherein the turbine rotor blades are operated at a number of rotations of 4000 rpm to 8000 rpm. ### Claim 9 (depends on 1) The turbine rotor blade assembly according to claim 1, wherein the profile of each of the turbine rotor blades has a height of 20 mm to 80 mm. ### Claim 10 (depends on 1) The turbine rotor blade assembly according to claim 1, wherein a gravity center of each of the profiles is offset from a center of the corresponding blade root to rear side or front side to which the turbine rotor blades are inclined during the assembly. ### Claim 11 (depends on 1) The turbine rotor blade assembly according to claim 1, wherein the values A, CF, T, and L are set to satisfy a following expression in the two-dimensional coordinates, 2.3×105≤(A×CF)/(T×L)≤10.6×105. ### Claim 12 (depends on 1) The turbine rotor blade assembly according to claim 1, wherein the values A, CF, T, and L are set to satisfy a following expression in the two-dimensional coordinates, 3.0×105≤(A×CF)/(T×L)≤5.0×105. ### Claim 13 (depends on 1) The turbine rotor blade assembly according to claim 1, wherein the centrifugal force CF is determined from a following expression, CF={M×R×(2π×N/60)2}/G, where M is a mass [kg] of each of the turbine rotor blades, R is a rotation radius [m] of each of the turbine rotor blades, N is a number of rotations [rpm] of each of the turbine rotor blades, and G is gravity acceleration [m/s2].