Compressor areas for high overall pressure ratio gas turbine engine

摘要

A gas turbine engine (20) comprises a high pressure turbine rotor (55), an intermediate pressure turbine rotor (44) and a fan drive turbine rotor (34). The fan drive turbine rotor (34) drives a fan rotor (24) through a gear reduction (28). The intermediate pressure rotor (44) drives a low pressure compressor rotor (36) and the high pressure turbine rotor (55) drives a high pressure compressor rotor (46). A first flow cross-sectional area (A) is between an outer periphery of a hub (38) in the low pressure compressor rotor (36), and an outer tip of an upstream most blade row of the low pressure compressor rotor (36). A second flow cross-sectional area (B) is between an outer periphery of a hub in the high pressure compressor rotor (46), and an outer tip of an upstream most blade row of the high pressure compressor rotor (46). A ratio of the second and first flow cross-sectional areas is greater than or equal to about 0.12 and less than or equal to about 0.33.