Compressor Areas For High Overall Pressure Ratio Gas Turbine Engine

摘要

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

主权项

1. A gas turbine engine comprising:
a high pressure turbine rotor, an intermediate pressure turbine rotor and a fan drive turbine rotor, said fan drive turbine rotor driving a fan rotor through a gear reduction, said intermediate pressure rotor driving a low pressure compressor rotor and said high pressure turbine rotor driving a high pressure compressor rotor, a first flow cross-sectional area between an outer periphery of a hub in said low pressure compressor rotor, and an outer tip of an upstream most blade row of said low pressure compressor rotor; a second flow cross-sectional area between an outer periphery of a hub in said high pressure compressor rotor, and an outer tip of an upstream most blade row of said high pressure compressor rotor; and a ratio of said second flow cross-sectional area to said first flow cross-sectional area being greater than or equal to about 0.12 and less than or equal to about 0.33.