Patent ID: 9194329
Filing Date: 2015-11-24
Classification: F01D,F02C,F02K,Y02T,Y10T

Abstract:
1. A compressor module for a gas turbine engine comprising: a housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path; a shaft providing a rotational axis; first and second bearings supporting the shaft relative to the intermediate case and the inlet case, respectively, wherein the first bearing is arranged in a first bearing support, the first bearing support removably secured to the intermediate case, and the second bearing is arranged in a second bearing support, the second bearing support removably secured to the inlet case; a hub operatively supported by the shaft; and a rotor connected to the hub; a core inlet has a radially inner boundary that is spaced a first radial distance from the rotational axis, the radially inner boundary of the core inlet is at a location of a core inlet stator; and a compressor section inlet has a radially inner boundary that is spaced a second radial distance from the rotational axis, the radially inner boundary of the compressor section inlet is at a location of a first stage low-pressure compressor rotor, wherein a ratio of the second radial distance to the first radial distance is about 0.65 to about 0.9.