# US 9,038,366 B2 · LPC flowpath shape with gas turbine engine shaft bearing configuration > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,038,366 B2 - Document ID: US9038366B2 - Status: Granted - Kind: B2 - Application number: 14/067,354 - Filed: 2013-10-30 - Published: 2014-09-04 - Granted: 2015-05-26 - Earliest claimed: 2012-01-31 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Brian D. Merry; Gabriel L. Suciu; Lisa I. Brilliant; Becky E. Rose; Yuan Dong; Stanley J. Balamucki - Web page: https://patentgrep.com/patent/US9038366B2 ## CPC - F02C 3/13: having variable working fluid interconnections between turbines or compressors or stages of different rotors {(controlling flow ratio between different flows of multi-flow jet-propulsion plant, e.g. ducted fan F02K3/075)} - F01D 5/143: {Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour} - F01D 25/162: {Bearing supports} - F02C 7/36: Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) - F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} - F02K 3/04: the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flowpath. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged in a core flow path axially between the inlet case flow path and the intermediate case flow path. The core flowpath has an inner diameter and an outer diameter. At least a portion of inner diameter has an increasing slope angle relative to the rotational axis. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case. ## Claims ### Claim 1 A gas turbine engine comprising: a core housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flowpath, wherein the inlet case includes a first inlet case portion defining the inlet case flow path, and a bearing support portion is removably secured to the inlet case portion; a fan arranged fluidly upstream of the core housing; a shaft providing a rotational axis; a geared architecture coupled to the shaft, and the fan coupled to and rotationally driven by the geared architecture; a hub operatively supported by the shaft; a rotor connected to the hub and supporting a compressor section arranged fluidly downstream from the inlet case, the compressor section being arranged in a core flow path axially between the inlet case flow path and the intermediate case flow path, the core flowpath having an inner diameter and an outer diameter, wherein the at least a portion of the inner diameter has an increasing slope angle relative to the rotational axis; a first bearing mounted to the hub and supporting the shaft relative to one of the intermediate case and the inlet case, the first bearing mounted to the bearing support portion; and a second bearing mounted to the hub and supporting the shaft relative to the other of the intermediate case and the inlet case. ### Claim 2 (depends on 1) The gas turbine engine according to claim 1, wherein the outer diameter has an outer diameter slope angle relative to the rotational axis along a fluid flow direction of the core flow path of between 0 degrees and 15 degrees. ### Claim 3 (depends on 1) The gas turbine engine according to claim 1, wherein the fan is connected to the shaft through the geared architecture, wherein the compressor section is a low pressure compressor. ### Claim 4 (depends on 2) The gas turbine engine according to claim 2, wherein the outer diameter slope angle decreases relative to the rotational axis. ### Claim 5 (depends on 2) The gas turbine engine according to claim 2, wherein the outer diameter slope angle is in the range of 0 degrees to 10 degrees. ### Claim 6 (depends on 5) The gas turbine engine according to claim 5, wherein the outer diameter slope angle is in the range of 5 degrees to 7 degrees. ### Claim 7 (depends on 6) The gas turbine engine according to claim 6, wherein the outer diameter slope angle is 6 degrees. ### Claim 8 (depends on 4) The gas turbine engine according to claim 4, wherein the fan is connected to the shaft through the geared architecture, wherein the compressor section is a low pressure compressor. ### Claim 9 (depends on 8) The gas turbine engine according to claim 8, wherein the low pressure compressor comprises at least one variable vane. ### Claim 10 (depends on 8) The gas turbine engine according to claim 8, wherein the low pressure compressor further comprises an exit guide vane, wherein the exit guide vane is located in a low pressure compressor outlet section of the core flow path. ### Claim 11 (depends on 10) The gas turbine engine according to claim 10, wherein the low pressure compressor further comprises a low pressure bleed located between a low pressure compressor rotor and the exit guide vane. ### Claim 12 (depends on 11) The gas turbine engine according to claim 11, wherein the low pressure bleed further comprises a bleed trailing edge, and wherein the bleed trailing edge extends into the core flow path beyond the outer diameter of the core flow path. ### Claim 13 (depends on 8) The gas turbine engine according to claim 8, wherein the low pressure compressor is a multi-stage compressor. ### Claim 14 (depends on 1) The gas turbine engine according to claim 1, wherein the intermediate case includes an intermediate case portion defining the intermediate case flow path, and a second bearing support portion removably secured to the intermediate case portion, the second mounted to the second bearing support portion. ### Claim 15 (depends on 14) The gas turbine engine according to claim 14, wherein the other bearing is a ball bearing. ### Claim 16 (depends on 1) The gas turbine engine according to claim 1, wherein the first and second bearings are arranged in separate sealed lubrication compartments. ### Claim 17 (depends on 1) The gas turbine engine according to claim 1, wherein the shaft includes a main shaft and a flex shaft, the flex shaft secured to the main shaft at a first end and including a second end opposite the first end, wherein the geared architecture includes a sun gear supported on the second end. ### Claim 18 (depends on 17) The gas turbine engine according to claim 17, wherein the hub is secured to the main shaft, and the compressor section includes a rotor mounted to the hub. ### Claim 19 (depends on 18) The gas turbine engine according to claim 18, wherein the geared architecture includes a torque frame supporting multiple circumferentially arranged star gears intermeshing with the sun gear, the torque frame secured to the inlet case. ### Claim 20 (depends on 1) The gas turbine engine according to claim 1, wherein the rotor supports multiple compressor stages, and the first bearing is axially aligned with and radially inward of one of the compressor stages. ### Claim 21 (depends on 20) The gas turbine engine according to claim 20, wherein the compressor section includes a variable vane array. ### Claim 22 (depends on 1) The gas turbine engine according to claim 1, comprising a lubrication compartment, wherein the geared architecture is arranged in the lubrication compartment.