# US 12,000,339 B2 · Integral superstructure for load path optimization > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,000,339 B2 - Document ID: US12000339B2 - Status: Granted - Kind: B2 - Application number: 17/526,340 - Filed: 2021-11-15 - Published: 2022-03-10 - Granted: 2024-06-04 - Earliest claimed: 2016-11-15 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Joshua Tyler Mook; John Alan Manteiga; Christopher Williams - Web page: https://patentgrep.com/patent/US12000339B2 ## CPC - F02C 7/06: Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) - F01D 25/162: {Bearing supports} - F01D 25/246: {Fastening of diaphragms or stator-rings} - F02C 3/14: characterised by the arrangement of the combustion chamber in the plant (combustion chambers per se F23R; F02C3/205 takes precedence) - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F02C 7/20: Mounting or supporting of plant; Accommodating heat expansion or creep - F04D 29/053: Shafts - F04D 29/056: Bearings - F04D 29/321: {for axial flow compressors} - F04D 29/541: {Specially adapted for elastic fluid pumps (F04D29/56 takes precedence)} - F05D 2220/32: in gas turbines - F05D 2240/35: Combustors or associated equipment - 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) - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract The present disclosure generally relates to monolithic superstructures for supporting a rotating shaft coupled to a rotor relative to a stator. An integral superstructure supports the rotating component. The superstructure includes a bearing portion that contacts the shaft. A stator portion, is spaced a critical dimension radially outward, from the rotor. A first annular transfer portion extends axially forward from the bearing to the stator portion. A second annular transfer portion extends axially aft from the stator portion to a mounting flange. The mounting flange connects the superstructure to a frame. The superstructure maintains a critical dimension between the rotor and the stator as the temperature of the superstructure increases. The rotor may be a compressor impeller in a gas turbine engine and the stator may be an aero component that transfers air into a combustor. ## Claims ### Claim 1 An apparatus for transferring load from a rotating component including a longitudinal shaft and a rotor, comprising: an integral superstructure supporting the rotating component including: a bearing portion that contacts the longitudinal shaft; an aero component, spaced radially outward a dimension, from the rotor, the aero component to define a flow path between the rotor and a combustor; a first annular transfer portion extending axially forward from the bearing portion to the aero component; an outer case including a mounting tab to connect the integral superstructure to a frame; and an aero component support extending axially aft from the aero component to the mounting tab, the aero component support radially inward of the outer case, the aero component support having a first end and a second end, the first end extending from and integral with the aero component, the second end extending from and integral with the outer case, the aero component support radially outward of the flow path. ### Claim 2 (depends on 1) The apparatus of claim 1, wherein the first annular transfer portion and the aero component support allow the aero component to maintain radial alignment with the rotor when a temperature of the apparatus increases. ### Claim 3 (depends on 1) The apparatus of claim 1, wherein the dimension is maintained within 10% when a temperature of the apparatus increases by at least 200 degrees Fahrenheit. ### Claim 4 (depends on 1) The apparatus of claim 1, wherein the first annular transfer portion is conical. ### Claim 5 (depends on 1) The apparatus of claim 1, wherein the aero component includes: a diffuser portion; and a deswirler portion including a plurality of conjoined tubes extending from a radial end of the diffuser portion. ### Claim 6 (depends on 5) The apparatus of claim 5, wherein the aero component support is adjacent to the deswirler portion. ### Claim 7 (depends on 1) The apparatus of claim 1, further including a compressor flange to couple the integral superstructure to a compressor case. ### Claim 8 (depends on 5) The apparatus of claim 5, wherein the plurality of conjoined tubes include a plurality of air extraction ports providing fluid communication between the plurality of conjoined tubes and an interior of the frame. ### Claim 9 (depends on 5) The apparatus of claim 5, wherein the aero component further includes a back wall swirl plate extending radially inward from the diffuser portion. ### Claim 10 A gas turbine engine including: a shaft; a rotor; and an integral superstructure including: a bearing portion that contacts the shaft; an aero component, spaced radially outward a dimension, from the rotor, the aero component to define a flow path between the rotor and a combustor; a first annular transfer portion extending axially forward from the bearing portion to the aero component; an outer case including a mounting tab that connects the integral superstructure to a frame; and an aero component support extending axially aft from the aero component to the mounting tab, the aero component support radially inward of the outer case, the aero component support having a first end and a second end, the first end extending from and integral with the aero component, the second end extending from and integral with the outer case, the aero component support radially outward of the flow path. ### Claim 11 (depends on 10) The gas turbine engine of claim 10, wherein the first annular transfer portion and the aero component support allow the aero component to move from thermal expansion in a same direction as the rotor when a temperature of the integral superstructure increases. ### Claim 12 (depends on 10) The gas turbine engine of claim 10, wherein the dimension is maintained within 10% when a temperature of the integral superstructure increases by at least 200 degrees Fahrenheit. ### Claim 13 (depends on 10) The gas turbine engine of claim 10, wherein the first annular transfer portion is conical. ### Claim 14 (depends on 10) The gas turbine engine of claim 10, wherein the aero component includes: a diffuser portion; and a deswirler portion including a plurality of conjoined tubes extending from a radial end of the diffuser portion. ### Claim 15 (depends on 14) The gas turbine engine of claim 14, wherein the aero component support is adjacent to the deswirler portion. ### Claim 16 (depends on 10) The gas turbine engine of claim 10, further including: a compressor case; and a compressor flange to couple the integral superstructure to the compressor case. ### Claim 17 (depends on 14) The gas turbine engine of claim 14, wherein the plurality of conjoined tubes includes a plurality of air extraction ports providing fluid communication between the plurality of conjoined tubes and an interior of the frame. ### Claim 18 A method of distributing bearing load, comprising: transferring a load from a rotating shaft to a bearing portion of a superstructure via contact between the rotating shaft and the bearing portion; transferring the load from the bearing portion via a first annular support of the superstructure to an aero component, the aero component to define a flow path between a rotor and a combustor; transferring the load from the aero component of the superstructure to an aero component support; transferring the load from the aero component support to a mounting tab of an outer case, the aero component support radially inward of the outer case, the aero component support having a first end and a second end, the first end extending from and integral with the aero component, the second end extending from and integral with the outer case, the aero component support radially outward of the flow path; and transferring the load from the mounting tab to a vehicle. ### Claim 19 (depends on 18) The method of claim 18, wherein the rotating shaft is coupled to the rotor, and wherein a critical dimension is defined between the rotor and the aero component. ### Claim 20 (depends on 19) The method of claim 19, further comprising maintaining the critical dimension within 10% when a at least one of a temperature of the rotor or a temperature of the aero component increases by at least 200 degrees Fahrenheit.