# US 12,179,929 B2 · Engine mount system for a gas turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,179,929 B2 - Document ID: US12179929B2 - Status: Granted - Kind: B2 - Application number: 18/215,394 - Filed: 2023-06-28 - Published: 2024-03-07 - Granted: 2024-12-31 - Earliest claimed: 2008-06-02 - Assignees: Rtx Corporation - Applicants: Rtx Corporation - Inventors: Gabriel L. Suciu; Brian D. Merry; Christopher M. Dye; Steven B. Johnson; Frederick M. Schwarz - Web page: https://patentgrep.com/patent/US12179929B2 ## CPC - F02K 3/06: with front fan - B64D 27/402: {comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant} - B64D 27/404: {Suspension arrangements specially adapted for supporting vertical loads} - B64D 27/406: {Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links} - F01D 5/06: Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections {(F01D5/022, F01D5/023 take precedence)} - F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} - F01D 15/12: Combinations with mechanical gearing (driven by multiple engines F01D13/00) - F01D 25/24: Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) - F01D 25/28: Supporting or mounting arrangements, e.g. for turbine casing - F02C 3/107: with two or more rotors connected by power transmission - F02C 7/20: Mounting or supporting of plant; Accommodating heat expansion or creep - 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)} - F02C 9/20: by throttling; by adjusting vanes - F02K 1/15: Control or regulation - F05D 2220/32: in gas turbines - F05D 2220/36: specially adapted for the fan of turbofan engines - F05D 2260/4031: as in toothed gearing - F05D 2260/40311: of the epicyclical, planetary or differential type - F05D 2270/42: passive or reactive, e.g. using large wind vanes - 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) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A gas turbine engine includes, among other things, a propulsor section including a rotor and blades, a gear train, a compressor section and a turbine section. A static structure includes a first case and a second case. The first case includes a first engine mount location. The second case includes a second engine mount location. The first engine mount location is axially near the gear train. ## Claims ### Claim 1 A gas turbine engine comprising: a propulsor section including a rotor and a plurality of blades; an epicyclic gear train having a gear reduction ratio of greater than 2.5:1; a compressor section including a first compressor and a second compressor axially aft of the first compressor relative to an engine axis, the first compressor including three stages, and the second compressor including a greater number of stages than the first compressor; a turbine section including a first turbine and a second turbine, the first turbine including two stages, the second turbine including a greater number of stages than the first turbine but including a lesser number of stages than the second compressor, and the second turbine having a pressure ratio greater than 5:1 and driving the rotor through the gear train; and a static structure comprising a plurality of cases distributed along the engine axis, wherein the plurality of cases includes a first case and a second case positioned aft of the first case relative to the engine axis, the first case includes a first engine mount location, the second case includes a second engine mount location that reacts an engine thrust in operation, wherein the first engine mount location is axially near the gear train relative to the engine axis, and each of the first engine mount location and second engine mount location supporting an engine mount when the engine is mounted; and wherein the static structure supports a bearing system, and wherein the first turbine, the second turbine and the rotor are rotatably supported by the bearing system. ### Claim 2 (depends on 1) The gas turbine engine as recited in claim 1, wherein the epicyclic gear train is a planetary gear system. ### Claim 3 (depends on 2) The gas turbine engine as recited in claim 2, wherein the second engine mount location is configured so as to not be connected to the first case by any thrust links when the gas turbine engine is mounted. ### Claim 4 (depends on 2) The gas turbine engine as recited in claim 2, wherein the plurality of blades have a fixed stagger angle. ### Claim 5 (depends on 2) The gas turbine engine as recited in claim 2, wherein the propulsor delivers airflow to an entrance of a core flow path, the core flow path extends through the compressor section, and the epicyclic gear train extends axially aft of the entrance relative to the engine axis. ### Claim 6 (depends on 5) The gas turbine engine as recited in claim 5, wherein the second turbine includes no more than six stages. ### Claim 7 (depends on 2) The gas turbine engine as recited in claim 2, wherein the first case is a compressor case. ### Claim 8 (depends on 2) The gas turbine engine as recited in claim 2, wherein: the second case is a thrust case; and the turbine section includes a mid-turbine frame axially between first and second turbines relative to the engine axis, and the mid-turbine frame supports bearings of the bearing system within the thrust case. ### Claim 9 (depends on 2) The gas turbine engine as recited in claim 2, wherein the propulsor is a fan, and further comprising: a first nacelle which at least partially surrounds a second nacelle and the rotor, the first nacelle having a first exit, the second nacelle having a second exit at an axial location aft of the first exit along the engine axis, and the fan communicates airflow into the first nacelle and the second nacelle; and a bypass ratio of greater than 10:1. ### Claim 10 (depends on 9) The gas turbine engine as recited in claim 9, further comprising a fan pressure ratio of less than 1.45 across the blade alone at cruise at 0.8 Mach and 35,000 feet. ### Claim 11 (depends on 10) The gas turbine engine as recited in claim 10, wherein the second turbine includes no more than six stages, and the second compressor includes seven stages. ### Claim 12 A gas turbine engine comprising: a propulsor section including a rotor with a plurality of blades; an epicyclic gear train having a gear reduction ratio of greater than 2.5:1; a first spool including a first compressor and a first turbine, wherein the first compressor includes a plurality of stages, the first turbine includes three stages, and the first turbine drives the rotor through the gear train; a second spool including a second compressor and a second turbine, wherein the second turbine includes two stages, the first turbine includes a greater number of stages than the second turbine but includes a lesser number of stages than the second compressor, and the first and second spools are rotatable about an engine axis; and a static structure comprising a first case and a first static structure component located forward of a second static structure component, the first static structure component having a first engine mount location, the second static structure component having a second engine mount location, each of the first engine mount location and the second engine mount location supporting an engine mount when the engine is mounted, and the first engine mount location is axially near the gear train relative to the engine axis. ### Claim 13 (depends on 12) The gas turbine engine as recited in claim 12, wherein: the engine mount includes a forward mount associated with the first engine mount location and an aft mount associated with the second engine mount location; the aft mount reacts a thrust vector of a thrust load along the engine axis at a second case in operation; and the forward mount reacts a vertical load and a side load in operation. ### Claim 14 (depends on 13) The gas turbine engine as recited in claim 13, wherein the first case is an intermediate case that at least partially surrounds the gear train. ### Claim 15 (depends on 13) The gas turbine engine as recited in claim 13, wherein the first case is a compressor case. ### Claim 16 (depends on 13) The gas turbine engine as recited in claim 13, wherein: the second case is a thrust case; and the turbine section includes a mid-turbine frame axially between first and second turbines relative to the engine axis, the mid-turbine frame supports a pair of bearings of the bearing system within the thrust case, and the pair of bearings rotatably support the first and second spools. ### Claim 17 (depends on 16) The gas turbine engine as recited in claim 16, wherein the first compressor includes three stages, the first turbine includes no more than six stages, and the second compressor includes seven stages. ### Claim 18 (depends on 16) The gas turbine engine as recited in claim 16, wherein the propulsor section is a fan section including a fan case, the propulsor is a fan, and the fan case surrounds the fan. ### Claim 19 (depends on 18) The gas turbine engine as recited in claim 18, further comprising a bypass ratio of greater than 10:1.