# US 12,215,622 B1 · Partial exhaust condensation intercooling > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,215,622 B1 - Document ID: US12215622B1 - Status: Granted - Kind: B1 - Application number: 18/457,458 - Filed: 2023-08-29 - Granted: 2025-02-04 - Earliest claimed: 2023-08-29 - Assignees: Rtx Corporation - Applicants: Rtx Corporation - Inventors: Neil J. Terwilliger; Lance L. Smith - Web page: https://patentgrep.com/patent/US12215622B1 ## CPC - F02C 3/305: {Increasing the power, speed, torque or efficiency of a gas turbine or the thrust of a turbojet engine by injecting or adding water, steam or other fluids (F01K21/04 takes precedence)} - F02C 7/1435: {by water injection} - F02C 3/06: the compressor comprising only axial stages (F02C3/10 takes precedence) - F02C 3/22: the fuel or oxidant being gaseous at standard temperature and pressure (F02C3/28 takes precedence) - F02C 7/143: before or between the compressor stages - F02C 7/16: characterised by cooling medium - F02C 7/224: Heating fuel before feeding to the burner - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2220/62: with energy recovery turbines - F05D 2260/211: by intercooling, e.g. during a compression cycle - F05D 2260/212: by water injection - F05D 2260/213: by the provision of a heat exchanger within the cooling circuit - F05D 2260/609: Deoiling or demisting - 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 An aircraft propulsion system includes a compressor section where an inlet airflow is compressed, a combustor section where the compressed inlet airflow is mixed with fuel and ignited to generate an exhaust gas flow that is communicated through a core flow path, a turbine section through which the exhaust gas flow expands to generate a mechanical power output, the exhaust gas flow is split into at least a first exhaust gas flow and a second exhaust gas flow, and a condenser where water is extracted from the second exhaust gas flow, and a first heat exchanger where at least a portion of the extracted water is utilized for cooling a core flow along the core flow path. ## Claims ### Claim 1 An aircraft propulsion system comprising: a compressor section where an inlet airflow is compressed to generate a compressed airflow; a combustor section where the compressed airflow is mixed with fuel and ignited to generate an exhaust gas flow that is communicated through a core flow path; a turbine section through which the exhaust gas flow expands to generate a mechanical power output, wherein the exhaust gas flow is split into at least a first exhaust gas flow and a second exhaust gas flow, wherein the second exhaust gas flow is of a flow volume that is less than that of the first exhaust gas flow; and a condenser where water is extracted from the second exhaust gas flow to generate an extracted water flow; and a first heat exchanger where at least a portion of the extracted water flow is utilized for cooling a core flow along the core flow path. ### Claim 2 (depends on 1) The aircraft propulsion system as recited in claim 1, including a fuel system for communication of a fuel flow to the combustor section, wherein a portion of the fuel flow is in thermal communication with the condenser for cooling the second exhaust gas flow. ### Claim 3 (depends on 1) The aircraft propulsion system as recited in claim 1, including a refrigerant circuit heat exchanger for transferring thermal energy between the condenser and a cold sink. ### Claim 4 (depends on 3) The aircraft propulsion system as recited in claim 3, wherein the cold sink comprises a cryogenic fuel flow and further including a turboexpander where a portion of a heated fuel flow is expanded to generate a cooled fuel flow that is thermally communicated with the refrigerant circuit heat exchanger. ### Claim 5 (depends on 1) The aircraft propulsion system as recited in claim 1, including a secondary condenser where a fan bypass airflow is placed in thermal communication with the second exhaust gas flow. ### Claim 6 (depends on 1) The aircraft propulsion system as recited in claim 1, wherein the first heat exchanger is in thermal communication with a portion of the core flow where the extracted water flow is heated to generate a steam flow, and wherein the steam flow is injected into the core flow path. ### Claim 7 (depends on 6) The aircraft propulsion system as recited in claim 6, wherein the steam flow is communicated to a fuel nozzle of the combustor section for injection with a flow of fuel. ### Claim 8 (depends on 1) The aircraft propulsion system as recited in claim 1, wherein at least a portion of the extracted water flow is injected as an intercooling flow into the core flow path through at least one injection location. ### Claim 9 (depends on 1) The aircraft propulsion system as recited in claim 1, including an exhaust flow turbine through which the first exhaust gas flow is expanded to generate shaft power. ### Claim 10 (depends on 1) The aircraft propulsion system as recited in claim 1, wherein the first exhaust gas flow is exhausted from an aft exit of the turbine section and the second exhaust gas flow is tapped from a location in the turbine section that is upstream of the aft exit. ### Claim 11 An aircraft propulsion system comprising: a compressor section where an inlet airflow is compressed to generate a compressed airflow; a combustor section where the compressed airflow is mixed with fuel and ignited to generate an exhaust gas flow that is communicated through a core flow path; a turbine section through which the exhaust gas flow expands to generate a mechanical power output, wherein the exhaust gas flow is split into at least a first exhaust gas flow and a second exhaust gas flow; and a condenser where water is extracted from the second exhaust gas flow to generate an extracted water flow; a first heat exchanger where at least a portion of the extracted water flow is utilized for cooling a core flow along the core flow path; and a control device configured to vary a ratio of the first exhaust gas flow to the second exhaust gas flow and a controller programmed to operate the control device based upon information indicative of at least one operating condition. ### Claim 12 An aircraft propulsion system comprising: a compressor section where an inlet airflow is compressed to generate a compressed airflow; a combustor section where the compressed airflow is mixed with fuel and ignited to generate an exhaust gas flow that is communicated through a core flow path; a turbine section through which the exhaust gas flow expands to generate a mechanical power output, wherein the exhaust gas flow is split into at least a first exhaust gas flow and a second exhaust gas flow; and a condenser where water is extracted from the second exhaust gas flow to generate an extracted water flow; a first heat exchanger where at least a portion of the extracted water flow is utilized for cooling a core flow along the core flow path; and a mixer where the first exhaust gas flow and the second exhaust gas flow are recombined and exhausted through a nozzle. ### Claim 13 (depends on 12) The aircraft propulsion system as recited in claim 12, further including a controller programmed to operate at least one control device configured to control recombination of the first exhaust gas flow and the second exhaust gas flow, wherein the at least one control device comprises one of a turbine, a valve or the mixer. ### Claim 14 A turbine engine assembly comprising: a core engine defining a core flow path and configured to generate an exhaust gas flow; a condenser configured to receive a partial portion of the exhaust gas flow and to extract water from the partial portion of the exhaust gas flow to generate an extracted water flow, wherein the partial portion of the exhaust gas flow is tapped from a location in the turbine section that is upstream of an aft exit; and a first heat exchanger where at least a portion of the extracted water flow is utilized for cooling a core flow along the core flow path. ### Claim 15 (depends on 14) The turbine engine assembly as recited in claim 14, wherein the first heat exchanger is in thermal communication with a portion of the core flow where the extracted water flow is heated to generate a steam flow, and wherein the steam flow is injected into the core flow path. ### Claim 16 (depends on 14) The turbine engine assembly as recited in claim 14, including a fuel system generating a fuel flow, wherein a portion of the fuel flow is in thermal communication with a refrigerant circuit for cooling the partial portion of the exhaust gas flow. ### Claim 17 A method of operating a turbine engine including a cryogenic fuel system comprising: splitting a total exhaust gas flow into a first exhaust gas flow and a second exhaust gas flow such that the second exhaust gas flow is of a flow volume less than that of the first exhaust gas flow; cooling the second exhaust gas flow to condense water into a liquid form, wherein a portion of a cryogenic fuel flow from the cryogenic fuel system accepts thermal energy from the second exhaust gas flow; extracting liquid water from the partial portion of the second exhaust gas flow to generate an extracted water flow; and cooling a portion of a core flow along a core flow path by injecting a portion of the extracted water flow into the core flow path. ### Claim 18 (depends on 17) The method as recited in claim 17, further comprising generating a steam flow from at least a portion of the extracted water flow and injecting the steam flow into the core flow path of the turbine engine.