# US 9,752,507 B2 · Aircraft system with fuel-to-fuel heat exchanger > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,752,507 B2 - Document ID: US9752507B2 - Status: Granted - Kind: B2 - Application number: 14/618,801 - Filed: 2015-02-10 - Published: 2016-08-11 - Granted: 2017-09-05 - Earliest claimed: 2015-02-10 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Tyler J. Selstad; Timothy J. Gaudet - Web page: https://patentgrep.com/patent/US9752507B2 ## CPC - F02C 7/224: Heating fuel before feeding to the burner - F02C 7/14: of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)} - F05D 2260/213: by the provision of a heat exchanger within the cooling circuit - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An aircraft system is provided that includes a fuel reservoir, a turbine engine and a fuel-to-fuel heat exchanger. The heat exchanger is fluidly coupled between the fuel reservoir and the turbine engine. ## Claims ### Claim 1 An aircraft system, comprising: a fuel reservoir; a turbine engine; and a fuel-to-fuel heat exchanger fluidly coupled between the fuel reservoir and the turbine engine, wherein the heat exchanger is adapted to direct supply fuel from the fuel reservoir to the turbine engine, and the heat exchanger is further adapted to direct return fuel from the turbine engine to the fuel reservoirs; wherein the fuel-to-fuel heat exchanger comprises a supply flow path and a return flow path; wherein the supply flow path is fluidly coupled between an outlet of the fuel reservoir and an inlet of the turbine engine and is adapted to direct the supply fuel from the fuel reservoir to the turbine engine; wherein the return flow path is fluidly coupled between an inlet of the fuel reservoir and an outlet of the turbine engine and is adapted to direct the return fuel from the turbine engine to the fuel reservoir; and wherein the supply flow path and the return flow path are configured fluidly in parallel between the fuel reservoir and the turbine engine through the heat exchanger. ### Claim 2 (depends on 1) The aircraft system of claim 1, wherein the heat exchanger is a counter-flow heat exchanger. ### Claim 3 (depends on 1) The aircraft system of claim 1, wherein the heat exchanger includes a first flow path and a second flow path; and the first flow path and the second flow path are fluidly coupled in parallel between the fuel reservoir and a component of the turbine engine. ### Claim 4 (depends on 1) The aircraft system of claim 1, wherein the heat exchanger includes a first flow path and a second flow path with a plurality of sub-flow paths distributed about the first flow path. ### Claim 5 (depends on 1) The aircraft system of claim 1, wherein the heat exchanger comprises a conduit including a central bore and a plurality of channels, and the channels are embedded within a sidewall of the conduit. ### Claim 6 (depends on 5) The aircraft system of claim 5, wherein the heat exchanger further comprises a first manifold and a second manifold, and the channels extend between the first manifold and the second manifold. ### Claim 7 (depends on 5) The aircraft system of claim 5, wherein the turbine engine comprises a fuel management system including an inlet and an outlet; the inlet is fluidly coupled with the bore; and the outlet is fluidly coupled with the channels. ### Claim 8 (depends on 1) The aircraft system of claim 1, further comprising an airframe, wherein the heat exchanger is arranged within the airframe and the turbine engine is attached to the airframe. ### Claim 9 (depends on 1) The aircraft system of claim 1, wherein the heat exchanger is remotely located from the turbine engine. ### Claim 10 An aircraft system, comprising: a fuel reservoir; a fuel management system including a boost pump, a main pump and an injector; and a fuel-to-fuel heat exchanger fluidly coupled between the fuel reservoir and the fuel management system; wherein the heat exchanger includes a supply flow path and a return flow path, and the supply flow path and the return flow path are fluidly coupled in parallel between the fuel reservoir and the fuel management system through the heat exchanger; wherein the supply flow path is fluidly coupled between an outlet of the fuel reservoir and an inlet of the fuel management system and is adapted to direct the supply fuel from the fuel reservoir to the fuel management system; and wherein the return flow path is fluidly coupled between an inlet of the fuel reservoir and an outlet of the fuel management system and is adapted to direct the return fuel from the fuel management system to the fuel reservoir. ### Claim 11 (depends on 10) The aircraft system of claim 10, further comprising a turbine engine that includes the fuel management system, wherein the heat exchanger is remotely located from the turbine engine. ### Claim 12 (depends on 10) The aircraft system of claim 10, further comprising an airframe within which the heat exchanger is configured. ### Claim 13 An aircraft system, comprising: a fuel reservoir; a turbine engine; and a fuel-to-fuel heat exchanger including a supply flow path and a return flow path, wherein the supply flow path and the return flow path are fluidly coupled in parallel between the fuel reservoir and a component of the turbine engine through the heat exchanger; wherein the supply flow path is fluidly coupled between an outlet of the fuel reservoir and an inlet of the turbine engine and is adapted to direct the supply fuel from the fuel reservoir to the turbine engine; and wherein the return flow path is fluidly coupled between an inlet of the fuel reservoir and an outlet of the turbine engine and is adapted to direct the return fuel from the turbine engine to the fuel reservoir. ### Claim 14 (depends on 13) The aircraft system of claim 13, wherein the heat exchanger is remotely located from the turbine engine. ### Claim 15 (depends on 13) The aircraft system of claim 13, further comprising an airframe, wherein the heat exchanger is arranged within the airframe and the turbine engine is mounted to the airframe.