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US 9,752,507 B2Granted
Aircraft system with fuel-to-fuel heat exchanger
AssigneeUnited Technologies Corporation
InventorsTyler J. Selstad, Timothy J. Gaudet
Life of this patent
Estimating the term…
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.
Claims15
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.
6 more elements
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.
5 more elements
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.
4 more elements
Dependencies are inferred from the claim text.