Method of operating an aircraft engine and fuel system using multiple fuel types
AssigneePratt & Whitney Canada Corp.
InventorsSean DURAND, Harris SHAFIQUE, David WADDLETON
Life of this patent
Estimating the term…
Abstract
The method can include simultaneously conveying a controlled flow rate of jet fuel from a first reservoir area of the aircraft to a fuel nozzle across at least one auxiliary system, including the at least one auxiliary system using the controlled flow rate of jet fuel for operation and conveying a controlled flow rate of an alternative fuel from a second reservoir area of the aircraft to the fuel nozzle.
Claims21
A method of operating an aircraft gas turbine engine having at least one fuel nozzle in fluid communication with a combustion chamber, the method comprising:
- conveying a first fuel at a first controlled flow rate from a first reservoir of the aircraft towards the at least one fuel nozzle through at least one auxiliary system, the at least one auxiliary system using the first fuel for operation, the at least one auxiliary system requiring a minimal flow rate of the first fuel for operation, the first controlled flow rate being equal to or greater than the minimal flow rate;
- directing at least a portion of the first fuel from a location downstream of the at least one auxiliary system towards the first reservoir;
- and
- simultaneously to the conveying of the first fuel at the first controlled flow rate, conveying an alternative fuel at a second controlled flow rate from a second reservoir of the aircraft towards the at least one fuel nozzle.
A fuel system for a gas turbine engine having at least one fuel nozzle open to a combustion chamber, the fuel system comprising:
- a jet fuel subsystem having a jet fuel conduit extending from a first reservoir area to the at least one fuel nozzle across at least one auxiliary system using a flow of the jet fuel during operation, the at least one auxiliary system requiring a minimal flow rate of the jet fuel for operation, the jet fuel subsystem flowing the jet fuel at a first controlled flow rate within the jet fuel conduit during operation, the jet fuel subsystem having an actuator valve downstream of the at least one auxiliary system, the actuator valve having an inlet fluidly connected to the at least one auxiliary system, a first outlet fluidly connected to the at least one fuel nozzle, and a second outlet fluidly connected to a recirculation conduit fluidly connected to the first reservoir, wherein the jet fuel subsystem is operable in a configuration in which the actuator valve connects the second outlet to the recirculation conduit and in which the first controlled flow rate is equal to or greater than the minimal flow rate;
- and
- an alternative fuel subsystem having an alternative fuel conduit extending from a second reservoir area to the at least one fuel nozzle, the alternative fuel subsystem being configured to deliver the alternative fuel at a second controlled flow rate to the at least one fuel nozzle.
(canceled)
An aircraft having a gas turbine engine having at least one fuel nozzle open to a combustion chamber and a fuel system comprising :
- a jet fuel subsystem having a jet fuel conduit extending from a first reservoir area to the at least one fuel nozzle across at least one auxiliary system using a flow of the jet fuel during operation, the at least one auxiliary system requiring a minimal flow rate of the jet fuel for operation, the jet fuel subsystem circulating the jet fuel at a first controlled flow rate within the jet fuel conduit during operation, the jet fuel subsystem having an actuator valve downstream of the at least one auxiliary system, the actuator valve having an inlet fluidly connected to the at least one auxiliary system, a first outlet fluidly connected to the at least one fuel nozzle, and a second outlet fluidly connected to a recirculation conduit fluidly connected to the first reservoir, wherein the jet fuel subsystem is operable in a configuration in which the actuator valve fluidly connects the second outlet to the recirculation conduit and in which the first controlled flow rate is equal to or greater than the minimal flow rate;
- and
- an alternative fuel subsystem having an alternative fuel conduit extending from a second reservoir area to the at least one fuel nozzle, the alternative fuel subsystem being configured to deliver the alternative fuel at a second controlled flow rate to the at least one fuel nozzle.
Dependencies are inferred from the claim text.