Aircraft powerplant with multiple independent fuel systems
AssigneePratt & Whitney Canada Corp.
InventorsMichael Mark, Michael Hanna
Life of this patent
Estimating the term…
Abstract
A system is provided for an aircraft. This aircraft system includes a propulsor rotor and a powerplant configured to drive rotation of the propulsor rotor. The powerplant includes a turbine section, a flowpath, a first fuel system and a second fuel system fluidly independent of the first fuel system. The turbine section includes a turbine rotor. The flowpath extends through the turbine section from an inlet into the flowpath to an exhaust from the flowpath. The first fuel system is configured to direct first fuel into the flowpath between the inlet and the turbine rotor. The second fuel system is configured to direct second fuel into the flowpath between the inlet and the turbine rotor.
Claims20
A system for an aircraft, comprising:
- a propulsor rotor;
- and
- a powerplant configured to drive rotation of the propulsor rotor, the powerplant including a turbine section, a flowpath, a first fuel system and a second fuel system fluidly independent of the first fuel system, the turbine section comprising a turbine rotor, the flowpath extending through the turbine section from an inlet into the flowpath to an exhaust from the flowpath, the first fuel system configured to direct first fuel into the flowpath between the inlet and the turbine rotor, and the second fuel system configured to direct second fuel into the flowpath between the inlet and the turbine rotor.
A system for an aircraft, comprising:
- a propulsor rotor;
- a powerplant configured to drive rotation of the propulsor rotor, the powerplant including a turbine section, a flowpath, a first fuel system and a second fuel system, the turbine section comprising a turbine rotor, the flowpath extending through the turbine section, the flowpath including a first combustion zone and a second combustion zone between the first combustion zone and the turbine rotor, the first fuel system configured to deliver first fuel to the first combustion zone, and the second fuel system configured to deliver second fuel to the second combustion zone;
- a first controller configured to control operation of the first fuel system;
- and
- a second controller configured to control operation of the second fuel system independent of the first controller.
A system for an aircraft, comprising:
- a propulsor rotor;
- a powerplant configured to drive rotation of the propulsor rotor, the powerplant including a turbine section, a flowpath, a first fuel system and a second fuel system, the turbine section comprising a turbine rotor, the flowpath extending through the turbine section, the flowpath including a first combustion zone and a second combustion zone between the first combustion zone and the turbine rotor, the first fuel system configured to deliver first fuel to the first combustion zone, and the second fuel system configured to deliver second fuel to the second combustion zone;
- a first controller configured to control operation of the first fuel system;
- and
- a user interface configured to control operation of the second fuel system independent of the first controller.
Dependencies are inferred from the claim text.