Method and system for cross engine debris avoidance
A propulsion system for an aircraft includes at least two propulsion engines. Each propulsion engine rotates about a longitudinal rotational axis, and a propulsive fan associated with each propulsion engine rotates in a plane perpendicular to the longitudinal rotational axis. Each plane is at least one of spaced axially along a fuselage of the aircraft and canted such that each plane does not intersect any other plane associated with another propulsion engine and propulsive fan.
1. A fixed-wing aircraft comprising:
a fuselage, a first wing extending outwardly from a first side of the fuselage, and a second wing extending outwardly from a second, opposite side of the fuselage;
first and second propulsion engines, the first propulsion engine being connected to the first wing and the second propulsion engine being connected to the second wing, each of the first and second propulsion engines rotating about a respective longitudinal rotational axis;
a propulsive fan associated with each of the first and second propulsion engines rotating in a plane perpendicular to the respective longitudinal rotational axis, each plane positioned at least one of spaced axially along a longitudinal axis of the aircraft and canted such that each plane does not intersect any other propulsion engine or propulsive fan, wherein said first propulsion engine is axially spaced from said second propulsion engine and canted away from said second propulsion engine.
2. The aircraft of claim 1 , wherein said second propulsion engine is canted.
3. The aircraft of claim 2 , wherein said first propulsion engine and said second propulsion engine are canted in the same direction.
4. The aircraft of claim 2 , wherein said first propulsion engine and said second propulsion engine are canted in different directions.
5. A fixed-wing aircraft comprising:
a fuselage, a first wing extending outwardly from a first side of the fuselage, and a second wing extending outwardly from a second, opposite side of the fuselage;
first and second propulsion engines, the first propulsion engine being connected to the first wing and the second propulsion engine being connected to the second wing, each of the first and second propulsion engines rotating about a respective longitudinal rotational axis;
a propulsive fan associated with each of the first and second propulsion engines rotating in a plane perpendicular to the respective longitudinal rotational axis, each plane positioned at least one of spaced axially along a longitudinal axis of the aircraft and canted such that each plane does not intersect any other, propulsion engine or propulsive fan, wherein said first propulsion engine is axially spaced from said second propulsion engine and canted towards said second propulsion engine.
6. The aircraft of claim 1 , wherein said first and second propulsion engines are prop-fan engines, each prop-fan engine being dual propeller, contra-rotating, including a front propeller and an aft propeller.
7. The aircraft of claim 1 , wherein at least one of said first and second propulsion engines is canted at a toe angle ranging from about 20 degrees inboard to about 20 degrees outboard.
8. The aircraft of claim 1 , wherein each of said first and second propulsion engines is operated at different thrust levels to compensate for asymmetric torques resulting from at least one of said axial spacing and canting of each of said first and second propulsion engines.
9. A method for mounting a propulsion system comprising first and second propulsion engines on a fixed-wing aircraft having a fuselage and a first wing extending outwardly from a first side of the fuselage and a second wing extending outwardly from a second, opposite side of the fuselage, wherein each first and second propulsion engines rotates about a longitudinal rotational axis, the first propulsion engine being axially spaced from the second propulsive engine, a propulsive fan associated with each of the first and second propulsion engines rotate in a plane perpendicular to the longitudinal rotational axis, the plane defines a debris path, and an aft propeller is associated with each of said first and second propulsion engines, the method comprising:
spacing each plane associated with each of the first and second propulsion engines axially along a longitudinal axis of the aircraft; and
canting at least one plane associated with at least one of the first and second propulsion engines, such that the first propulsion engine is canted away from the second propulsion engine;
wherein each plane and resulting debris path do not intersect any other propulsion engine or propulsive fan; and
wherein said aft propeller is axially aft of said propulsive fan.
10. The method of claim 9 , wherein said aft propeller associated with each of said first and second propulsion engines rotates.
11. The method of claim 10 , wherein the first propulsion engine and the second propulsion engine are canted.
12. The method of claim 11 , wherein the first propulsion engine and the second propulsion engine are canted in the same direction, and wherein the first and second propulsion engines are prop-fan engines, each prop-fan engine being dual propeller, contra-rotating, including a front propeller and an aft propeller.
13. The method of claim 11 , wherein the first propulsion engine and the second propulsion engine are canted in different directions.
14. A method for mounting a propulsion system comprising first and second propulsion engines on a fixed-wing aircraft having a fuselage and a first wing extending outwardly from a first side of the fuselage and a second wing extending outwardly from a second, opposite side of the fuselage, wherein each first and second propulsion engines rotates about a longitudinal rotational axis, the first propulsion engine being axially spaced from the second propulsive engine, a propulsive fan associated with each of the first and second propulsion engines rotate in a plane perpendicular to the longitudinal rotational axis, the plane defines a debris path, and an aft propeller is associated with each of said first and second propulsion engines, the method comprising;
spacing each plane associated with each of the first and second propulsion engines axially along a longitudinal axis of the aircraft; and
canting at least one plane associated with at least one of the first and second propulsion engines, such that the first propulsion engine is canted towards the second propulsion engine;
wherein each plane and resulting debris path do not intersect any other propulsion engine or propulsive fan; and
wherein said aft propeller is axially aft of said propulsive fan.
15. The method of claim 9 , wherein the first and second propulsion engines are prop-fan engines, each prop-fan engine being dual propeller, contra-rotating, including a front propeller and an aft propeller.
16. The method of claim 9 wherein at least one of the first and second propulsion engines is canted at a toe angle ranging from about 1 degree outboard to about 20 degrees outboard.
17. The method of claim 9 , wherein each of the first and second propulsion engines of the propulsion system is operated at different thrust levels to compensate for asymmetric torques resulting from at least one of the axial spacing and canting of each of the first and second propulsion engines.