Off-set duct heat exchanger
A heat exchanger system for a propulsion system inlet duct includes a heat exchanger assembly that is disposed within an inlet duct assembly. The heat exchanger includes a heat exchanger with a front facing area that is greater than an area of the inlet duct that is transverse to a longitudinal length of the inlet duct.
1. A heat exchanger system for a propulsion system inlet duct comprising:
an inlet duct assembly, wherein the inlet duct assembly includes a maximum cross-sectional area defined in a plane taken transverse to a longitudinal length of the inlet duct; and
a heat exchanger assembly disposed in the inlet duct assembly, the heat exchanger assembly having a front facing cross-sectional area that is transverse to the longitudinal length of the inlet duct and that is greater than the maximum cross-sectional area of the inlet duct.
2. The heat exchanger system as recited in claim 1 , wherein the heat exchanger assembly includes a forward portion that is spaced axially forward of a first aft portion and a second aft portion.
3. The heat exchanger system as recited in claim 2 , wherein the front facing cross-sectional area of the heat exchanger comprises combined front facing cross-sectional areas of the forward portion, the first aft portion and the second aft portion.
4. The heat exchanger system as recited in claim 3 , wherein the front facing portion is centered in the inlet duct in a direction transverse to the longitudinal length, the first aft portion is disposed along a first side of the inlet duct and the second portion is disposed along a second side of the inlet duct.
5. The heat exchanger system as recited in claim 3 , wherein each of the forward portion, the first aft portion and the second aft portion have the same size cross-sectional area.
6. The heat exchanger system as recited in claim 1 , wherein the front facing cross-sectional area of the heat exchanger is between 10 and 40 percent larger than the maximum cross-sectional area of the inlet duct.
7. A heat exchanger system for a propulsion system comprising:
an inlet duct assembly, wherein the inlet duct assembly includes a cross-sectional area defined in a plane taken transverse to a longitudinal length of the inlet duct; and
a heat exchanger assembly disposed in the inlet duct assembly, the heat exchanger assembly having a front facing cross-sectional area that is greater than the cross-sectional area of the inlet duct, wherein the inlet duct assembly includes an upper inlet duct and a lower inlet duct and the heat exchanger assembly includes an upper heat exchanger assembly in the upper inlet duct and a lower heat exchanger assembly in the lower inlet duct and a combined front facing cross-sectional area of the upper heat exchanger assembly and the lower heat exchanger assembly is greater than a combined front facing cross-sectional area of the upper inlet duct and the lower inlet duct.
8. The heat exchanger system as recited in claim 7 , wherein the upper inlet duct and the lower inlet duct are differently sized.
9. The heat exchanger system as recited in claim 8 , wherein the upper inlet duct is larger than the lower inlet duct.
10. The heat exchanger system as recited in claim 7 , wherein the upper inlet duct and the lower inlet duct are configured to be in communication with a boundary layer flow of air along outer surfaces of an aircraft structure.
11. An aircraft propulsion system comprising:
a propulsor assembly disposed in an aircraft structure, the propulsor assembly including a propulsive fan rotatable about a fan axis;
a first inlet duct disposed in the aircraft structure forward of the propulsive fan, the first inlet duct having a cross-sectional area in a plane defined transverse to a longitudinal length of the first inlet duct; and
a first heat exchanger assembly disposed in the first inlet duct, the first heat exchanger assembly including a front facing cross-sectional area that is greater than the cross-sectional area of the first inlet duct, wherein the first inlet duct includes a maximum cross-sectional area that is transverse to the longitudinal length of the first the inlet duct and the front facing cross-sectional area of the first heat exchanger is transverse to the longitudinal length of the first inlet duct and is greater than the maximum cross-sectional area of the first inlet duct.
12. The aircraft propulsion system as recited in claim 11 , wherein the first heat exchanger assembly includes a forward portion that is spaced axially forward of a first aft portion and a second aft portion.
13. The aircraft propulsion system as recited in claim 12 , wherein the front facing cross-sectional area of the first heat exchanger assembly comprises a combined front facing cross-sectional area of the forward portion, the first aft portion and the second aft portion.
14. The aircraft propulsion system as recited in claim 13 , wherein the front facing portion is centered in the first inlet duct, the first aft portion is disposed along a first side of the first inlet duct and the second aft portion is disposed along a second side of the first inlet duct.
15. The aircraft propulsion system as recited in claim 11 , wherein the front facing cross-sectional area of the first heat exchanger assembly is between 10 and 40 percent larger than the cross-sectional area of the first inlet duct.
16. The aircraft propulsion system as recited in claim 11 , further including a second heat exchanger assembly in a second inlet duct, the second inlet duct having a cross-sectional area defined in a plane transverse to a longitudinal length of the second inlet duct and the second heat exchanger assembly having a front facing cross-sectional area that is greater than the cross-sectional area of the second inlet duct.
17. The aircraft propulsion system as recited in claim 16 , wherein the second heat exchanger assembly includes a forward portion, spaced axially forward of a first aft portion and second aft portion in the second inlet duct.
18. The aircraft propulsion system as recited in claim 16 , wherein the front facing cross-sectional area of the second heat exchanger assembly is between 10 and 40 percent larger than the cross-sectional area of the second inlet duct.
19. The aircraft propulsion system as recited in claim 16 , wherein a combined front facing cross-sectional area of the first heat exchanger assembly and the second heat exchanger assembly is between 10 and 40 percent larger than a combined cross-sectional area of the first inlet duct and the second inlet duct.
20. A method of assembling an inlet duct for an aircraft propulsion system disposed in an aircraft structure, the method comprising:
assembling a first inlet duct for communicating airflow to a propulsive fan, the first inlet duct assembled to include a maximum cross-sectional area in a plane defined transverse to a longitudinal length of the first inlet duct; and
mounting a first heat exchanger assembly into the first inlet duct forward of the propulsive fan, the first heat exchanger assembly mounted to include a front facing cross-sectional area that is transverse to the longitudinal length and that is greater than the maximum cross-sectional area of the first inlet duct.