Optical heat exchanger and associated method

• US 10,641,210 B2
• Filed: 03/13/2018
• Issued: 05/05/2020
• Est. Priority Date: 05/25/2012
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Tillotson, Brian J.
• Primary Examiner(s): Hoang, Michael G
• Application Number:
  US15/919,875
• Publication Number:
  US 20180202392A1
• Time in Patent Office: 784 Days
• Field of Search: 219618, 219628-629, 219200-203, 602001, 602031, 60204-207, 60267, 432 29- 30, 2441711, 2441713-1714, 2441727-1728
• CPC Class Codes: B64D 27/023 of rocket type, e.g. for assisting taking-off or braking
• CPC Class Codes: B64D 37/34 Conditioning fuel, e.g. heating during filling B64D37/18
• CPC Class Codes: B64G 1/401 Liquid propellant rocket engines Ion or plasma engines B64G1/413; Arcjets and other resistojets B64G1/415
• CPC Class Codes: B64G 1/409 Unconventional spacecraft propulsion systems
• CPC Class Codes: F02K 7/08 the jet being continuous
• CPC Class Codes: F02K 99/00 Subject matter not provided for in other groups of this subclass
• CPC Class Codes: F24S 23/30 with lenses
• CPC Class Codes: F24S 40/55 Arrangements for cooling, e.g. by using external heat dissipating means or internal cooling circuits by venting F24S40/53
• CPC Class Codes: F24S 70/60 characterised by the structure or construction absorbing coatings or surface treatment for increasing absorption F24S70/20; auxiliary coatings F24S70/30
• CPC Class Codes: Y02E 10/40 Solar thermal energy, e.g. solar towers
• CPC Class Codes: Y02E 10/44 Heat exchange systems
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An optical heat exchanger and an associated system and method are provided to allow a vehicle, such as an unmanned air vehicle, a rocket or the like, to deliver more payload at a lower cost. The optical heat exchanger includes a support surface defining a plurality of tapered openings. Each tapered opening tapers from the first size proximate an outwardly facing end of the opening to a second smaller size proximate an inwardly facing end of the opening. The inwardly facing end of each tapered opening is in communication with the propellant. The optical heat exchanger also includes a plurality of lenses with each lens positioned proximate the outwardly facing end of a respective opening. Each lens is configured to receive an electromagnetic energy beam and concentrate the majority of the electromagnetic energy beam through the inwardly facing end of the respective tapered opening, thereby heating the propellant.

Claims

1. A system for heating a propellant, the system comprising:

a vehicle carrying the propellant;

an optical heat exchanger carried by the vehicle, wherein the optical heat exchanger comprises;

a support structure defining a plurality of tapered openings, wherein each tapered opening tapers from a first size proximate an outwardly facing end of the opening to a second size, smaller than the first size, proximate an inwardly facing end of the opening; and

a plurality of lenses, each lens positioned proximate the outwardly facing end of a respective tapered opening,

wherein each lens is configured to receive an electromagnetic energy beam and to concentrate and focus a majority of the electromagnetic energy beam through the inwardly facing end of the respective tapered opening without contacting side surfaces of the support structure that define the respective tapered opening, the side surfaces extending between the outwardly facing end and the inwardly facing end of the respective tapered opening, such that the electromagnetic energy beam propagates through the respective tapered opening after having been focused by the respective lens so as to heat the propellant.

2. A system according to claim 1 wherein the vehicle comprises a rocket.

3. A system according to claim 1 wherein the vehicle comprises an unmanned air vehicle.

4. A system according to claim 1 wherein the inwardly facing end of each tapered opening of the plurality of tapered openings is in communication with the propellant.

5. A system according to claim 1 wherein each lens is at least partially seated within the outwardly facing end of the respective tapered opening in such a manner as to also abut adjacent lenses along respective edges thereof.

6. A system according to claim 5 wherein each lens includes a tapered edge, wherein the edge of each lens includes one portion disposed within the respective tapered opening and another portion that extends outside of the tapered opening so as to abut adjacent lenses, and wherein the edge of each lens and sidewalls of the respective tapered opening are tapered at a same angle.

7. A system according to claim 1 wherein the plurality of lenses comprise convex lenses having a focal length that causes the electromagnetic energy beam to be focused through the inwardly facing ends of the respective tapered openings.

8. A system according to claim 1 further comprising an absorber surface in communication with the inwardly facing end of each tapered opening and configured to absorb at least a portion of the electromagnetic energy beam, wherein the absorber surface is also configured to be in contact with the propellant.

9. A system according to claim 1 wherein the support structure is comprised of tungsten.

10. A system according to claim 1 further comprising an absorber surface defining a plurality of corrugations.

11. A system according to claim 10 wherein the plurality of corrugations extend in or are parallel to a direction in which the propellant is configured to flow.

12. A system according to claim 1 wherein the plurality of tapered openings is a first plurality of tapered openings, wherein the support structure further comprises a second plurality of tapered openings, the first and second plurality of tapered openings define a plurality of double tapered-openings tapering inwardly from the outwardly facing end to the inwardly facing end, and tapering outwardly again in a direction toward an interior of the vehicle.

13. A system according to claim 12, wherein the plurality of lenses is a first plurality of lenses, the system further comprising a second plurality of lenses, each lens of the second plurality of lenses positioned proximate the outwardly facing end of the second plurality of tapered openings.

14. A system according to claim 13, wherein the second plurality of lenses are positioned between the second plurality of tapered openings and the propellant.

15. A system according to claim 1 wherein the plurality of lenses comprise first and second lenses positioned proximate the outwardly facing ends of first and second plurality of tapered openings, respectively, wherein the first lens is configured to focus the electromagnetic energy beam along an axis defined by a center axis of the first lens, and wherein the second lens comprises an off-axis lens configured to focus the electromagnetic energy beam to a point offset from the center axis of the second lens in a direction toward the axis defined by the center axis of the first lens, and wherein the inwardly facing end of the second tapered opening with which the off-axis second lens is associated is off-axis relative to the outwardly facing end of the second tapered opening.

16. A system according to claim 1 wherein the plurality of lenses are aligned along a linear axis of the vehicle.

17. A system according to claim 1, wherein the support structure further comprises a reflective coating configured to reflect the electromagnetic energy beam.

18. A system according to claim 1, wherein the support structure defines a duct extending therethrough, wherein the duct is configured to permit coolant to pass therealong.

19. A system according to claim 1, wherein the plurality of lenses comprise rectangular lenses, and wherein the plurality of tapered openings define a plurality of frustopyramidal openings.

20. A system according to claim 1, wherein each lens of the plurality of lenses has at least one dimension that is smaller than a width of the electromagnetic energy beam.