COUNTER SPIRAL TUBE AND SHELL HEAT EXCHANGER

Abstract

A heat exchanger has an outer shell enclosing an inner chamber and extending between a first inlet and a first outlet. The chamber receives a separating wall. The shell extends between axial ends, and generally along a helix. The helix is defined with the wall moving in a continuous manner along a first axial direction and with a circumferential component between the first inlet and the first outlet. A plurality of tubes extend through openings in the separating wall and generally along a helix. The plurality of tubes extend from a second inlet and a second outlet, and with the helix defined along the first axial direction and with a component in a circumferential direction. A method and a temperature control system are also disclosed.

Description

BACKGROUND OF THE INVENTION

This application relates to a unique heat exchanger and a method of forming such a heat exchanger.

Heat exchangers are utilized in any number of applications. In one type of heat exchanger, an outer shell surrounds a plurality of tubes. One fluid is circulated through the outer shell and a second fluid is circulated through the tubes. The two fluids exchange heat with each other, and cooling or heating, or both is achieved.

It is typical that in such a shell and tube heat exchanger the tubes extend along a linear direction. In some applications, one of the two fluids may be in two distinct phases within the heat exchanger. When this occurs, efficient heat transfer between the two fluids raises challenges.

SUMMARY OF THE INVENTION

A heat exchanger has an outer shell enclosing an inner chamber and extending between a first inlet and a first outlet. The chamber receives a separating wall. The shell extends between axial ends, and generally along a helix. The helix is defined with the wall moving in a continuous manner along a first axial direction and with a circumferential component between the first inlet and the first outlet. A plurality of tubes extend through openings in the separating wall and generally along a helix. The plurality of tubes extend from a second inlet and a second outlet, and with the helix defined along the first axial direction and with a component in a circumferential direction.

A method and a temperature control system are also disclosed.

These and other features may be best understood from the following drawings and specification.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 shows a temperature control system in a spaceship.

FIG. 2 shows a detail of a heat exchanger included in the FIG. 1 system.

FIG. 3A is a first view along line 3-3 as shown in FIG. 1.

FIG. 3B shows further details of the cross-section at 3-3.

FIG. 4A shows a first portion of the heat exchanger with tubes omitted.

FIG. 4B is a reverse illustration of fluid flow in the tubes of the heat exchanger.

FIG. 4C shows the structure that forms the reverse portion shown in FIG. 4A.

FIG. 5 schematically shows a manufacturing method.

DETAILED DESCRIPTION

FIG. 1 schematically shows a spaceship 20. A heat exchanger 22 is incorporated into the spaceship. A heat sink 24 draws heat away from elements such as electronics E and passenger or astronaut support systems P.

A refrigerant circuit 25 circulates a refrigerant to cool the heat sink 24. The circuit 25 delivers refrigerant into an inlet 26 in the heat exchanger and outwardly of an outlet 28 to return to the circuit 25. A source of a second coolant 30 communicates with a second inlet 32 and delivers the second fluid to an outlet 34. In this arrangement, the second fluid 30 is stored in a tank on the spaceship, vaporized within the heat exchanger 22 and delivered outwardly of the spacecraft 20 as shown schematically at 36 into a surrounding environment. Of course, in embodiments, the second fluid may be maintained in a closed circuit and not delivered to the atmosphere. Of course, the connection to the inlets 26/32 and outlets 28/34 may be reversed, with the sacrificial fluid utilizing the connections 26/28. Moreover, while the fluids are shown in counter-flow orientation that is flowing in opposed axial directions between axial end 37 of the heat exchanger 22, it may flow in the same axial direction.

FIG. 2 shows an internal detail of the heat exchanger 22. As shown, a chamber 38 is defined by an end wall 39. The heat exchanger 22 is provided with a shell 23 and receives a plurality of tubes 40, shown partially. The tubes 40 extend through a separating wall 42 which forms a portion of the shell 23, as will be explained better below. The tubes 40 extend through holes 43 in the wall 42 and are also shown to extend to holes 44 in the end wall 39. Fluid coming into the inlet 26 moves into chamber 38, and then into the tubes 40. As mentioned above, the fluid may flow in the opposed direction.

The tubes extend continuously along an axial length of the heat exchanger 22. The separating wall 42 extends along an axial length generally between spaced end walls 39.

FIG. 3A shows the shell 23 without the tubes. As shown, the wall 42 has a plurality of holes.

FIG. 3B shows a similar view, but with the tubes 40 extending through the holes 43.

FIG. 4A again shows the shell 23 without the tubes. As can be seen, there are end walls 39 adjacent each axial end 37 of the shell 23. The chamber 38 will communicate with tubes (not shown) extending through the holes 44 in end walls 39. This fluid will then pass through an axial length of the heat exchanger to the chamber 46 and then communicate to the port 28 at an opposed axial end 37.

The shell 23 includes a fluid chamber for receiving a fluid through the inlet 32 and outlet 34, and extending along a helix. It should be understood that this a cross-section and the helix would be generally continuous between its axial ends. The helix is shown schematically between the ports 34 and 32 extending within an axial component and with a circumferential component shown in this embodiment to be counterclockwise from a first axial end towards a second axial end.

FIG. 4B is a reverse model 50 of the flow passages through the tubes 40. That is, it does not show the tubes, but rather the flow passages within the tubes. As shown, flow sections 54 are formed within the chambers 38 and 46. The flow passages through the tubes is shown at 52. As can be appreciated from this figure, the tubes also extend along a helix.

FIG. 4C shows the tubes 40 extending from a straight portion 56 then along a helix and to a second straight portion 58. Straight portion 56 extends to holes 44 in one end wall 39 and the straight portions 58 extends to holes 44 in the other end wall 39. Between the ends, the tubes 40 extend along a helix, as mentioned above.

As shown schematically, in this figure, the helix of the tubes 40 (when considered in the same axial direction as the helix for the shell 23) extends axially and in a circumferentially opposed direction to that of the shell passage. Thus, as illustrated in FIG. 4C from the illustrated top to the illustrated bottom, the helix will be generally clockwise.

By reversing the direction of the two flow passages, better momentum and better heat exchange efficiency is achieved. This becomes particularly valuable when one of the two fluids is a two-phase fluid. The helix configuration improves flow distribution of the two-phase fluid, in turn improving heat exchanger efficiency.

It should be understood, as mentioned with regard to FIG. 1, that the flow between the shell and the tubes may be in an opposed, or the same, axial direction, however, when the structure is looked at along a common axial direction, the shell and the tubes extend through opposed circumferential directions.

In a broader aspect of this disclosure, the two may also extend in a common circumferential direction.

Stated another way, a heat exchanger 22 comprises an outer shell 23 defining an inner chamber and extending between a first inlet and a first outlet. The chamber is defined by a separating wall 42. The shell extends between axial ends 37, and the separating wall 42 extends generally along a helix, with the helix being defined as the wall moving in a continuous manner, and along a first axial direction and with a component in a circumferential direction between the first inlet and the first outlet. A plurality of tubes 40 extend through a plurality of openings 43 in wall 42. The plurality of tubes 40 receive a fluid from a second inlet, and deliver the fluid to a second outlet. The plurality of tubes 40 extend in the first axial direction and with a circumferential component.

When utilized in this disclosure, the term “helix” does not mean a pure mathematical helix. Rather, it is intended to imply a structure which extends along an axial direction and with a circumferential component. Structures coming within the scope of this disclosure may move away from a purely mathematical formula for defining a “helix.”

As can be appreciated, to form such a complex system would be challenging. However, as schematically shown in FIG. 5, applicant has developed a method of forming such a heat exchanger. As shown in FIG. 5, a portion 160 of the outer shell has been formed as has wall portion 162. An end 169 of the wall formed to this point is also shown. As shown, tube portions 166 from a lower end 167 of the wall 160 extend along the helix as mentioned above. Other tube portions 168 are also being formed.

As shown schematically at 70, the formation may be by an additive manufacturing process shown schematically.

Any type of additive manufacturing processes may be used. Such processes build up the heat exchanger through layers. While the buildup is shown extending along the axial direction, the heat exchanger could also be formed by an additive manufacturing process extending from one circumferential side of the shell 23 to the other and forming the flow passages intermediate the two sides.

In particular, electron beam or laser disposition additive manufacturing for metals may be utilized for this method. Laser disposition is particularly beneficial for smaller sized heat exchangers.

The method could be said to comprise forming an outer shell by additive manufacturing, and forming an inner chamber extending between a first inlet and a first outlet. The chamber is formed with a separating wall 43. The shell is formed to extend between axial ends. The separating wall is formed extending generally along a helix, with the wall extending a first axial dimension and with a component in a circumferential direction between the first inlet and the first outlet. A plurality of tubes are also formed extending through the wall. The plurality of tubes are formed generally along a helix to extend in the first axial direction and with a circumferential component.

Although an embodiment of this invention has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this disclosure. For that reason, the following claims should be studied to determine the true scope and content of this disclosure.

Claims

1. A heat exchanger comprising: an outer shell enclosing an inner chamber and extending between a first inlet and a first outlet, with said chamber receiving a separating wall, said shell extending between axial ends, said separating wall extending generally along a helix, with said helix being defined with said separating wall moving in a continuous manner along a first axial direction and with a circumferential component between said first inlet and said first outlet; anda plurality of tubes, said separating wall having a plurality of openings, and said plurality of tubes extending through said openings in said wall and generally along a helix, and said plurality of tubes extending from a second inlet and a second outlet, with the helix defined extending along the first axial direction and with a component in a circumferential direction.

2. The heat exchanger as set forth in claim 1, wherein when looked at along the same said first axial direction, said separating wall circumferential component being in an opposed circumferential direction relative to said circumferential component of said plurality of tubes.

3. The heat exchanger as set forth in claim 1, wherein end walls within said shell separate said inlets and said outlets.

4. The heat exchanger as set forth in claim 3, wherein said end walls have holes and said tubes extend to said holes to deliver a fluid into end chambers defined between said end walls and said second inlet and said second outlet, respectively.

5. The heat exchanger as set forth in claim 1, wherein said first inlet and said first outlet extend circumferentially outwardly through an outer wall of said shell.

6. The heat exchanger as set forth in claim 5, wherein said second inlet and said second outlet extend outwardly through said axial ends of said shell.

7. A method of forming a heat exchanger comprising: forming an outer shell by additive manufacturing and forming an inner chamber extending between a first inlet and a first outlet;forming said chamber with a separating wall;extending said shell between axial endsforming said separating wall extending generally along a helix with the wall extending a first axial direction and with a circumferential component between said first inlet and said first outlet; anda plurality of tubes also formed extending through said separating wall, and said plurality of tubes are formed generally along a helix extending in said first axial direction with a circumferential component.

8. The method as set forth in claim 7, wherein when looked at along the same said first axial direction, said separating wall circumferential component being in an opposed circumferential direction relative to said circumferential component of said plurality of tubes.

9. The method as set forth in claim 7, wherein end walls are formed within said shell separating said inlets and said outlets.

10. The method as set forth in claim 9, wherein said tubes are formed to extend to end chambers defined between said end walls and said second inlet and said second outlet, respectively.

11. The method as set forth in claim 7, wherein said first inlet and said first outlet are formed to extend circumferentially outwardly through an outer wall of said shell.

12. The method as set forth in claim 11, wherein said second inlet and said second outlet are formed to extend outwardly through the axial ends of said shell.

13. A temperature control system for use on a spacecraft comprising: a source of a first fluid, and a heat sink to be cooled, a refrigerant circuit for circulating a second fluid across said heat sink; anda heat exchanger for exchanging heat between the first and second fluid, the heat exchanger including an outer shell enclosing an inner chamber and extending between a first inlet and a first outlet, with said chamber receiving a separating wall, said shell extending between axial ends, said separating wall extending generally along a helix, with said helix being defined with said separating wall moving in a continuous manner along a first axial direction and with a circumferential component between said first inlet and said first outlet; anda plurality of tubes, said separating wall having a plurality of openings, and said plurality of tubes extending through said openings in said wall and generally along a helix, and said plurality of tubes extending from a second inlet and a second outlet, with the helix defined extending along the first axial direction and with a component in a circumferential direction.

14. The system as set forth in claim 13, wherein when looked at along the same said first axial direction, said separating wall circumferential component being in an opposed circumferential direction relative to said circumferential component of said plurality of tubes.

15. The system for use on a spacecraft as set forth in claim 13, wherein there are end walls within said shell separating said inlets and said outlets.

16. The system for use on a spacecraft as set forth in claim 15, wherein said end walls have holes and said tubes extend to said holes to deliver a fluid into end chambers defined between said end walls and said second inlet and said second outlet, respectively.

17. The system for use on a spacecraft as set forth in claim 13, wherein said first inlet and said first outlet extend circumferentially outwardly through an outer wall of said shell, and said second inlet and said second outlet extend outwardly through said axial ends of said shell.

18. The system for use on a spacecraft as set forth in claim 13, wherein said heat sink cools electronics associated with a spaceship.

19. The system for use on a spacecraft as set forth in claim 13, wherein said heat sink providing cooling for systems associated with a passenger on a spacecraft.

20. The system for use on a spacecraft as set forth in claim 13, wherein said first fluid is delivered outwardly of the spaceship into the atmosphere.