Heat recovery system, in particular for use on aircraft, using a two-phase fluid circuit

Abstract

The system comprises at least one evaporator device arranged around a tube inside which a hot fluid flows and, for each evaporator device, a respective conduit connected at its opposite ends to the evaporator device so as to form with the latter a closed circuit containing a two-phase fluid. Each evaporator device comprises a casing, having an inner wall in contact with the respective tube and an outer wall enclosing a cavity with the inner wall, and a separating member of porous material arranged inside the casing so as to divide radially the cavity into an inner cavity, extending between the inner wall and the separating member, and an outer cavity extending between the separating member and the outer wall. Each conduit is in fluid communication at its opposite ends with the inner cavity and with the outer cavity, respectively, of the respective evaporator device so as to allow fluid in vapor phase to flow out from the evaporator device and the fluid in liquid phase to flow back into the evaporator device, respectively.

Claims

1. A heat recovery system for recovering heat from a hot fluid flowing in at least one tube, in particular from hot air drawn from a high-temperature compression stage of an aircraft engine, the system comprising at least one evaporator device arranged around said at least one tube and, for each evaporator device, a respective conduit connected at its opposite ends to the evaporator device so as to form with the latter a closed circuit containing a two-phase fluid, wherein each evaporator device comprises a casing, having an inner wall in contact with the respective tube and an outer wall enclosing a cavity with the inner wall, and a separating member arranged inside the casing so as to divide radially the cavity into an inner cavity, extending between the inner wall and the separating member, and an outer cavity, extending between the separating member and the outer wall, the separating member being made of porous material so as to allow the fluid to flow radially by capillarity through the separating member in the direction from the outer cavity to the inner cavity, wherein the inner wall and the outer wall of each evaporator device are cylindrical walls arranged coaxially with each other and coaxially with the respective tube, wherein the separating member of each evaporator device extends over the entire length of the cavity and is interrupted circumferentially in a connection zone of the cavity, and wherein each conduit is in fluid communication at its opposite ends with the inner cavity and the outer cavity, respectively, of the respective evaporator device so as to allow fluid in vapour phase to flow out of the evaporator device and fluid in liquid phase to flow back into the evaporator device, respectively.

2. The system of claim 1, wherein the separating member of each evaporator device is formed as a tubular element having an axial slit.

3. The system of claim 1, wherein each conduit is connected to the respective evaporator device at one end in the connection zone of the cavity and at the opposite end along the outer cavity, on the diametrically opposite side to the connection zone.

4. The system of claim 1, wherein the outer cavity of each evaporator device is in direct fluid communication with the connection zone of the cavity.

5. The system of claim 1, wherein each evaporator device comprises closure means arranged between the separating member and the outer wall so as to prevent direct fluid communication between the outer cavity and the connection zone of the cavity.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) Further characteristics and advantages of the present invention will appear more clearly from the following detailed description, given purely by way of a non-limiting example, with reference to the accompanying drawings in which:

(2) FIG. 1 shows a side view of a section of the hot air tube on which an evaporator device forming part of a heat recovery system according to the present invention is mounted;

(3) FIG. 2 is an axial-section view through section line II-II of FIG. 1;

(4) FIG. 3 is a cross-section view through section line of FIG. 1; and

(5) FIG. 4 is a cross-section view, similar to that of FIG. 3, showing a variant of embodiment of the present invention.

DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS

(6) With reference first to FIGS. 1 to 3, 10 denotes a hot air tube (only a section of which is shown) through which the hot air drawn from a high-temperature compression stage of an aircraft engine (not shown, but in any case of per-se-known type) flows to be used, after being cooled down to the desired temperature, in an aircraft air-conditioning system. An evaporator device 12 forming part of a heat recovery system according to the present invention is mounted on the hot air tube 10 (hereinafter simply referred to as tube). The evaporator device 12 comprises a sleeve-like casing having an inner wall 14, an outer wall 16 and a pair of end walls 18 which close the sleeve at its opposite axial ends and define, together with the inner wall 14 and the outer wall 16, a cavity 20. The inner wall 14 of the evaporator device 12 is in contact with the wall of the tube 10. Preferably, the inner wall 14 and the outer wall 16 of the evaporator device 12 are cylindrical walls arranged coaxially with each other, as well as coaxially with the tube 10.

(7) A separating member 22 of porous material is arranged inside the evaporator device 12, between the inner wall 14 and the outer wall 16, so as to divide radially the cavity 20 into an inner cavity 20a, extending between the inner wall 14 and the separating member 22, and an outer cavity 20b, extending between the separating member 22 and the outer wall 16. The separating member 22 extends over the entire length (axial dimension) of the cavity 20, while it is interrupted in the circumferential direction so as to connect the inner cavity 20a and the outer cavity 20b with each other in a zone of the cavity 20 indicated 20c (FIG. 3). The separating member 22 is therefore formed as a tubular element with an axial slit (i.e. a slit extending parallel to its axis, coinciding with the axis of the casing of the evaporator device 12).

(8) The heat recovery system further comprises a conduit 24 which is connected at its opposite ends to the evaporator device 12 so as to form with the latter a closed circuit which is filled with a two-phase fluid (such as water, ammonia or propylene). More specifically, the conduit 24 is connected to the evaporator device 12 on one side in the zone 20c of the cavity 20 and on the other side along the outer cavity 20b, preferably on the diametrically opposite side to the zone 20c.

(9) The heat recovery system operates as follows. The fluid in liquid phase which is inside the inner cavity 20a of the evaporator device 12 receives heat from the hot air flowing along the tube 10 and evaporates. The fluid in vapour phase flows out of the evaporator device 12 in the zone 20c of the cavity 20 (as indicated by the arrow OUT in FIGS. 2 and 3) and along the conduit 24 to transfer heat to one or more user appliances served by the heat recovery system. The recovered heat may be used, for example, for heating the fuel or for de-icing purposes, i.e. for heating parts of the aircraft, such as in particular the wings, where formation of ice must be avoided. The fluid then returns in liquid form to the evaporator device 12, namely to the region of the outer cavity 20b (as indicated by the arrow IN in FIGS. 2 and 3) and from here is pushed radially by capillarity through the separating member 22 into the inner cavity 20a, where transition from liquid phase to vapour phase again occurs owing to the heat released by the hot air which flows along the tube 10. A continuous fluid flow is thus established along the conduit 24, which allows the heat extracted from the hot air flowing in the tube 10 to be transferred wherever required, for example to the fuel tanks or to the wings of the aircraft.

(10) With reference now to FIG. 4, in which parts and elements identical or corresponding to those of the preceding figures have been given the same reference numerals, according to a variant of embodiment of the present invention the inner cavity 20a and the outer cavity 20b are not connected with each other in the zone 20c of the cavity 20, but communicate with each other only via the pores of the separating member 22. In this case also, as in the embodiment of FIGS. 1-3, the separating member 22 is interrupted in the circumferential direction (i.e. is formed in the manner of a tubular sleeve having an axial slit) so as to put the inner cavity 20a into communication with the conduit 24. However, differently from the embodiment of FIGS. 1-3, the passage between the outer cavity 20b and the zone 20c of the cavity 20 is closed by closure elements 26, preferably arranged at the free ends of the separating member 22. In this way, therefore, the fluid in liquid phase which is in the outer cavity 20b is forced to flow towards the inner cavity 20a passing through the separating member 22.

(11) Even though the attached drawings show only a single evaporator device, several evaporator devices might clearly be provided on the same hot air tube, each evaporator device being connected to a respective conduit so as to form with the latter a respective closed circuit containing the two-phase fluid. Moreover, in the case where several hot air tubes are provided, the heat recovery system will advantageously comprise at least one evaporator device arranged on each of the hot air tubes.

(12) Finally, even though the invention has been described here with particular reference to its application on aircrafts, in particular in combination with a hot air tube which supplies the air-conditioning system of the aircraft with hot air drawn from a high-temperature compression stage of the aircraft engine, in general it may be applied to any system in which the heat carried by a hot fluid flowing in a tube would otherwise be discharged into the external environment, without being at least partially recovered.

(13) Naturally, the principle of the invention remaining unchanged, the embodiments and the constructional details may vary widely from those described and illustrated purely by way of non-limiting example.