CLOSED LOOP ICING CONTROL FOR HEAT EXCHANGERS

Abstract

A heat exchanger has a heat exchanger body, an inlet for a fluid to be cooled, and an outlet for the fluid to be cooled. There is also an inlet for a cooling fluid and an outlet for the cooling fluid. The cooling fluid and the fluid to be cooled connects to the heat exchanger, but are maintained separate in the heat exchanger such that the cooling fluid lowers the temperature of the fluid to be cooled. The cooling fluid and the fluid to be cooled connects to pass through the heat exchanger, but are maintained separate such that the cooling fluid lowers the temperature of the fluid to be cooled. An ice detector detects an undesirable amount of ice particles in the cooling fluid. A control receives information from the ice detector and controls electric heating elements should an undesirable amount of ice particles be detected. An aircraft is also described.

Claims

1. A heat exchanger comprising: a heat exchanger body, an inlet for a fluid to be cooled, and an outlet for the fluid to be cooled; an inlet for a cooling fluid and an outlet for the cooling fluid, the cooling fluid and the fluid to be cooled connected to the heat exchanger, but maintained separate in the heat exchanger, such that the cooling fluid may lower the temperature of the fluid to be cooled; the cooling fluid and the fluid to be cooled connected to pass through the heat exchanger, but maintained separate such that the cooling fluid may lower the temperature of the fluid to be cooled; and an ice detector for detecting an undesirable amount of ice particles in the cooling fluid, and a control for receiving information from said ice detector and controlling electric heating elements should an undesirable amount of ice particles be detected.

2. The heat exchanger as set forth in claim 1, wherein said ice detector is an optical ice detector.

3. The heat exchanger as set forth in claim 1, wherein an ice filter is positioned upstream of said inlet for the cooling fluid for filtering ice particles from the cooling fluid.

4. The heat exchanger as set forth in claim 3, wherein said ice detector is positioned upstream of an ice filter outlet from said ice filter leading into said inlet for the cooling fluid at said heat exchanger.

5. The heat exchanger as set forth in claim 1, wherein said electric heating elements are positioned on an outer face of said heat exchanger.

6. The heat exchanger as set forth in claim 5, wherein crossing members are formed on said outer face and across a flow area into said heat exchanger, and said electric heating elements are also placed on said crossing members.

7. The heat exchanger as set forth in claim 1, wherein a plenum leads to said heat exchanger, and said electric heating elements are placed on said plenum.

8. The heat exchanger as set forth in claim 1, wherein the cooling fluid is air potentially at a temperature below the freezing point of water.

9. The heat exchanger as set forth in claim 8, wherein said air is from outside of an aircraft receiving said heat exchanger.

10. The heat exchanger as set forth in claim 1, wherein said heat exchanger is a fuel oil cooler, with said fluid to be cooled being oil, and said cooling fluid being fuel.

11. An aircraft comprising: an aircraft body enclosing a heat exchanger body, an inlet for a fluid to be cooled, and an outlet for the fluid to be cooled; an inlet for a cooling fluid and an outlet for the cooling fluid, the cooling fluid and the fluid to be cooled connected to the heat exchanger, but maintained separate in the heat exchanger, such that the cooling fluid may lower the temperature of the fluid to be cooled; and an ice detector for detecting an undesirable amount of ice particles in the cooling fluid, and a control for receiving information from said ice detector and controlling electric heating elements should an undesirable amount of ice particles be detected.

12. The aircraft as set forth in claim 11, wherein said ice detector is an optical ice detector.

13. The aircraft as set forth in claim 11, wherein an ice filter is positioned upstream of said inlet for the cooling fluid for filtering ice particles from the cooling fluid.

14. The aircraft as set forth in claim 13, wherein said ice detector is positioned upstream of an outlet from said ice filter leading into said cooling fluid inlet at said heat exchanger.

15. The aircraft as set forth in claim 11, wherein said electric heating elements are positioned on an outer face of said heat exchanger.

16. The aircraft as set forth in claim 11, wherein crossing members are formed on said outer face and across a flow area into said heat exchanger, and said electric heating elements are also placed on said crossing members.

17. The aircraft as set forth in claim 11, wherein a plenum leads to said heat exchanger, and said electric heating elements are placed on said plenum.

18. The aircraft as set forth in claim 11, wherein the cooling fluid is air potentially at a temperature below the freezing point of water.

19. The aircraft as set forth in claim 18, wherein said air is from outside of said aircraft body.

20. The aircraft as set forth in claim 11, wherein said heat exchanger is a fuel oil cooler, with said fluid to be cooled being oil, and said cooling fluid being fuel.

21. The heat exchanger as set forth in claim 1, wherein the undesirable amount of ice particles is in the cooling fluid approaching the heat exchanger.

22. The aircraft as set forth in claim 1, wherein the undesirable amount of ice particles is in the cooling fluid approaching the heat exchanger.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0008] FIG. 1 shows a first heat exchanger and control system.

[0009] FIG. 2 shows a second embodiment.

[0010] FIG. 3 shows an optional feature.

[0011] FIG. 4 shows a detail.

[0012] FIG. 5 shows a detail.

[0013] FIG. 6 shows a detail.

DETAILED DESCRIPTION

[0014] An aircraft 18 is shown schematically in FIG. 1 including a heat exchanger 20. The heat exchanger 20 may include a heat exchanger body 22 and may function as a condenser for a refrigerant system that may be incorporated for use on the aircraft 18. Hot refrigerant to be cooled enters at inlet 24, is cooled within the body 22, and leaves at an outlet 26, having been cooled by cooling air from a duct 28. Duct 28 may be drawn from outside the aircraft, such as shown at 27. This air may be at very low temperatures. It is possible there could be ice particles in this air. The ice particles can decrease the efficiency of operation of the heat exchanger 20. The air enters inlet 38, cools the fluid to be cooled and outlets at 32.

[0015] As known, the flow from inlet 30 to outlet 32 is maintained separate from the flow between inlet 24 and outlet 26.

[0016] An ice detector 34, such an optical ice detector, monitors the cooling air passing toward the inlet 30. Alternatively, the optical detector can detect ice build up on the heat exchanger face. If an undesirable amount of ice particles are detected, the controller 36 will send a signal to actuate a heater 38, which is in the path of flow of the air passing to the inlet 30. This will tend to melt the ice particles, such that the efficiency of the heat exchanger 20 is maintained. The heater 38 may include elements of a resistive nature. When power is applied the wires heat up. Now, the use of the control and heater thus provide a simple and reliable way of decreasing ice particle flow to a heat exchanger when an inlet airflow is at temperatures below the freezing point of water.

[0017] FIG. 2 shows a fuel oil cooler 40 having a heat exchanger body 39. Oil passes from a line 41 into an inlet 42, and across the heat exchanger to an outlet 44, into a return line 45. The oil is at a hot temperature, such as may be found downstream of a lubrication application for the oil. The oil may then pass back to a sump or pump to be utilized again as a lubricant.

[0018] Duct 46 communicates, such as with the fuel supply 47, and connects the fuel to an inlet 48. The fuel passes across the heat exchanger body 39 to an outlet 50 and may then move into a line 51, such as heading to a combustor for a gas turbine engine.

[0019] As known, the fuel may be at very low temperatures and may be below the freezing point of water. Thus, the possibility exists for ice particles to be in the fuel flow heading into the heat exchanger 39.

[0020] Again, an ice detector 52, which in one embodiment is an optical ice detector, senses an amount of ice particles in the flow. A control 54 selectively actuates heater elements 56 to remove the ice particles when they are detected in an undesirable level.

[0021] FIG. 3 shows an optional feature wherein an ice filter 58 is also utilized. The ice filter may include an inlet 60 passing a cooling fluid, which may include ice, to an inner tube 64 and an outlet 66. The ice filter 58 may be utilized in either the FIG. 1 or FIG. 2 embodiment. An ice detector 62 again detects an undue amount of ice in the inlet and may actuate heater elements as in the first two embodiments, such as on the inlet to a heat exchanger.

[0022] FIG. 4 shows a detail of a heat exchanger 100 having a front face 102. The nature of the heater element 104 will be defined by the front face 102. In this embodiment the heater is shown extending around the periphery of the front face 102, and outwardly of a central flow path 103.

[0023] FIG. 5 shows an embodiment 106 wherein the front face 110 has crossing members 112 across the flow area 113 such that heater element 110 can have branches 114 extending across the flow area 113 to provide improved ice management.

[0024] FIG. 6 shown an embodiment 120 wherein a plenum 122 leads to the heat exchanger 130. The plenum has a flow area 124 receiving the cooling fluid, and the heater element 126 may be positioned either at an upstream end 127 or within an inner periphery 129 defining the plenum area 124.

[0025] While the operation of the system as disclosed above indicates the heat element is turned on when an undesirable amount of ice particles are detected, it should be understood that the undesirable amount could be any ice particles. That is, the detection of even a single ice particle could cause operation of the heater element.

[0026] 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.