Oxygen supply device and method for supplying a passenger cabin of an aircraft with oxygen

Abstract

An oxygen supply device for an aircraft has a reaction tank for chemical oxygen generation and a pressurized tank filled with oxygen. The oxygen supply device also has an energy converter for converting thermal energy into electrical energy and also a control unit for setting a first amount of oxygen, provided by the reaction tank to a consumer unit, and a second amount of oxygen, provided by the pressurized tank to the consumer unit. The energy converter is designed to convert a thermal energy, generated by the chemical oxygen generation in the reaction tank, into electrical energy and to provide the electrical energy. The control unit is designed to set the second amount of oxygen, provided by the pressurized tank to the consumer unit, by using the electrical energy provided by the energy converter. The invention also relates to a method for supplying a passenger cabin of an aircraft with oxygen.

Claims

1. An oxygen supply device for an aircraft, comprising: a reaction tank for chemical oxygen generation; a pressurized tank filled with oxygen; an energy converter for converting thermal energy into electrical energy; and a control unit for setting an amount of oxygen provided by the pressurized tank to a consumer unit; wherein the energy converter is configured to convert a thermal energy generated by the chemical oxygen generation in the reaction tank into electrical energy and to provide the electrical energy, and wherein the control unit is configured to set the amount of oxygen provided by the pressurized tank to the consumer unit by using the electrical energy provided by the energy converter.

2. The oxygen supply device according to claim 1, further comprising: a sensing unit for sensing a measured value, wherein the measured value that is sensed corresponds to a flow of oxygen from the reaction tank; and/or wherein the measured value that is sensed corresponds to an ambient pressure in the aircraft; and/or wherein the measured value that is sensed corresponds to an operating time of the control unit.

3. The oxygen supply device according to claim 2, wherein the control unit is configured to set the second amount of oxygen, provided by the pressurized tank to the consumer unit, in dependence on the measured value that is sensed.

4. The oxygen supply device according to claim 1, further comprising: an energy storage unit configured to store the electrical energy provided by the energy converter and provide it to the control unit.

5. The oxygen supply device according to claim 4, wherein an activation of the control unit is only performed when a prescribed state of charge of the energy storage unit is reached.

6. The oxygen supply device according to claim 1, wherein the control unit is configured to provide a minimum flow of oxygen from the reaction tank and/or from the pressurized tank to the consumer unit of the aircraft during a prescribed time period.

7. The oxygen supply device according to claim 1, wherein the control unit is configured to set the second amount of oxygen, provided by the pressurized tank to the consumer unit, continuously by a control valve, so that, as the provision of the first amount of oxygen falls, the second amount of oxygen provided increases.

8. The oxygen supply device according to claim 1, wherein the reaction tank is configured to provide the first amount of oxygen to the consumer unit over a time period of at least 10 minutes; and/or wherein the pressurized tank is configured to provide the second amount of oxygen to the consumer unit over a time period of at least 50 minutes.

9. An aircraft with an oxygen supply device according to claim 1 for supplying a passenger cabin of the aircraft with oxygen.

10. A method for supplying a passenger cabin of an aircraft with oxygen, comprising: providing a first amount of oxygen, obtained from a chemical reaction in a reaction tank, the first amount of oxygen set by a control unit; providing a second amount of oxygen, stored in a pressurized tank, the second amount of oxygen set by the control unit; converting, by an energy converter, thermal energy, generated by the chemical reaction, into electrical energy; and using, by the control unit, the electrical energy for setting the second amount of oxygen, provided by the pressurized tank, to a consumer unit.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1 shows an oxygen supply device according to an exemplary embodiment of the invention.

(2) FIG. 2 shows an aircraft with an oxygen supply device according to an exemplary embodiment of the invention.

(3) FIG. 3 shows a flow diagram for a method for supplying a passenger cabin of an aircraft with oxygen.

DETAILED DESCRIPTION

(4) The representations in the figures are schematic and not to scale.

(5) If the same reference signs are used in various figures in the following description of the figures, these reference signs denote identical or similar elements. However, identical or similar elements may also be denoted by different reference signs.

(6) FIG. 1 shows a circuit diagram of an oxygen supply device 10. The oxygen supply device 10 may be part of an aircraft, in particular part of a passenger aircraft. The oxygen supply device 10 has a reaction tank 11 for chemical oxygen generation and a pressurized tank 12 filled with oxygen. The oxygen supply device 10 also has an energy converter 13 for converting thermal energy into electrical energy, in particular into electrical power. A voltage transformer 18 of the oxygen supply device 10 is designed to set a certain voltage on the basis of the electrical power generated by the energy converter 13. The electrical energy provided by the voltage transformer 18 and/or provided by the energy converter 13 may be stored in an energy store 17 and subsequently fed to a control unit of the oxygen supply device 10 or be fed directly to the control unit 14.

(7) The control unit 14 may set or regulate a first amount of oxygen, provided by the reaction tank 11 to a consumer unit 15, and/or a second amount of oxygen, provided by the pressurized tank 12 to the consumer unit 15. In particular, a first flow of oxygen 21a, from the reaction tank 11 to the consumer unit 15, and/or a second flow of oxygen 22a, from the pressurized tank 12 to the consumer unit 15, can be set by the control unit 14. The electrical energy provided by the energy converter 13 is used for this setting that is carried out by means of the control unit 14. It is possible that the control unit 14 only sets the second amount of oxygen, provided by the pressurized tank 12 to the consumer unit 15, by using the electrical energy provided by the energy converter 13, and consequently does not need an external energy source.

(8) The oxygen supply device 10 has a sensing unit 16 for sensing a measured value, it also being possible for the sensing unit 16 itself to be supplied with the electrical energy provided by the energy converter 13. The sensing unit 16 has a sensor 16a, for measuring the flow of oxygen 21a through a first line 21. The first line 21 in this case connects the reaction tank 11 to the consumer unit 15. The sensing unit 16 has an altitude sensor 16b in the form of a pressure sensor 16b for measuring an ambient pressure, and consequently the flying altitude of the aircraft. A pressure sensor 16b for measuring a current pressure within a passenger cabin of the aircraft may also be provided.

(9) The sensors 16a, 16b may be connected to the control unit 14 by way of data lines 30 in order to supply the control unit 14 with data, in particular with the measured values measured by the sensors 16a, 16b.

(10) Further signal lines or data lines 30 connect the control unit 14 to a control valve 19, so that the control valve 19 can be activated by the control signals provided by the control unit 14 in such a way that the second flow of oxygen 22a, from the pressurized tank 12 to the consumer unit 15, can be set. In this case, an electrical ignition device 19a may initiate an activation of the pressurized tank 12 likewise by control signals, that is to say start or initiate the second flow of oxygen 22a. A second line 22 connects the pressurized tank 12 to the consumer unit 15. The activation of the control valve 19 and the ignition device 19a by the control unit 14 in this case takes place by using, preferably exclusively using, the electrical energy provided by the energy converter 13. The control unit 14 sets the second amount of oxygen, provided by the pressurized tank 12 to the consumer unit 15, that is to say the second flow of oxygen 22a through the second line 22, in dependence on the measured values sensed by the sensing unit 16.

(11) The first line 21 and the second line 22 converge into a third line 23, before the third line 23 finally ends in the consumer unit 15.

(12) The control unit 14 is designed to provide a minimum flow of oxygen from the reaction tank 11 and/or from the pressurized tank 12 to the consumer unit 15 of the aircraft during a prescribed time period, in which the first flow of oxygen 21a through the first line 21 and/or the second flow of oxygen 22a through the second line 22 are regulated such that the flow of oxygen through the third line 23 does not go below a minimum limit value.

(13) The control unit 14 is also designed to set the second amount of oxygen, provided by the pressurized tank 12 to the consumer unit 15, continuously by means of the control valve 19 in such a way that, as the first flow of oxygen 21a falls, the second flow of oxygen 22a is increased. It may however also be provided that the control valve 19 is only opened to provide the second flow of oxygen 22a when the first flow of oxygen 21a goes below a limit value, which is established by the sensor 16a.

(14) FIG. 2 shows an aircraft 100 with an oxygen supply device 10 for supplying a passenger cabin 110 of the aircraft 100 with oxygen, in particular with emergency oxygen, by way of the consumer unit 15 (not represented). It may in this case be provided that the emergency oxygen is provided to the passengers of the aircraft 100 by way of breathing masks, it being possible for the consumer unit 15 to have a multiplicity of breathing masks.

(15) FIG. 3 shows a flow diagram of a method for supplying a passenger cabin 110 of an aircraft 100 with oxygen. In a step S1 of the method, a first amount of oxygen, obtained from a chemical reaction in a reaction tank 11, is provided. In a further step S2, a second amount of oxygen, stored in a pressurized tank 12, is provided. In a further step S3, a thermal energy generated by the chemical reaction is converted into electrical energy. This electrical energy is subsequently used in a further step S4 for setting the second amount of oxygen, provided by the pressurized tank 12, to a consumer unit 15.

(16) It is additionally pointed out that “comprising” does not rule out other elements or steps, and “a” or “an” does not rule out a multiplicity. It is also pointed out that features or steps that have been described with reference to one of the above exemplary embodiments may also be used in combination with other features or steps of other exemplary embodiments described above. Reference designations in the claims are not to be regarded as restrictive.

(17) While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.