CN211711101U - Cabin pressurization oxygen supply system based on motor-driven compressor - Google Patents
Cabin pressurization oxygen supply system based on motor-driven compressor Download PDFInfo
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- CN211711101U CN211711101U CN201922076178.5U CN201922076178U CN211711101U CN 211711101 U CN211711101 U CN 211711101U CN 201922076178 U CN201922076178 U CN 201922076178U CN 211711101 U CN211711101 U CN 211711101U
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Abstract
The utility model discloses a cabin pressure boost oxygen system based on motor drive compressor, which comprises a temperature sensor, a first electric control valve, a Venturi voltage stabilizer, a first flow sensor, a hollow fiber membrane separator, an oxygen concentration sensor, a second electric control valve, a compressor, a motor, a cooler, a second temperature sensor, a third electric control valve, a second flow sensor and a controller; the utility model discloses regard as oxygen nitrogen separation mode with the hollow fiber membrane to make full use of passenger cabin is to supplying with gaseous pressure requirement, uses by motor drive's compressor, and the oxygen-enriched gas with hollow fiber membrane air separator separation retrieves, supplies with the passenger cabin after the pressure boost. The utility model has the advantages of small, reduce engine bleed volume, engine bleed high-usage, the system is simple, the reliability is high, improve passenger cabin environmental comfort, has accorded with aircraft passenger cabin pressure boost oxygen system's development direction better.
Description
Technical Field
The utility model relates to an aeronautical system technical field especially relates to a passenger cabin pressure boost oxygen system based on motor drive compressor.
Background
The aviation physiology research shows that if a person is exposed to a high-altitude low-pressure environment for a long time, symptoms such as high-altitude decompression, high-altitude anoxia and the like occur, the middle ear is easily damaged due to large-amplitude frequent pressure fluctuation or pressure change in a cabin, and the life is threatened under severe conditions. The cabin must therefore be pressurized to raise the cabin air oxygen partial pressure to ensure that the occupants do not react to hypoxia. For civil aircraft with longer endurance, it is generally chosen to maintain the ambient cabin pressure at a level equivalent to 2400m or less. At present, effective measures for overcoming high altitude anoxia mainly comprise two measures, namely adopting a pressurized cabin to enable members to be at the height of the cabin without anoxia, and improving the oxygen concentration in inspiration to enable the oxygen partial pressure to reach a specified level.
At present, the mainstream large passenger aircraft adopts an air supply mode of air bleed of an aircraft engine, and the bleed air enters a cabin after the pressure and the temperature of an environment control system are adjusted, so that a relatively suitable environment is created for passengers. Because the oxygen concentration in the bleed air of the engine at different altitudes is kept basically constant (the volume concentration of nitrogen is 78 percent and the volume concentration of oxygen is 21 percent), the oxygen partial pressure level of the cabin cannot be effectively improved by the method, the oxygen partial pressure of passengers can be ensured to be only increased by the pressure of the cabin, the structural strength and the bleed air quantity requirement of the cabin are increased, and the fuel compensation loss is increased.
Meanwhile, an on-board nitrogen generation system in a fuel tank inerting system needs to bleed air from an engine, and due to the limitation of separation efficiency, the obtained product air only accounts for a small part of the total bleed air amount, and most of the product air is discharged as waste gas, so that large compensation loss is caused. Such as: when nitrogen is prepared by using a membrane separation technology, when the volume fraction of the generated nitrogen-rich gas is 95%, the corresponding volume fraction of the oxygen-rich gas is as high as about 35%, and the oxygen-rich gas is generally taken as exhaust gas to be discharged outside the engine and wasted, so that the utilization of bleed air of the engine is insufficient. Therefore, if the exhaust gas (oxygen-enriched gas) of the nitrogen making system can be used for pressurization and oxygen supply of the cabin after pressurization treatment, the air-entraining amount of an aircraft engine can be greatly reduced, the separation efficiency of the membrane nitrogen making system can be improved, the environmental comfort of the cabin can be improved, the pressure of the cabin is reduced, the danger of explosion decompression and the strength requirement on the body structure are reduced, however, the pressure condition of the oxygen-enriched gas generated by the nitrogen making system cannot meet the condition of directly introducing the oxygen-enriched gas into the cabin, and certain technical difficulty exists in the pressurization and oxygen supply of the cabin by using the oxygen-enriched gas.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that to the defect that involves in the background art, in order to overcome that the engine bleed air volume of current aircraft is big, compensation loss is high, the dangerous not enough such as big of blasting decompression, provide a pressure boost oxygen system of area by motor drive compressor.
The utility model discloses a solve above-mentioned technical problem and adopt following technical scheme:
the cabin pressurization oxygen supply system based on the motor-driven compressor is characterized by comprising a first temperature sensor, a first electric control valve, a Venturi pressure stabilizer, a first flow sensor, a hollow fiber membrane separator, an oxygen concentration sensor, a second electric control valve, a compressor, a motor, a cooler, a second temperature sensor, a third electric control valve, a second flow sensor and a controller;
the hollow fiber membrane separator comprises a mixed gas inlet, an oxygen outlet and a nitrogen outlet, and is used for separating the mixed gas entering from the mixed gas inlet into oxygen-enriched gas and nitrogen-enriched gas and then respectively outputting the oxygen-enriched gas and the nitrogen-enriched gas through the oxygen outlet and the nitrogen outlet;
one end of the first electric control valve is connected with the engine bleed air through a pipeline, and the other end of the first electric control valve, the Venturi pressure stabilizer and the mixed gas inlet of the hollow fiber membrane separator are sequentially connected through pipelines;
the nitrogen outlet of the hollow fiber membrane separator is connected with an oil tank pipeline of the airplane through the second electric control valve; an oxygen outlet of the hollow fiber membrane separator, a compressor, a cooler and one end of a third electric control valve are connected in sequence through pipelines;
the other end of the third electric control valve is communicated with the aircraft cabin through a pipeline;
the motor is used for driving the compressor to work;
the first temperature sensor is arranged in a pipeline between the first electric control valve and engine bleed air; the first flow sensor is arranged in a pipeline between the Venturi pressure stabilizer and the hollow fiber membrane separator; the second temperature sensor is arranged in a pipeline between the cooler and the third electric control valve; the second flow sensor is arranged in a pipeline between the third electric control valve and the cabin; the oxygen concentration sensor is arranged in a pipeline between the hollow fiber membrane separator and the second electric control valve;
the controller is respectively electrically connected with the first temperature sensor, the second temperature sensor, the first flow sensor, the second flow sensor, the oxygen concentration sensor, the motor, the first electric control valve, the second electric control valve and the third electric control valve, and is used for acquiring the sensing information of the first temperature sensor, the second temperature sensor, the first flow sensor, the second flow sensor and the oxygen concentration sensor and controlling the motor, the first electric control valve, the second electric control valve and the third electric control valve to work.
The utility model adopts the above technical scheme to compare with prior art, have following technological effect:
the utility model discloses use motor drive compressor, retrieve the gas that the hollow fiber membrane separator discharged. The system has no special oxygen-making equipment, and the oxygen-enriched gas discharged by the hollow fiber membrane separator is pressurized, cooled and adjusted to meet the condition of feeding into the cabin by a compressor and a cooler; the requirement on the air entraining quantity of the engine is reduced; the utilization efficiency of the air entraining amount of the engine is improved; the environmental comfort of the cabin is improved; the strength requirement on the machine body structure is reduced, and the economy is improved; the system has reliable operation, small volume, light weight and feasible manufacture, and meets the requirements of airborne equipment. The device can be applied to various civil aircrafts and is taken as airborne equipment for coupling cabin pressurization oxygen supply and oil tank inerting safety protection measures.
Drawings
Fig. 1 is a schematic view of the cabin pressurization oxygen supply system based on the motor-driven compressor of the present invention.
In the figure, 1-first temperature sensor, 2-first electric control valve, 3-Venturi stabilizer, 4-first flow sensor, 5-hollow fiber membrane separator, 6-oxygen concentration sensor, 7-second electric control valve, 8-oil tank, 9-compressor, 10-motor, 11-cooler, 12-second temperature sensor, 13-third electric control valve, 14-second flow sensor, 15-cabin, 16-controller.
Detailed Description
The technical scheme of the utility model is further explained in detail with the attached drawings as follows:
the present invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, components are exaggerated for clarity.
As shown in fig. 1, the utility model discloses a cabin pressure boost oxygen supply system based on motor-driven compressor, which comprises a first temperature sensor, a first electric control valve, a venturi stabilizer, a first flow sensor, a hollow fiber membrane separator, an oxygen concentration sensor, a second electric control valve, a compressor, a motor, a cooler, a second temperature sensor, a third electric control valve, a second flow sensor and a controller;
the hollow fiber membrane separator comprises a mixed gas inlet, an oxygen outlet and a nitrogen outlet, and is used for separating the mixed gas entering from the mixed gas inlet into oxygen-enriched gas and nitrogen-enriched gas and then respectively outputting the oxygen-enriched gas and the nitrogen-enriched gas through the oxygen outlet and the nitrogen outlet;
one end of the first electric control valve is connected with the engine bleed air through a pipeline, and the other end of the first electric control valve, the Venturi pressure stabilizer and the mixed gas inlet of the hollow fiber membrane separator are sequentially connected through pipelines;
the nitrogen outlet of the hollow fiber membrane separator is connected with an oil tank pipeline of the airplane through the second electric control valve; an oxygen outlet of the hollow fiber membrane separator, a compressor, a cooler and one end of a third electric control valve are connected in sequence through pipelines;
the other end of the third electric control valve is communicated with the aircraft cabin through a pipeline;
the motor is used for driving the compressor to work;
the first temperature sensor is arranged in a pipeline between the first electric control valve and engine bleed air; the first flow sensor is arranged in a pipeline between the Venturi pressure stabilizer and the hollow fiber membrane separator; the second temperature sensor is arranged in a pipeline between the cooler and the third electric control valve; the second flow sensor is arranged in a pipeline between the third electric control valve and the cabin; the oxygen concentration sensor is arranged in a pipeline between the hollow fiber membrane separator and the second electric control valve;
the controller is respectively electrically connected with the first temperature sensor, the second temperature sensor, the first flow sensor, the second flow sensor, the oxygen concentration sensor, the motor, the first electric control valve, the second electric control valve and the third electric control valve, and is used for acquiring the sensing information of the first temperature sensor, the second temperature sensor, the first flow sensor, the second flow sensor and the oxygen concentration sensor and controlling the motor, the first electric control valve, the second electric control valve and the third electric control valve to work.
The utility model also discloses a working method of this passenger cabin pressure boost oxygen system based on motor drive compressor contains following specific step:
after flowing through a temperature sensor and a first electric control valve, bleed air of an aircraft engine flows through a first flow sensor after being stabilized and stabilized in a Venturi pressure stabilizer and is separated into nitrogen-rich gas and oxygen-rich gas through a hollow fiber membrane separator, wherein the nitrogen-rich gas flows through an oxygen concentration sensor and a second electric control valve and then is introduced into an aircraft oil tank for inerting; the oxygen-enriched gas is compressed in the compressor and then flows through the cooler for cooling; the cooled oxygen-enriched gas flows into the cabin through the temperature sensor, the third electric control valve and the second flow sensor and is output as oxygen for passengers to breathe;
the first temperature sensor detects the temperature of engine bleed air and transmits a signal to the controller, and when the temperature of the engine bleed air is greater than a preset first temperature threshold value, the controller outputs a control signal to the first electric control valve to close the first electric control valve;
the second temperature sensor detects the temperature of the cooled oxygen-enriched gas and transmits a signal to the controller, and when the temperature of the oxygen-enriched gas is greater than a preset second temperature threshold value, the controller outputs a control signal to the third electric control valve to close the third electric control valve;
the first flow sensor and the second flow sensor detect the gas flow and transmit signals to the controller for analyzing and judging the working condition of the system;
the oxygen concentration sensor detects the oxygen concentration in the nitrogen-rich gas and transmits a signal to the controller, and when the oxygen concentration in the nitrogen-rich gas is greater than a preset oxygen concentration threshold value, the controller outputs a control signal to the second electric control valve to close the second electric control valve;
the controller controls the opening and closing degree of the third electric control valve according to whether the cooled oxygen-enriched gas meets the oxygen supply pressure and temperature conditions of the cabin.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
The above-mentioned embodiments further describe the objects, technical solutions and advantages of the present invention in detail, it should be understood that the above description is only the embodiments of the present invention, and is not intended to limit the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (1)
1. The cabin pressurization oxygen supply system based on the motor-driven compressor is characterized by comprising a first temperature sensor, a first electric control valve, a Venturi pressure stabilizer, a first flow sensor, a hollow fiber membrane separator, an oxygen concentration sensor, a second electric control valve, a compressor, a motor, a cooler, a second temperature sensor, a third electric control valve, a second flow sensor and a controller;
the hollow fiber membrane separator comprises a mixed gas inlet, an oxygen outlet and a nitrogen outlet, and is used for separating the mixed gas entering from the mixed gas inlet into oxygen-enriched gas and nitrogen-enriched gas and then respectively outputting the oxygen-enriched gas and the nitrogen-enriched gas through the oxygen outlet and the nitrogen outlet;
one end of the first electric control valve is connected with the engine bleed air through a pipeline, and the other end of the first electric control valve, the Venturi pressure stabilizer and the mixed gas inlet of the hollow fiber membrane separator are sequentially connected through pipelines;
the nitrogen outlet of the hollow fiber membrane separator is connected with an oil tank pipeline of the airplane through the second electric control valve; an oxygen outlet of the hollow fiber membrane separator, a compressor, a cooler and one end of a third electric control valve are connected in sequence through pipelines;
the other end of the third electric control valve is communicated with the aircraft cabin through a pipeline;
the motor is used for driving the compressor to work;
the first temperature sensor is arranged in a pipeline between the first electric control valve and engine bleed air; the first flow sensor is arranged in a pipeline between the Venturi pressure stabilizer and the hollow fiber membrane separator; the second temperature sensor is arranged in a pipeline between the cooler and the third electric control valve; the second flow sensor is arranged in a pipeline between the third electric control valve and the cabin; the oxygen concentration sensor is arranged in a pipeline between the hollow fiber membrane separator and the second electric control valve;
the controller is respectively electrically connected with the first temperature sensor, the second temperature sensor, the first flow sensor, the second flow sensor, the oxygen concentration sensor, the motor, the first electric control valve, the second electric control valve and the third electric control valve, and is used for acquiring the sensing information of the first temperature sensor, the second temperature sensor, the first flow sensor, the second flow sensor and the oxygen concentration sensor and controlling the motor, the first electric control valve, the second electric control valve and the third electric control valve to work.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922076178.5U CN211711101U (en) | 2019-11-27 | 2019-11-27 | Cabin pressurization oxygen supply system based on motor-driven compressor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922076178.5U CN211711101U (en) | 2019-11-27 | 2019-11-27 | Cabin pressurization oxygen supply system based on motor-driven compressor |
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| CN211711101U true CN211711101U (en) | 2020-10-20 |
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| CN201922076178.5U Active CN211711101U (en) | 2019-11-27 | 2019-11-27 | Cabin pressurization oxygen supply system based on motor-driven compressor |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114275164A (en) * | 2022-01-18 | 2022-04-05 | 中国兵器工业集团第二一四研究所苏州研发中心 | High-altitude continuous oxygen supply pressure regulation and control system and method |
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2019
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114275164A (en) * | 2022-01-18 | 2022-04-05 | 中国兵器工业集团第二一四研究所苏州研发中心 | High-altitude continuous oxygen supply pressure regulation and control system and method |
| CN114275164B (en) * | 2022-01-18 | 2023-10-20 | 中国兵器工业集团第二一四研究所苏州研发中心 | High-altitude continuous oxygen supply pressure regulation and control system and method |
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