An air-breathing simulation test bench for an aircraft on-board oxygen generation system

Abstract

The application belongs to the technical field of air simulation test of aircraft on-board oxygen generation system, and particularly relates to an air simulation test bench for the aircraft on-board oxygen generation system, which is provided with a ring control cold assembly, a primary heat exchanger, a positive displacement compressor, a secondary heat radiator, an on-board condensation water removal device, a ring control cold assembly exciter and an air source simulation control center, cooperates with corresponding pipelines, valves and sensors, and uses a single high-temperature air source and a low-temperature air source to save, efficiently and conveniently generate oxygen source air with required flow, pressure, temperature and humidity, and supply the on-board oxygen generation system. Therefore, the oxygen source air pressure point and related air parameter range can be accurately determined through test at the beginning of the design of the on-board oxygen generation system.

Description

Technical Field

[0001] This application belongs to the technical field of bleed air simulation test technology for aircraft airborne oxygen generation systems, specifically relating to a bleed air simulation test bench for aircraft airborne oxygen generation systems. Background Technology

[0002] Airborne oxygen generation systems use compressed air from the aircraft as the oxygen source. When the aircraft is in idle mode, the bleed air pressure of the oxygen source may be low, resulting in insufficient bleed air pressure for the oxygen generator. Therefore, it is necessary to determine the bleed air pressure point of the oxygen source and its related bleed air parameter range at the initial design stage of the airborne oxygen generation system. Currently, this is mostly determined through experience or simulation, lacking relevant experimental verification, and thus having low reliability.

[0003] This application is made in view of the aforementioned technical deficiencies.

[0004] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this application, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0005] The purpose of this application is to provide a test bench for bleed air simulation of an aircraft airborne oxygen generation system, in order to overcome or mitigate at least one of the known technical defects.

[0006] The technical solution of this application is:

[0007] A test bench for bleed air simulation of an aircraft airborne oxygen generation system includes:

[0008] The ring-controlled cooling component has its hot-side inlet connected to a high-temperature air source via a pipeline, and its cold-side inlet connected to a low-temperature air source via a pipeline.

[0009] The primary heat exchanger has its hot-side inlet connected to a high-temperature air source via a pipeline, which is equipped with a flow regulating valve; the cold-side inlet of the primary heat exchanger controls the air supply outlet of the cold component via a pipeline connecting to a loop, which is equipped with a first flow regulating valve.

[0010] The positive displacement compressor has its inlet connected to the hot side outlet of the primary heat exchanger via a pipeline, and a first temperature sensor is installed on this pipeline.

[0011] The secondary radiator has its hot-side inlet connected to the outlet of the positive displacement compressor via a pipeline, which is equipped with a temperature and pressure composite sensor; the cold-side inlet of the secondary radiator is connected to the air supply outlet of the cooling component via a pipeline, which is equipped with a second flow control valve.

[0012] The airborne condensate removal device has a cold-side inlet connected to the hot-side outlet of the secondary radiator via a pipeline. A second temperature sensor and a first humidity sensor are installed on this pipeline. The hot-side inlet of the airborne condensate removal device controls the air supply outlet of the cold component through a pipeline connecting loop. A branch is connected in parallel on the hot-side pipeline of the secondary radiator, and a temperature regulating valve is installed on this branch.

[0013] The airborne oxygen generation system has its inlet connected to the outlet of the airborne condensate removal device via a pipeline, and a second humidity sensor is installed on this pipeline.

[0014] The loop-controlled cooling component actuator is connected to the loop-controlled cooling component and is used to control the operating mode and output parameters of the loop-controlled cooling component.

[0015] The gas source simulation control center is connected to the flow regulating valve, the first flow regulating valve, the second flow control valve, the temperature control valve, and the positive displacement compressor. It can control the opening degree of the flow regulating valve, the first flow regulating valve, the second flow control valve, and the temperature control valve, as well as control the working mode of the positive displacement compressor.

[0016] According to at least one embodiment of this application, in the above-mentioned aircraft airborne oxygen generation system bleed air simulation test bench, the airborne oxygen generation system includes:

[0017] The oxygen concentration unit has its inlet connected to the outlet of the onboard condensate removal unit via a pipeline.

[0018] An oxygen concentrator actuator is connected to an oxygen concentrator assembly to control the oxygen production status of the assembly and to monitor and record the pressure and concentration of the produced oxygen.

[0019] The breathing simulation device has its inlet connected to the outlet of the oxygen concentration component via a pipeline, and its outlet is vented through a pipeline.

[0020] According to at least one embodiment of this application, in the above-mentioned aircraft airborne oxygen generation system bleed air simulation test bench, the breathing simulation device includes a mechanical lung and is equipped with a corresponding flow regulating valve for flow control.

[0021] According to at least one embodiment of this application, the above-mentioned aircraft airborne oxygen generation system bleed air simulation test bench further includes:

[0022] The integrated data acquisition system connects various pressure, temperature, flow, and humidity measurement points to collect, record, and display relevant data on pressure, temperature, flow, and humidity.

[0023] According to at least one embodiment of this application, the above-mentioned aircraft airborne oxygen generation system bleed air simulation test bench further includes:

[0024] The dual-channel air supply system has an inlet connected to a compressed air source via pipeline, and an outlet divided into a hot-side outlet and a cold-side outlet. The hot-side outlet provides high-temperature air to the hot-side inlet of the cold component and primary heat exchanger through a pipeline connection loop, while the cold-side outlet provides low-temperature air to the cold-side inlet of the cold component through a pipeline connection loop.

[0025] The dual-channel controller connects to the monitoring devices of the dual-channel gas supply system and controls the pressure, temperature, and flow parameters output by the dual-channel gas supply system.

[0026] According to at least one embodiment of this application, the dual-path air source system in the above-mentioned aircraft airborne oxygen generation system bleed air simulation test bench includes:

[0027] The filter has three outlets: an instrument path, a hot path, and a cold path. The hot path outlet is its hot-side outlet, and the cold path outlet is its cold-side outlet.

[0028] After the filter, the instrument circuit is equipped with a manual gate valve and a pressure reducing valve in sequence.

[0029] The following components are arranged sequentially on the hot path after the filter: a hot path manual gate valve, a hot path primary pressure regulating valve, a hot path flow meter, a hot path flow regulating valve, a hot path electric heating unit group, a hot path pressurized jet type humidity control device, and a hot path high-precision dynamic pressure regulating valve. The hot path electric heating unit group is connected to a hot path power regulator.

[0030] The cold circuit after the filter is sequentially equipped with a cold circuit manual gate valve, a cold circuit primary pressure regulating valve, a cold circuit flow meter, a cold circuit primary flow regulating valve, a cold circuit turbine, and a cold circuit high-precision dynamic pressure regulating valve. The cold circuit turbine is connected in parallel with a cold circuit secondary flow regulating valve.

[0031] This application has at least the following beneficial technical effects:

[0032] A test bench for bleed air simulation of an aircraft airborne oxygen generation system is provided. It is equipped with a loop-controlled refrigeration assembly, a primary heat exchanger, a volumetric compressor, a secondary radiator, an airborne condensation and dehydration device, a loop-controlled refrigeration assembly actuator, and an air source simulation control center. With corresponding pipelines, valves, and sensors, it can generate oxygen bleed air with the required flow rate, pressure, temperature, and humidity using a single high-temperature air source or a low-temperature air source in an economical, efficient, and convenient manner, and supply it to the airborne oxygen generation system. This allows for the accurate determination of the bleed air pressure point and related bleed air parameter range during the initial design of the airborne oxygen generation system. Attached Figure Description

[0033] Figure 1 This is a schematic diagram of the bleed air simulation test bench for the aircraft airborne oxygen generation system provided in the embodiments of this application;

[0034] Figure 2This is a schematic diagram of the bleed air simulation test bench for the aircraft airborne oxygen generation system provided in the embodiments of this application;

[0035] in:

[0036] 1-Loop control cooling assembly; 2-Primary heat exchanger; 3-Flow regulating valve; 4-Polydisplacement compressor; 5-First temperature sensor; 6-Secondary radiator; 7-Temperature and pressure composite sensor; 8-Second flow control valve; 9-Airborne condensate removal device; 10-Second temperature sensor; 11-First humidity sensor; 12-Temperature control valve; 13-Airborne oxygen generation system; 14-Second humidity sensor; 15-First flow regulating valve; 16-Loop control cooling assembly actuator; 17-Gas source simulation control center; 18-Oxygen concentration assembly; 19-Oxygen concentrator actuator; 20-Respiratory simulation device; 21-Integrated data acquisition system; 22-Dual-channel gas source system; 23-Dual-channel controller.

[0037] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the accompanying drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0038] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0039] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0040] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0041] The following is in conjunction with the appendix Figures 1 to 2 This application will be described in further detail.

[0042] A test bench for bleed air simulation of an aircraft airborne oxygen generation system includes:

[0043] The ring-controlled cooling component 1 has a hot-side inlet connected to a high-temperature air source via a pipeline and a cold-side inlet connected to a low-temperature air source via a pipeline. The high-temperature air can simulate compressed air from an aircraft engine or air source system, and the low-temperature air can simulate ram air from an aircraft.

[0044] The primary heat exchanger 2 has its hot-side inlet connected to a high-temperature air source via a pipeline. A flow regulating valve 3 is installed on this pipeline. This high-temperature air source serves as the starting source for the oxygen production source. The flow regulating valve 3 is used to control the flow rate of the oxygen production source to meet the design operating requirements. The cold-side inlet of the primary heat exchanger 2 is connected to the air supply outlet of the loop control cooling component 1 via a pipeline. A first flow regulating valve 15 is installed on this pipeline. The airflow from the air supply outlet of the loop control cooling component 1 is used to initially reduce the temperature of the high-temperature air flowing into the hot side of the primary heat exchanger 2. The first flow regulating valve 15 is used to control the heat sink.

[0045] The positive displacement compressor 4 has its inlet connected to the hot side outlet of the primary heat exchanger 2 via a pipeline. A first temperature sensor 5 is installed on this pipeline. The temperature of the airflow flowing out of the hot side outlet of the primary heat exchanger 2 is reduced, which can protect the positive displacement compressor 4. The positive displacement compressor 4 pressurizes the airflow so that the pressure of the airflow is consistent with the pressure of the oxygen source bleed air on the aircraft. The first temperature sensor 5 is used for heat exchange monitoring and feedback control.

[0046] The secondary radiator 6 has its hot-side inlet connected to the outlet of the positive displacement compressor 4 via a pipeline. A temperature and pressure composite sensor 7 is installed on this pipeline to monitor the temperature and pressure of the airflow at the outlet of the positive displacement compressor 4, and feedback control can be designed. The cold-side inlet of the secondary radiator 6 is connected to the air supply outlet of the loop-controlled cooling component 1 via a pipeline. A second flow control valve 8 is installed on this pipeline. The airflow from the air supply outlet of the loop-controlled cooling component 1 is used to cool the airflow entering the hot side of the secondary radiator 6. The second flow control valve 8 is used to control the heat sink.

[0047] The airborne condensation and dehydration device 9 has its cold-side inlet connected to the hot-side outlet of the secondary radiator 6 via a pipeline. A second temperature sensor 10 and a first humidity sensor 11 are installed on this pipeline. The hot-side inlet of the airborne condensation and dehydration device 9 is connected to the air supply outlet of the loop control cooling component 1 via a pipeline. The airflow from the air supply outlet of the loop control cooling component 1 is used to dehydrate the airflow from the hot-side outlet of the secondary radiator 6, so as to restore the humidity of the oxygen source priming air. The second temperature sensor 10 is located after the junction of the hot-side pipeline and the parallel branch of the secondary radiator 6, and is used for heat exchange monitoring and feedback control. The first humidity sensor 11 is used to monitor humidity. A branch is connected in parallel on the hot-side pipeline of the secondary radiator 6. A temperature regulating valve 12 is installed on this branch. The airflow from the branch is at a higher temperature and will mix with the airflow from the hot-side outlet of the secondary radiator 6. The ratio of the two airflows can be controlled by the temperature regulating valve 12, so as to restore the temperature of the oxygen source priming air.

[0048] The airborne oxygen generation system 13 has its inlet connected to the outlet of the airborne condensate removal device 9 via a pipeline. A second humidity sensor 14 is installed on the pipeline to monitor the humidity of the airflow.

[0049] The loop-controlled cooling component actuator 16 is connected to the loop-controlled cooling component 1 and is used to control the working mode and output parameters of the loop-controlled cooling component 1.

[0050] The gas source simulation control center 17 is connected to the flow regulating valve 3, the first flow regulating valve 15, the second flow control valve 8, the temperature regulating valve 12, and the positive displacement compressor 4. It can control the opening degree of the flow regulating valve 3, the first flow regulating valve 15, the second flow control valve 8, and the temperature regulating valve 12, as well as control the working mode of the positive displacement compressor 4. It can be combined with relevant temperature, pressure, and flow monitoring to build feedback regulation.

[0051] For the bleed air simulation test bench for the aircraft airborne oxygen generation system disclosed in the above embodiments, those skilled in the art will understand that it is equipped with a loop-controlled refrigeration component 1, a primary heat exchanger 2, a volumetric compressor 4, a secondary radiator 6, an airborne condensate removal device 9, a loop-controlled refrigeration component exciter 16, and an air source simulation control center 17, along with corresponding pipelines, valves, and sensors. It utilizes a single high-temperature air source and a low-temperature air source to generate oxygen-generating bleed air with the required flow rate, pressure, temperature, and humidity in an economical, efficient, and convenient manner, and supplies it to the airborne oxygen generation system 13. In this way, the bleed air pressure point and its related bleed air parameter range can be accurately determined experimentally at the initial design stage of the airborne oxygen generation system 13.

[0052] In some optional embodiments, in the above-described aircraft airborne oxygen generation system bleed air simulation test bench, the airborne oxygen generation system 13 includes:

[0053] The oxygen concentration unit 18 has its inlet connected to the outlet of the airborne condensate removal device 9 via a pipeline;

[0054] The oxygen concentrator actuator 19 is connected to the oxygen concentrator assembly 18 to control the oxygen production status of the oxygen concentrator assembly 18 and to monitor and record the pressure and concentration of the produced oxygen.

[0055] The breathing simulation device 20 has its inlet connected to the outlet of the oxygen concentration component 18 via a pipeline, and its outlet is vented through a pipeline.

[0056] In some optional embodiments, the above-mentioned aircraft airborne oxygen generation system bleed air simulation test bench includes a breathing simulation device 20 with a mechanical lung and a corresponding flow regulating valve for flow control, simulating the oxygen usage of personnel on board the aircraft.

[0057] In some optional embodiments, the above-described aircraft airborne oxygen generation system bleed air simulation test bench further includes:

[0058] The integrated data acquisition system 21 connects various pressure, temperature, flow, and humidity measuring points to collect, record, and display relevant data on pressure, temperature, flow, and humidity.

[0059] In some optional embodiments, the above-described aircraft airborne oxygen generation system bleed air simulation test bench further includes:

[0060] The dual-channel air supply system has an inlet connected to a compressed air source via a pipeline, and an outlet divided into a hot-side outlet and a cold-side outlet. The hot-side outlet provides high-temperature air to the hot-side inlet of the cold component 1 and the primary heat exchanger 2 through a pipeline connection loop, and the cold-side outlet provides low-temperature air to the cold-side inlet of the cold component 1 through a pipeline connection loop.

[0061] The dual-channel controller connects to the monitoring devices of the dual-channel gas supply system and controls the pressure, temperature, and flow parameters output by the dual-channel gas supply system.

[0062] In some optional embodiments, the dual-path air supply system in the above-described aircraft airborne oxygen generation system bleed air simulation test bench includes:

[0063] The filter has three outlets: an instrument path, a hot path, and a cold path. The hot path outlet is its hot-side outlet, and the cold path outlet is its cold-side outlet.

[0064] After the filter, the instrument circuit is equipped with a manual gate valve and a pressure reducing valve in sequence.

[0065] The following components are arranged sequentially on the hot path after the filter: a hot path manual gate valve, a hot path primary pressure regulating valve, a hot path flow meter, a hot path flow regulating valve, a hot path electric heating unit group, a hot path pressurized jet type humidity control device, and a hot path high-precision dynamic pressure regulating valve. The hot path electric heating unit group is connected to a hot path power regulator.

[0066] The cold circuit following the filter is sequentially equipped with a cold circuit manual gate valve, a cold circuit primary pressure regulating valve, a cold circuit flow meter, a cold circuit primary flow regulating valve, a cold circuit turbine, and a cold circuit high-precision dynamic pressure regulating valve. The cold circuit turbine is connected in parallel with a cold circuit secondary flow regulating valve. The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably.

[0067] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A test bench for bleed air simulation of an aircraft airborne oxygen generation system, characterized in that, include: The ring-controlled cooling component (1) has its hot-side inlet connected to a high-temperature air source via a pipeline, and its cold-side inlet connected to a low-temperature air source via a pipeline; The primary heat exchanger (2) has its hot side inlet connected to a high-temperature air source via a pipeline, and a flow regulating valve (3) is installed on the pipeline; the cold side inlet of the primary heat exchanger (2) is connected to the air outlet of the cold component (1) via a pipeline, and a first flow regulating valve (15) is installed on the pipeline. The inlet of the positive displacement compressor (4) is connected to the hot side outlet of the primary heat exchanger (2) through a pipeline, and a first temperature sensor (5) is installed on the pipeline. The secondary radiator (6) has its hot side inlet connected to the outlet of the volumetric compressor (4) via a pipeline, and a temperature and pressure composite sensor (7) is installed on the pipeline; the cold side inlet of the secondary radiator (6) is connected to the air supply outlet of the cooling component (1) via a pipeline, and a second flow control valve (8) is installed on the pipeline. The airborne condensate removal device (9) has its cold side inlet connected to the hot side outlet of the secondary radiator (6) via a pipeline. A second temperature sensor (10) and a first humidity sensor (11) are installed on the pipeline. The hot side inlet of the airborne condensate removal device (9) is connected to the air supply outlet of the cold component (1) via a pipeline loop. A branch is connected in parallel on the hot side pipeline of the secondary radiator (6), and a temperature regulating valve (12) is installed on the branch. The airborne oxygen generation system (13) has its inlet connected to the outlet of the airborne condensate removal device (9) via a pipeline, and a second humidity sensor (14) is installed on the pipeline. A ring-controlled cooling component actuator (16) is connected to the ring-controlled cooling component (1) and is used to control the working mode and output parameters of the ring-controlled cooling component (1). The gas source simulation control center (17) is connected to the flow regulating valve (3), the first flow regulating valve (15), the second flow control valve (8), the temperature control valve (12), and the positive displacement compressor (4) so ​​as to control the opening degree of the flow regulating valve (3), the first flow regulating valve (15), the second flow control valve (8), the temperature control valve (12), and the working mode of the positive displacement compressor (4).

2. The bleed air simulation test bench for an aircraft airborne oxygen generation system according to claim 1, characterized in that, The airborne oxygen generation system (13) includes: The oxygen concentration unit (18) has its inlet connected to the outlet of the airborne condensate removal device (9) via a pipeline; An oxygen concentrator actuator (19) is connected to an oxygen concentrator assembly (18) to control the oxygen production status of the oxygen concentrator assembly (18) and to monitor and record the pressure and concentration of the produced oxygen. The breathing simulation device (20) has its inlet connected to the outlet of the oxygen concentration component (18) via a pipeline, and its outlet is vented via a pipeline.

3. The bleed air simulation test bench for an aircraft airborne oxygen generation system according to claim 2, characterized in that, The breathing simulation device (20) includes a mechanical lung and is equipped with a corresponding flow regulating valve for flow control.

4. The bleed air simulation test bench for an aircraft airborne oxygen generation system according to claim 1, characterized in that, Also includes: The integrated data acquisition system (21) connects various pressure, temperature, flow and humidity measurement points to collect, record and display relevant data on pressure, temperature, flow and humidity.

5. The test bench for designing an airborne oxygen generation system for aircraft according to claim 1, characterized in that, Also includes: The dual-path air source system has an inlet connected to a compressed air source via a pipeline, and an outlet divided into a hot-side outlet and a cold-side outlet. The hot-side outlet provides high-temperature air to the hot-side inlet of the cold component (1) and the primary heat exchanger (2) through a pipeline connection loop, and the cold-side outlet provides low-temperature air to the cold-side inlet of the cold component (1) through a pipeline connection loop. The dual-channel controller connects to the monitoring devices of the dual-channel gas supply system and controls the pressure, temperature, and flow parameters output by the dual-channel gas supply system.

6. The test bench for designing an airborne oxygen generation system for aircraft according to claim 5, characterized in that, The dual-channel gas supply system includes: The filter has three outlets: an instrument path, a hot path, and a cold path. The hot path outlet is its hot-side outlet, and the cold path outlet is its cold-side outlet. After the filter, the instrument circuit is equipped with a manual gate valve and a pressure reducing valve in sequence. The following components are arranged sequentially on the hot path after the filter: a hot path manual gate valve, a hot path primary pressure regulating valve, a hot path flow meter, a hot path flow regulating valve, a hot path electric heating unit group, a hot path pressurized jet type humidity control device, and a hot path high-precision dynamic pressure regulating valve. The hot path electric heating unit group is connected to a hot path power regulator. The cold circuit after the filter is sequentially equipped with a cold circuit manual gate valve, a cold circuit primary pressure regulating valve, a cold circuit flow meter, a cold circuit primary flow regulating valve, a cold circuit turbine, and a cold circuit high-precision dynamic pressure regulating valve. The cold circuit turbine is connected in parallel with a cold circuit secondary flow regulating valve.

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