Dual-path injection helicopter cabin heating system and control method

Abstract

The application provides a dual-path injection helicopter cabin heating system and a control method. The helicopter cabin heating system comprises a high-temperature ejector, a low-temperature ejector, two electric valves, a hot air pipeline, a mixing chamber, an air switching valve, three temperature sensors, an air distribution pipeline and a control system. By adjusting the air flow and the proportion of the two ejectors, the air flow and the temperature entering the cabin can be controlled, the environmental temperature of the cabin is adjusted, and the application has the advantages of high reliability, accurate temperature control and large temperature adjustment range.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of design of helicopter environmental control system, and relates to a double-path induction helicopter cabin heating system and a control method. BACKGROUND

[0002] The helicopter cabin heating system is used for heating the helicopter cabin, and high-temperature and high-pressure air is introduced into a mixing chamber from a compression section of an engine, cold air outside is introduced into the mixing chamber through the induction of a fan or hot edge air, and the cold and hot air is mixed in the mixing chamber at a certain ratio to a suitable temperature and then enters the cabin. This heating mode has the problems of small temperature regulation range and large influence of ambient temperature change on cabin air temperature. SUMMARY

[0003] The application aims to:

[0004] The application provides a double-path induction heating system, which comprises two inducers with different induction ratios. By adjusting the air flow and ratio of the two inducers, the air flow and temperature entering the cabin can be controlled, and the ambient temperature of the cabin can be adjusted. The system has the advantages of high reliability, accurate temperature control and large temperature regulation range.

[0005] TECHNICAL SCHEME

[0006] The application provides a double-path induction helicopter cabin heating system, which comprises a hot air pipeline 2, an electric valve 1, an electric valve 2, a high-temperature inducer 5, a low-temperature inducer 6, a high-temperature temperature sensor 7, a low-temperature temperature sensor 8, a mixing chamber 9, a mixing chamber temperature sensor 10 and a control device 11. The hot air pipeline 2 has two paths and is connected with the high-temperature inducer 5 and the low-temperature inducer 6. The electric valve 1 and the electric valve 2 are arranged on the pipelines connected with the high-temperature inducer 5 and the low-temperature inducer 6, respectively. The outlets of the high-temperature inducer 5 and the low-temperature inducer 6 are communicated with the mixing chamber 9. The high-temperature temperature sensor 7 is arranged at the outlet position of the high-temperature inducer 5 and is used for measuring the temperature of high-temperature air entering the mixing chamber. The low-temperature temperature sensor 8 is arranged at the outlet position of the low-temperature inducer 6 and is used for measuring the temperature of low-temperature air entering the mixing chamber. The mixing chamber temperature sensor 10 is used for measuring the temperature of air entering the cabin. The electric valve 1, the electric valve 2, the high-temperature temperature sensor 7, the low-temperature temperature sensor 8 and the mixing chamber temperature sensor 10 are connected with the control device 11.

[0007] Preferably, the high-temperature inducer 5 and the low-temperature inducer 6 have different induction ratios. By controlling the flow and ratio of the high-temperature inducer 5 and the low-temperature inducer 6, the flow and temperature of air entering the cabin can be controlled.

[0008] Preferably, the front end of the hot air pipeline 2 is connected with an air inlet of the compression section of the engine.

[0009] Preferably, the high-temperature ejector 5 has a small entrainment ratio, a high hot air ratio, and a high mixed air temperature, and the low-temperature ejector 6 has a large entrainment ratio, a low hot air ratio, and a low mixed air temperature.

[0010] Preferably, one-way valves are installed at the cold air inlets of the high-temperature ejector 5 and the low-temperature ejector 6 to prevent air in the mixing chamber from flowing out through the cold air inlets.

[0011] Preferably, when the flow rate is constant, the opening of the high-temperature electric valve 3 is reduced by the control device 11 to reduce the air flow rate in the high-temperature ejector 5, and the opening of the low-temperature electric valve 4 is increased by the control device 11 to increase the air flow rate in the low-temperature ejector 6, thereby reducing the air temperature entering the cabin.

[0012] Conversely, the opening of the high-temperature electric valve 3 is increased by the control device 11 to increase the air flow rate in the high-temperature ejector 5, and the opening of the low-temperature electric valve 4 is reduced by the control device 11 to reduce the air flow rate in the low-temperature ejector 6, thereby increasing the air temperature entering the cabin.

[0013] Preferably, when the temperature is constant, the openings of the high-temperature electric valve 3 and the low-temperature electric valve 4 are increased by the control device 11 in the same proportion, thereby increasing the air flow rates in the high-temperature ejector 5 and the low-temperature ejector 6 in the same proportion, and increasing the air flow rate entering the cabin.

[0014] Conversely, the openings of the high-temperature electric valve 3 and the low-temperature electric valve 4 are reduced by the control device 11 in the same proportion, thereby reducing the air flow rates in the high-temperature ejector 5 and the low-temperature ejector 6 in the same proportion, and reducing the air flow rate entering the cabin.

[0015] Advantages:

[0016] The present application provides a dual-path ejecting cabin heating system, which includes two ejectors with different entrainment ratios. By adjusting the air flow rates and proportions of the two ejectors, the air flow rate and temperature entering the cabin can be controlled, and the environmental temperature of the cabin can be adjusted. The system has the advantages of high reliability, accurate temperature control, and a large temperature adjustment range. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 The present application is a main component of a dual-path ejecting helicopter cabin heating system.

[0018] BRIEF DESCRIPTION OF THE DRAWINGS

[0019] 1 - engine compression section bleed air port; 2 - hot air pipeline; 3 - high-temperature electric valve;

[0020] 4 - low-temperature electric valve; 5 - high-temperature ejector; 6 - low-temperature ejector;

[0021] 7—High-temperature temperature sensor; 8—Low-temperature temperature sensor; 9—Mixing chamber;

[0022] 10—Mixing chamber temperature sensor; 11—Control device. Detailed Implementation

[0023] The present invention provides a dual-path ejector helicopter cabin heating system in detail below with reference to the accompanying drawings.

[0024] like Figure 1 As shown, the dual-ejector helicopter cabin heating system includes a hot air duct 2, a high-temperature electric valve 3, a low-temperature electric valve 4, a high-temperature ejector 5, a low-temperature ejector 6, a high-temperature temperature sensor 7, a low-temperature temperature sensor 8, a mixing chamber 9, a mixing chamber temperature sensor 10, and a control device 11. The high-temperature temperature sensor 7 is located at the outlet of the high-temperature ejector 5 and measures the temperature of the high-temperature air entering the mixing chamber. The low-temperature temperature sensor 8 is located at the outlet of the low-temperature ejector 6 and measures the temperature of the low-temperature air entering the mixing chamber. The mixing chamber temperature sensor 10 measures the temperature of the air entering the cabin.

[0025] Assuming the ambient temperature is 0℃, the cabin air temperature is set to 60℃, the hot air temperature from engine compression section bleed port 1 is 200℃, and the pressure is 500KPa, under this pressure, the ejection ratio of the high-temperature ejector is 1, and the ejection ratio of the low-temperature ejector is 4.

[0026] Hot air enters the high-temperature ejector 5 after passing through the high-temperature electric valve 3, and mixes with the ejected cold air from the outside. The ratio of hot to cold air is 1:1, and the temperature of the mixed air is 100°C. The temperature value is transmitted to the control device 11 by the high-temperature temperature sensor 7.

[0027] Hot air enters the cryogenic ejector 6 after passing through the cryogenic electric valve 4, and mixes with the ejected cold air from the outside. The ratio of hot to cold air is 1:4, and the temperature of the mixed air is 40°C. The temperature value is transmitted to the control device 11 by the cryogenic temperature sensor (8).

[0028] The set temperature is 60℃. At this time, the ratio of the outlet air of the high temperature ejector 5 and the low temperature ejector 6 should be 1:2. The proportion of hot air in the high temperature ejector is 50% and the proportion of hot air in the low temperature ejector is 20%. Therefore, the control device 11 controls the proportion of hot air entering the high temperature ejector 5 and the low temperature ejector 6 according to a ratio of 5:4.

[0029] When the ambient temperature or the set temperature changes, the opening degree of the high-temperature electric valve 3 and the low-temperature electric valve 4 can be adjusted by the control device 11 to control the ratio of the air outlets of the high-temperature ejector 5 and the low-temperature ejector 6, thereby adjusting the temperature and flow rate of the air entering the cabin.

[0030] In extreme cases, only one ejector can be used, and a one-way valve is installed on each ejector, and the overall ejector ratio of the system can be adjusted between 1 and 4 in an environment where hot air is not allowed to leak.

[0031] The above is only a specific embodiment of the present application, which is described in detail, and the part not described in detail is the conventional technology. However, the protection scope of the present application is not limited to this, and any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the present application. The protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A control method of a two-pass induction type helicopter cabin heating system for controlling the two-pass induction type helicopter cabin heating system, characterized by, The double-path ejector helicopter cabin heating system comprises a hot air pipeline (2), a high-temperature electric valve (3), a low-temperature electric valve (4), a high-temperature ejector (5), a low-temperature ejector (6), a high-temperature temperature sensor (7), a low-temperature temperature sensor (8), a mixing chamber (9), a mixing chamber temperature sensor (10) and a control device (11), the hot air pipeline (2) has two paths and is connected with the high-temperature ejector (5) and the low-temperature ejector (6) respectively, the high-temperature electric valve (3) and the low-temperature electric valve (4) are arranged on the pipelines connected with the high-temperature ejector (5) and the low-temperature ejector (6) respectively, the outlets of the high-temperature ejector (5) and the low-temperature ejector (6) are communicated with the mixing chamber (9), the high-temperature temperature sensor (7) is located at the outlet position of the high-temperature ejector (5) and is used for measuring the temperature of high-temperature air entering the mixing chamber, the low-temperature temperature sensor (8) is located at the outlet position of the low-temperature ejector (6) and is used for measuring the temperature of low-temperature air entering the mixing chamber, the mixing chamber temperature sensor (10) is used for measuring the temperature of air entering the cabin, and the high-temperature electric valve (3), the low-temperature electric valve (4), the high-temperature temperature sensor (7), the low-temperature temperature sensor (8) and the mixing chamber temperature sensor (10) are connected with the control device (11). The control method comprises a temperature control method and a flow control method. The temperature control method is as follows: Under the condition that the flow is unchanged, the opening of the high-temperature electric valve (3) is reduced by the control device (11), the air flow in the high-temperature ejector (5) is reduced, the opening of the low-temperature electric valve (4) is increased by the control device (11), the air flow in the low-temperature ejector (6) is increased, and the temperature of air entering the cabin is reduced. Conversely, the opening of the high-temperature electric valve (3) is increased by the control device (11), the air flow in the high-temperature ejector (5) is increased, the opening of the low-temperature electric valve (4) is reduced by the control device (11), the air flow in the low-temperature ejector (6) is reduced, and the temperature of air entering the cabin is increased. The flow control method is as follows: Under the condition that the temperature is unchanged, the openings of the high-temperature electric valve (3) and the low-temperature electric valve (4) are increased in equal proportion by the control device (11), the air flows in the high-temperature ejector (5) and the low-temperature ejector (6) are increased in equal proportion, and the air flow into the cabin is increased. Conversely, the openings of the high-temperature electric valve (3) and the low-temperature electric valve (4) are reduced in equal proportion by the control device (11), the air flows in the high-temperature ejector (5) and the low-temperature ejector (6) are reduced in equal proportion, and the air flow into the cabin is reduced.

2. The control method according to claim 1, characterized by, The air flow and temperature entering the cabin are controlled by the flow and proportion of the high-temperature ejector (5) and the low-temperature ejector (6) with different ejector ratios.

3. The control method according to claim 1, characterized by, The front end of the hot air pipeline (2) is connected with an engine compression section bleed air port.

4. The control method according to claim 2, characterized by, The ejector ratio of the high-temperature ejector (5) is small, the hot air proportion is high, the mixed air temperature is high, the ejector ratio of the low-temperature ejector (6) is large, the hot air proportion is low, and the mixed air temperature is low.

5. The control method according to claim 1, characterized by, One-way valves are installed at the cold air inlets of the high temperature ejector (5) and the low temperature ejector (6) to prevent the air in the mixing chamber from flowing out through the cold air inlets.

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