CN116006313A - Intermediate cooling system and method for aviation piston engine and aviation engine - Google Patents
Intermediate cooling system and method for aviation piston engine and aviation engine Download PDFInfo
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- CN116006313A CN116006313A CN202211694716.7A CN202211694716A CN116006313A CN 116006313 A CN116006313 A CN 116006313A CN 202211694716 A CN202211694716 A CN 202211694716A CN 116006313 A CN116006313 A CN 116006313A
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- intercooler
- piston engine
- control valve
- bypass control
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
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Abstract
The invention discloses an intermediate cooling system and a cooling method of an aviation piston engine and the aviation engine, and relates to the technical field of aviation equipment cooling, comprising the following steps: an intercooling front air inlet pipeline; the first cooling structure comprises a bypass control valve and a first intercooler, and the bypass control valve is connected with one end of an intercooling front air inlet pipeline; the second cooling structure comprises a three-way valve, a second intercooler and a third intercooler, and an inlet and two outlets of the three-way valve are respectively connected with one end of the air inlet pipeline before intercooling, the second intercooler and the third intercooler; the first cooling structure and the second cooling structure are arranged in parallel; the intercooling post-air inlet pipeline is used for connecting the aviation piston engine with the first cooling structure and the second cooling structure; a control unit for controlling the bypass control valve according to the operation state of the aviation piston engine; the intermediate cooling system has the advantages of small internal resistance, high safety margin, adjustability and adaptability to complex working conditions.
Description
Technical Field
The invention belongs to the technical field of aviation equipment cooling, and particularly relates to an aviation piston engine intermediate cooling system, an aviation piston engine intermediate cooling method and an aviation engine.
Background
The prior aviation piston engine intermediate cooling system commonly used in China mainly has the following problems:
when the traditional intercooling mode is applied to a high-supercharging large-displacement aviation piston engine, the internal resistance and the size are overlarge, the traditional intercooling mode does not have an adjusting function, and the temperature easily exceeds a safety boundary after intercooling under the high-altitude or high-power and low-power states of the engine;
when the parallel intercooling system is applied to a high-supercharging large-displacement aviation piston engine, the internal resistance of the system is reduced, but the parallel intercooling system also does not have an adjustable function, and is not applicable to complex working conditions such as high altitude, thin air, large engine power change amplitude and the like.
The two ways of intercooling channels are only one or two, the safety margin is low, if a single way is damaged, the intercooling function is lost, and the engine or the aircraft is damaged seriously.
Disclosure of Invention
The invention aims at overcoming the defects of the prior art and provides an intermediate cooling system and a cooling method of an aviation piston engine and the aviation engine.
In order to achieve the above object, the present invention provides an aircraft piston engine intermediate cooling system comprising:
an intercooling front air inlet pipeline;
the first cooling structure comprises a bypass control valve and a first intercooler, and the bypass control valve is connected with one end of the intercooling front air inlet pipeline;
the second cooling structure comprises a three-way valve, a second intercooler and a third intercooler, and an inlet and two outlets of the three-way valve are respectively connected with one end of the intercooling front air inlet pipeline, the second intercooler and the third intercooler;
the first cooling structure and the second cooling structure are arranged in parallel;
the intercooling post-air inlet pipeline is used for connecting the aviation piston engine with the first cooling structure and the second cooling structure;
and the control unit is used for controlling the bypass control valve according to the running state of the aviation piston engine.
Optionally, the first intercooler is a fan-cooled intercooler, and the first intercooler is connected with the pre-intercooler air inlet pipeline through the bypass control valve.
Optionally, the cold side of the first intercooler is connected to a cooling fan.
Optionally, the second intercooler is a fan-cooled intercooler, and the third intercooler is an air duct-cooled intercooler.
Optionally, the cold sides of the second intercooler and the third intercooler are connected to an air intake duct of an aircraft.
Optionally, the other end of the intercooling front air inlet pipeline is used for being connected with a supercharger.
Optionally, a sensor is arranged on the aviation piston engine, and the sensor comprises an altitude test module, an ambient temperature test module and an air density calculation module.
The invention also provides an intermediate cooling method of the aviation piston engine, which comprises the following steps of:
according to the power state of the aviation piston engine, the opening degree of the bypass control valve is adjusted;
and adjusting the opening degree of the bypass control valve according to the operation state of the second intercooler and/or the third intercooler.
The invention also provides an aeroengine, which comprises the aeropiston engine intermediate cooling system.
The invention provides an intermediate cooling system and a cooling method of an aero-piston engine and the aero-piston engine, and has the beneficial effects that: the intermediate cooling system can control the opening degree of the bypass control valve according to the working power of the aviation piston engine, so that the supercharged gas in the air inlet pipeline before intercooling is divided into multiple paths of air passing through the intercooler, the internal resistance of the cooling system is effectively reduced, the load of the supercharger is reduced, and the mechanical efficiency is improved.
Additional features and advantages of the invention will be set forth in the detailed description which follows.
Drawings
The foregoing and other objects, features and advantages of the invention will be apparent from the following more particular descriptions of exemplary embodiments of the invention as illustrated in the accompanying drawings wherein like reference numbers generally represent like parts throughout the exemplary embodiments of the invention.
Fig. 1 shows a schematic structural view of an aircraft piston engine intercooler system according to an embodiment of the invention.
Reference numerals illustrate:
1. an intercooling front air inlet pipeline; 2. a bypass control valve; 3. a first intercooler; 4. a three-way valve; 5. a second intercooler; 6. a third intercooler; 7. an intercooling post-air inlet pipeline; 8. and (5) starting the aviation piston.
Detailed Description
Preferred embodiments of the present invention will be described in more detail below. While the preferred embodiments of the present invention are described below, it should be understood that the present invention may be embodied in various forms and should not be 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.
The invention provides an intermediate cooling system of an aviation piston engine, which comprises the following components:
an intercooling front air inlet pipeline;
the first cooling structure comprises a bypass control valve and a first intercooler, and the bypass control valve is connected with one end of an intercooling front air inlet pipeline;
the second cooling structure comprises a three-way valve, a second intercooler and a third intercooler, and an inlet and two outlets of the three-way valve are respectively connected with one end of the air inlet pipeline before intercooling, the second intercooler and the third intercooler;
the first cooling structure and the second cooling structure are arranged in parallel;
the intercooling post-air inlet pipeline is used for connecting the aviation piston engine with the first cooling structure and the second cooling structure;
and the control unit is used for controlling the bypass control valve according to the running state of the aviation piston engine.
Specifically, the cooling system is provided with three intercoolers, so that a plurality of bypasses are formed, the safety redundancy of the system is increased, when one of the bypasses fails, other bypasses work normally, the middle and low power operation of the engine can be maintained, the aviation piston engine can operate normally, and the aviation safety of the aircraft is ensured; the bypass control valve is arranged in the cooling system, so that the cooling system can adapt to complex working conditions such as high altitude, thin air, large engine power change amplitude and the like, and when the aviation piston engine is in a low-power state, the bypass control valve can be closed, and the energy consumption is saved.
In one embodiment, the inner wall of the pipeline is smooth, and the intercooling post-air inlet pipeline, the intercooling forward air inlet pipeline and the three-way valve connector can be connected by a high Wen Fangsong clamp.
Optionally, the first intercooler is a fan-cooled intercooler, and the first intercooler is connected with the intercooling front air inlet pipeline through a bypass control valve.
Optionally, the cold side of the first intercooler is connected to a cooling fan.
Specifically, an air pipe branch is connected to the air inlet pipe before intercooling, and the air pipe branch is sequentially provided with a bypass control valve and a first intercooler, and the control unit controls the opening angle and the opening and closing state of the bypass control valve, so that the cooling system can adapt to complex working conditions; the cold side incoming flow of the first intercooler is ensured by an inter-cooling fan, and part of electric energy needs to be consumed.
Optionally, the second intercooler is a fan-cooled intercooler, and the third intercooler is an air duct-cooled intercooler.
Optionally, the cold sides of the second and third intercoolers are connected to an air intake duct of the aircraft.
Specifically, the air inlet pipeline before intercooling is also connected with another air pipe branch, and the air pipe branch is connected with the second intercooler and the third intercooler through a three-way valve, so that the internal resistance of the cooling system is reduced, and when the aviation piston engine is in a low-power state, the supercharged air can only pass through the second intercooler and the third intercooler; the cold sides of the second intercooler and the third intercooler are guaranteed to flow against an air inlet channel of the aircraft, and the two intercoolers are always in a working state.
Optionally, the other end of the charge air charge conduit is adapted to be connected to a supercharger.
Optionally, a sensor is arranged on the aviation piston engine, and the sensor comprises an altitude test module, an ambient temperature test module and an air density calculation module.
Specifically, the opening of the bypass control valve is continuously adjusted along with the change of the power of the engine and the change of the altitude, the ambient temperature and the air density of the outside so as to adapt to the complex operation conditions of the engine and the aircraft.
Optionally, the first intercooler, the second intercooler and the third intercooler are compatible with the structural dimensions of the aviation piston engine.
Specifically, the cooling system can adjust the size, the structure and the arrangement mode of each intercooler according to different aircrafts and engine arrangement spaces, and has universal applicability.
The invention also provides an intermediate cooling method of the aviation piston engine, which comprises the following steps of:
according to the power state of the aviation piston engine, the opening degree of the bypass control valve is adjusted;
and adjusting the opening degree of the bypass control valve according to the operation state of the second intercooler and/or the third intercooler.
Specifically, the opening degree of the bypass control valve is regulated according to the running power of the engine, so that the flowing gas in the three intercoolers is changed, the overall internal resistance of the system is reduced, and the system has higher safety margin; when one of the intercoolers fails, the bypass control valve can be opened to enable a part of gas to pass through the first intercooler, so that the engine can at least maintain medium-low power operation, and the flying safety of the aircraft is ensured.
The invention also provides an aeroengine, which comprises the aeropiston engine intermediate cooling system.
Examples
As shown in fig. 1, the present invention provides an aircraft piston engine intercooler system comprising:
an intercooling front air inlet pipeline 1;
the first cooling structure comprises a bypass control valve 2 and a first intercooler 3, and the bypass control valve 2 is connected with one end of the intercooler air inlet pipeline 1;
the second cooling structure comprises a three-way valve 4, a second intercooler 5 and a third intercooler 6, and an inlet and two outlets of the three-way valve 4 are respectively connected with one end of the intercooling front air inlet pipeline 1, the second intercooler 5 and the third intercooler 6;
the first cooling structure and the second cooling structure are arranged in parallel;
the intercooling post-air inlet pipeline 7 is used for connecting the aviation piston engine 8 with the first cooling structure and the second cooling structure;
the control unit controls the bypass control valve 2 in dependence on the operating state of the aviation piston engine 8.
In the present embodiment, the first intercooler 3 is a fan-cooled intercooler, and the first intercooler 3 is connected to the intercooler intake pipe 1 through the bypass control valve 2.
In the present embodiment, the cold side of the first intercooler 3 is connected to a cooling fan.
In the present embodiment, the second intercooler 5 is a fan-cooled intercooler, and the third intercooler 6 is an air duct-cooled intercooler.
In the present embodiment, the cold sides of the second and third charge air coolers 5, 6 are connected with the inlet duct of the aircraft.
In the present embodiment, the other end of the charge air line before charge air conditioning 1 is used for connection with a supercharger.
In the present embodiment, the aviation piston engine 8 is provided with sensors, which include an altitude test module, an ambient temperature test module, and an air density calculation module.
In the present embodiment, the first intercooler 3, the second intercooler 5 and the third intercooler 6 are matched in size to the aviation piston engine 8.
The invention also provides an intermediate cooling method of the aviation piston engine, which comprises the following steps of:
adjusting the opening degree of the bypass control valve 2 according to the power state of the aviation piston engine 8;
the opening degree of the bypass control valve 2 is adjusted according to the operating state of the second intercooler 5 and/or the third intercooler 6.
The invention also provides an aeroengine, which comprises the aeropiston engine intermediate cooling system.
In summary, the cooling system pressurizes the exhaust gas discharged by the aviation piston engine 8 through the supercharger, and then discharges the exhaust gas into the first cooling structure and the second cooling structure, the control unit controls the opening of the bypass control valve 2 through the power of the aviation piston engine 8, so as to determine whether the supercharged air passes through the first intercooler 3, divide the high-pressure gas into two paths or three paths to pass through the intercooler, and effectively reduce the internal resistance of the system; and the opening degree of the bypass control valve 2 is adjusted to be different, so that the cooling system can adapt to different engine operation conditions.
The foregoing description of embodiments of the invention has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the various embodiments described.
Claims (9)
1. An aircraft piston engine intercooler system, comprising:
an intercooling front air inlet pipeline;
the first cooling structure comprises a bypass control valve and a first intercooler, and the bypass control valve is connected with one end of the intercooling front air inlet pipeline;
the second cooling structure comprises a three-way valve, a second intercooler and a third intercooler, and an inlet and two outlets of the three-way valve are respectively connected with one end of the intercooling front air inlet pipeline, the second intercooler and the third intercooler;
the first cooling structure and the second cooling structure are arranged in parallel;
the intercooling post-air inlet pipeline is used for connecting the aviation piston engine with the first cooling structure and the second cooling structure;
and the control unit is used for controlling the bypass control valve according to the running state of the aviation piston engine.
2. The aircraft piston engine intercooler system of claim 1, wherein the first intercooler is a fan-cooled intercooler, the first intercooler being connected to the pre-charge air intake conduit via the bypass control valve.
3. The aircraft piston engine intercooler system of claim 2, wherein the cold side of the first intercooler is connected to a cooling fan.
4. The aircraft piston engine intercooler system of claim 1, wherein the second intercooler is a fan-cooled intercooler and the third intercooler is a duct-cooled intercooler.
5. The aircraft piston engine intercooler system of claim 4, wherein the cold side of the second intercooler and the third intercooler are connected to an air intake duct of an aircraft.
6. The aircraft piston engine intercooler system of claim 1, wherein the other end of the pre-charge air conduit is adapted to be connected to a supercharger.
7. The aircraft piston engine intercooler system of claim 1, wherein a sensor is provided on the aircraft piston engine, the sensor comprising an altitude test module, an ambient temperature test module, and an air density calculation module.
8. An aircraft piston engine intermediate cooling method, with an aircraft piston engine intermediate cooling system according to any one of claims 1-7, characterized in that the cooling method comprises:
according to the power state of the aviation piston engine, the opening degree of the bypass control valve is adjusted;
and adjusting the opening degree of the bypass control valve according to the operation state of the second intercooler and/or the third intercooler.
9. An aircraft engine, characterized by comprising an aircraft piston engine intermediate cooling system according to any one of claims 1-7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211694716.7A CN116006313A (en) | 2022-12-28 | 2022-12-28 | Intermediate cooling system and method for aviation piston engine and aviation engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211694716.7A CN116006313A (en) | 2022-12-28 | 2022-12-28 | Intermediate cooling system and method for aviation piston engine and aviation engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116006313A true CN116006313A (en) | 2023-04-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211694716.7A Pending CN116006313A (en) | 2022-12-28 | 2022-12-28 | Intermediate cooling system and method for aviation piston engine and aviation engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116006313A (en) |
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2022
- 2022-12-28 CN CN202211694716.7A patent/CN116006313A/en active Pending
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