Air cooling system for aircraft engine

Abstract

The present application discloses an air cooling system for an aircraft engine, which is used to implement forced heat dissipation on the cylinder of the aircraft engine, and includes a temperature detection module, a forced air cooling module and a main control module. The temperature detection module is used to detect the cylinder temperature of the aircraft engine and output the cylinder temperature to the main control module; the main control module is connected to the temperature detection module and the forced air cooling module respectively, and is used to receive the cylinder temperature, and obtain the air cooling control instruction according to the relationship between the cylinder temperature and the preset temperature threshold and the speed of the aircraft engine, and output the air cooling control instruction to the forced air cooling module; the forced air cooling module is used to implement forced air cooling and heat dissipation on the heat dissipation part of the aircraft engine based on the air cooling control instruction. Through the forced heat dissipation of the forced air cooling module, the engine no longer relies on the oncoming airflow for heat dissipation, so that it can achieve good heat dissipation effect in any flight state.

Description

Technical Field

[0001] The present application relates to the field of aviation technology, and more specifically, to an air cooling system for an aircraft engine. Background Art

[0002] As we all know, aircraft engines need to maintain a certain temperature to work properly, and they generate a lot of heat during operation, so the excess heat needs to be dissipated in time. If it cannot dissipate heat effectively during work, it will cause failures such as cylinder pulling due to excessive temperature. At present, there are two main types of temperature control systems for aircraft engines: air cooling system and water cooling system.

[0003] The water cooling system uses water or coolant as a cooling medium to remove the heat from the engine cylinder through the principle of heat exchange, thereby ensuring that the engine operates at a normal temperature. The water cooling system includes a water pump, water or coolant, a cooling fan and other equipment. It is heavy and not suitable for equipment such as aircraft engines that have strict load requirements. A lighter cooling system means higher working efficiency.

[0004] The air cooling system uses air as a cooling medium and directly blows away the heat from the engine block through high-speed airflow to achieve heat dissipation. The current air cooling system uses the oncoming airflow of the aircraft during flight to directly take away the heat from the engine block. Its heat dissipation efficiency is affected by the movement speed of the aircraft, and sometimes it cannot achieve good heat dissipation effects, especially when the aircraft is flying at a low speed or hovering, at which time it cannot effectively dissipate heat. Summary of the invention

[0005] In view of this, the present application provides an air cooling system for an aircraft engine, which is used to implement forced cooling of the aircraft engine. During the cooling process, it does not rely on the oncoming airflow, so that it can achieve good heat dissipation effect in any flight state.

[0006] In order to achieve the above objectives, the proposed solution is as follows:

[0007] An air cooling system for an aircraft engine is used to implement forced heat dissipation on a cylinder of the aircraft engine. The air cooling system comprises a temperature detection module, a forced air cooling module and a main control module, wherein:

[0008] The temperature detection module is used to detect the cylinder temperature of the aircraft engine and output the cylinder temperature to the main control module;

[0009] The main control module is connected to the temperature detection module and the forced air cooling module respectively, and is used to receive the cylinder temperature, obtain an air cooling control instruction according to the relationship between the cylinder temperature and the preset temperature threshold and the rotation speed of the aircraft engine, and output the air cooling control instruction to the forced air cooling module;

[0010] The forced air cooling module is used to implement forced air cooling on the heat dissipation part of the aircraft engine based on the air cooling control instruction.

[0011] Optionally, the temperature detection module includes a temperature sensor and a temperature calculation unit, wherein:

[0012] The temperature sensor is arranged on the cylinder of the aircraft engine, and is used to detect the temperature of the cylinder, obtain and output a temperature signal to the temperature calculation unit;

[0013] The temperature calculation unit is connected to the temperature sensor and is used to process the temperature signal to obtain the cylinder temperature.

[0014] Optionally, the temperature sensor is a thermal resistor.

[0015] Optionally, the temperature calculation unit is used to process the temperature signal based on a temperature filtering algorithm to obtain the cylinder temperature.

[0016] Optionally, the forced air cooling module comprises a plurality of motors arranged on a bracket on the aircraft engine, each motor being connected to a fan facing the cylinder body, wherein:

[0017] The main control module is connected to each of the motors respectively, and the motor is used to drive the fan to blow air to the cylinder body based on the control instruction, so as to dissipate heat and reduce the temperature of the cylinder body.

[0018] Optionally, the forced air cooling module has a manual mode and an automatic mode.

[0019] Optionally, when the forced air cooling module operates in the manual mode, the motor rotates based on a field control instruction input by a user, and drives the fan to blow air to the cylinder body.

[0020] Optionally, when the forced air cooling module operates in the automatic mode, the motor rotates based on the air cooling control instruction and drives the fan to blow air to the cylinder body.

[0021] It can be seen from the above technical solution that the present application discloses an air cooling system for an aircraft engine, which is used to implement forced heat dissipation for the cylinder of the aircraft engine, and includes a temperature detection module, a forced air cooling module and a main control module. The temperature detection module is used to detect the cylinder temperature of the aircraft engine and output the cylinder temperature to the main control module; the main control module is respectively connected to the temperature detection module and the forced air cooling module, and is used to receive the cylinder temperature, and obtain the air cooling control instruction according to the relationship between the cylinder temperature and the preset temperature threshold and the speed of the aircraft engine, and output the air cooling control instruction to the forced air cooling module; the forced air cooling module is used to implement forced air cooling and heat dissipation of the heat dissipation part of the aircraft engine based on the air cooling control instruction. Through the forced heat dissipation of the forced air cooling module, the engine no longer relies on the oncoming airflow for heat dissipation, so that it can achieve good heat dissipation effect in any flight state. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0023] Figure 1 A schematic diagram of an air cooling system of an aircraft engine according to an embodiment of the present application;

[0024] Figure 2 A thermal resistance measurement circuit diagram of an embodiment of the present application;

[0025] Figure 3 This is a temperature filtering algorithm diagram of an embodiment of the present application;

[0026] Figure 4 This is a fan operation logic diagram of an embodiment of the present application. DETAILED DESCRIPTION

[0027] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0028] Embodiment 1

[0029] Figure 1 This is an air cooling system for an aircraft engine according to an embodiment of the present application.

[0030] like Figure 1As shown, this embodiment provides an air cooling system, which is applied to an aircraft engine. The aircraft engine referred to in this embodiment refers to an engine installed on a helicopter, which works based on the principle of an internal combustion engine. The helicopter can be a cross-rotor unmanned helicopter. The air cooling system provided by the present application includes a temperature detection module 10, a forced air cooling module 20 and a main control module 30.

[0031] The main control module is the core of the air cooling system, and is used to control the forced air cooling module based on the cylinder temperature output by the temperature detection module. It is connected to the temperature detection module and the forced air cooling module respectively. In addition, the control module is also connected to the ECU of the aircraft engine to obtain the speed of the aircraft engine.

[0032] The temperature detection module of the present application is arranged on the cylinder body of the aircraft engine, and is used to detect the cylinder temperature of the cylinder. The temperature detection module includes a temperature sensor 11 and a temperature calculation unit 12. The temperature sensor is an electronic component used to sense the actual temperature of the cylinder. In this embodiment, a thermal resistor is selected as the temperature sensor, and the thermal resistor measurement circuit Figure 2 Different temperatures will affect the resistance of the temperature sensor's thermal resistor. By measuring the resistance of the thermal resistor through analog signals, the temperature information of the engine block and other key parts can be obtained.

[0033] A 2000 ohm resistor is connected in series in the temperature measurement circuit. By measuring the voltage value U across the resistor m , the resistance of the PT1000 thermal resistor can be calculated. Since the temperature and resistance of the thermal resistor are linearly related, the current cylinder temperature can be obtained through linear interpolation.

[0034] Thermal resistor value R pt1000 The calculation formula is as follows. The temperature calculation unit calculates the cylinder temperature based on the following process:

[0035]

[0036] The linear interpolation formula is as follows:

[0037]

[0038] The variables in the formula are shown in the following table:

[0039]

[0040]

[0041] i is the i-th group of corresponding relationships in the table. There are 36 groups in the table. The first group is i=0, and the last group is i=35. pt1000ref [i-1]≤R pt1000 ≤Rpt1000ref [i];

[0042] R pt1000 The measured voltage value U m Calculated by the formula;

[0043] R pt1000ref [i] is the resistance value in the i-th group of data in the table;

[0044] R pt1000ref [i-1] is the resistance value in the i-1th group of data in the table.

[0045] refer to Figure 3 As shown in the figure, which is the temperature filtering algorithm diagram of this embodiment, due to the interference in the circuit, the voltage value obtained by measurement fluctuates greatly, resulting in the temperature value obtained after conversion fluctuating within the range of ±30°C, which will cause inaccurate measurement data, so a set of filtering algorithms is added on the basis of the original measurement. The filtering algorithm consists of two parts, one is the filtering algorithm for the voltage measurement value, and the other is the filtering algorithm for the temperature measurement value. Finally, the temperature value after being processed by the filtering algorithm fluctuates within ±3°C.

[0046] (1-α)u+αu y0 =u h0

[0047] (1-α)u h0 +αu y1 =u h1

[0048] (1-α)u h1 +αu y2 =u h2

[0049] ···

[0050] (1-α)u h8 +αu y9 =u h9

[0051]

[0052]

[0053] αt p0 +(1-α)t=t c1

[0054] αt p1 +(1-α)t c1 =t c2

[0055] ···

[0056] αt p49 +(1-α)t c49 =t c50

[0057] The variables in the formula are: α is the weighted average coefficient, α=0.5; u is the set initial voltage value; u yi is the original measurement value from T0 to T9; u hj is the weighted average value; u pk is the average value after weighted average processing; t is the set initial temperature value; t pk is the temperature value converted from the voltage value; t ck is the temperature measurement.

[0058] After receiving the cylinder temperature, the control module outputs a corresponding control instruction based on the cylinder temperature and the engine speed. The control instruction is used to control the forced air cooling module to force heat dissipation of the cylinder body.

[0059] The forced air cooling module in this embodiment includes four groups of motors arranged on a frame on the cylinder block of the engine. A fan is arranged at the shaft end of each motor. The control module controls the rotation of the motor based on the cylinder temperature and the engine speed. The motor drives the fan to rotate at a high speed and blows directly onto the cylinder block of the engine so that the fan drives the air to cool the cylinder block.

[0060] refer to Figure 4 As shown, the fan working logic diagram is disclosed. The forced air cooling module in this application has a manual mode and an automatic mode. Before the engine is ignited and started, the working mode can be adjusted to the manual mode, at which time the fan can be manually controlled to check whether it can work normally. After the aircraft engine is started, it can be made to work in the automatic mode.

[0061] When working in automatic mode, the forced air cooling module operates based on the control instructions of the above control module. In automatic mode, the control module takes the highest cylinder temperature among the four cylinders of the engine, and sets four gears for the fan according to the highest cylinder temperature and engine speed, which are:

[0062] 1) In the stationary state, in the first gear, the engine is stopped and the ECU is turned off;

[0063] 2) In hot engine state, gear 2, the maximum cylinder temperature is higher than 120°C or the motor speed is greater than 6000 rpm;

[0064] 3) Normal state 3 gear, the maximum cylinder temperature is higher than 150℃;

[0065] 4) In the 4th gear of the boost state, the maximum cylinder temperature is higher than 180℃.

[0066] By controlling the forced air cooling module to operate in the above-mentioned gear position, the cylinder temperature of the engine is ensured to be between 150°C and 180°C, so as to maintain a relatively good working condition.

[0067] It can be seen from the above technical scheme that this embodiment provides an air cooling system for an aircraft engine, which is used to implement forced heat dissipation for the cylinder of the aircraft engine, and includes a temperature detection module, a forced air cooling module and a main control module. The temperature detection module is used to detect the cylinder temperature of the aircraft engine and output the cylinder temperature to the main control module; the main control module is connected to the temperature detection module and the forced air cooling module respectively, and is used to receive the cylinder temperature, and obtain the air cooling control instruction according to the relationship between the cylinder temperature and the preset temperature threshold and the speed of the aircraft engine, and output the air cooling control instruction to the forced air cooling module; the forced air cooling module is used to implement forced air cooling and heat dissipation of the heat dissipation part of the aircraft engine based on the air cooling control instruction. Through the forced heat dissipation of the forced air cooling module, the engine no longer relies on the oncoming airflow for heat dissipation, so that it can achieve good heat dissipation effect in any flight state.

[0068] The various embodiments in this specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other.

[0069] Although the preferred embodiments of the present invention have been described, those skilled in the art may make additional changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the embodiments of the present invention.

[0070] Finally, it should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or terminal device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or terminal device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or terminal device including the elements.

[0071] The technical solution provided by the present invention is introduced in detail above. Specific examples are used in this article to illustrate the principle and implementation mode of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core idea. At the same time, for those skilled in the art, according to the idea of ​​the present invention, there will be changes in the specific implementation mode and application scope. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. An air cooling system for an aircraft engine, used for forced heat dissipation of a cylinder of the aircraft engine, characterized in that: The air cooling system includes a temperature detection module, a forced air cooling module and a main control module, wherein: The temperature detection module includes a temperature sensor and a temperature calculation unit. The temperature sensor is arranged on the cylinder of the aircraft engine and is used to detect the temperature of the cylinder, obtain and output a temperature signal to the temperature calculation unit. The temperature calculation unit is connected to the temperature sensor and is used to process the temperature signal based on a temperature filtering algorithm to obtain the cylinder temperature of the aircraft engine and output the cylinder temperature to the main control module. The temperature filtering algorithm includes a filtering algorithm for voltage measurement values ​​and a filtering algorithm for temperature measurement values. The main control module is connected to the electronic controller ECU of the aircraft engine and is used to obtain the rotation speed of the aircraft engine; The main control module is connected to the temperature detection module and the forced air cooling module respectively, and is used to receive the cylinder temperature, obtain an air cooling control instruction according to the relationship between the cylinder temperature and the preset temperature threshold and the rotation speed of the aircraft engine, and output the air cooling control instruction to the forced air cooling module; The forced air cooling module includes a plurality of motors arranged on a bracket on the aircraft engine, each motor is connected to a fan facing the cylinder body, and the main control module is connected to each of the motors respectively. The motor is used to drive the fan to blow air to the cylinder body based on the control instruction, so as to dissipate heat and cool the cylinder body.

2. The air cooling system according to claim 1, characterized in that: The temperature sensor is a thermal resistor.

3. The air cooling system according to claim 1, characterized in that: The forced air cooling module has a manual mode and an automatic mode.

4. The air cooling system according to claim 3, characterized in that: When the forced air cooling module operates in the manual mode, the motor rotates based on the on-site control command input by the user and drives the fan to blow air to the cylinder body.

5. The air cooling system according to claim 3, characterized in that: When the forced air cooling module operates in the automatic mode, the motor rotates based on the air cooling control instruction and drives the fan to blow air to the cylinder body.

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