Thermal protection and power generation integrated device based on thermodynamic cycle

Abstract

The invention relates to the technical field of thermal protection power generation, and discloses a thermal protection power generation integrated device based on thermodynamic cycle. The device comprises a Stirling thermodynamic cycle assembly used for converting heat energy into mechanical energy and a linear motor used for converting the mechanical energy into electric energy, and the Stirling thermodynamic cycle assembly is connected with the linear motor. The Stirling thermodynamic cycle assembly comprises a heating area, a heat insulation area, a cooling area, a conformal heating face, a working medium inflation inlet and a cooling flow channel, the heating area and the cooling area are connected through the heat insulation area, and the Stirling thermodynamic cycle assembly is arranged on the inner wall face of the aircraft through the conformal heating face. Heat on the inner wall face of the aircraft is transferred to the heating area through the conformal heating face, a cooling medium is connected into the cooling flow channel to be used for providing a cold source for the cooling area, and a working medium is inflated into the Stirling thermodynamic cycle assembly through the working medium inflation opening to conduct Stirling cycle.

Description

Technical Field

[0001] The present invention relates to the technical field of thermal protection power generation, and in particular to an integrated thermal protection power generation device based on a thermodynamic cycle. Background Art

[0002] The integrated thermal protection and power generation device is a device that converts thermal energy and finally outputs electrical energy. Thermodynamic cycle refers to the process of a thermodynamic system returning to its initial state after a series of intermediate processes. Generally, in this process, the thermodynamic system will convert thermal energy into mechanical energy. Based on the thermodynamic cycle, the converted mechanical energy is converted into electrical energy, that is, the process of converting thermal energy into electrical energy is completed.

[0003] At present, the existing integrated thermal protection and power generation devices in the prior art are relatively complex and have low conversion efficiency. Summary of the invention

[0004] The purpose of the present invention is to overcome the deficiencies of the prior art and to provide an integrated thermal protection and power generation device based on a thermodynamic cycle, which can solve the problems in the prior art mentioned above.

[0005] The technical solution of the present invention is: a thermal protection and power generation integrated device based on thermal cycle, wherein the device includes a Stirling thermal cycle component for converting thermal energy into mechanical energy and a linear motor for converting mechanical energy into electrical energy, the Stirling thermal cycle component is connected to the linear motor, the Stirling thermal cycle component includes a heating zone, an insulating zone, a cooling zone, a conformal heating surface, a working fluid charging port and a cooling channel, the heating zone and the cooling zone are connected through the insulating zone, the Stirling thermal cycle component is arranged on the inner wall of the aircraft through the conformal heating surface, the heat on the inner wall of the aircraft is transferred to the heating zone through the conformal heating surface, the cooling medium is connected to the cooling channel to provide a cold source for the cooling zone, and the working fluid is charged into the Stirling thermal cycle component through the working fluid charging port to perform a Stirling cycle.

[0006] Preferably, the Stirling thermal cycle component also includes a gas distribution piston, a power piston, an expansion chamber and a compression chamber. When the power piston is at the lowest point, the working fluid is in the compression chamber, and as the power piston rises, the working fluid is compressed. Subsequently, the working fluid undergoes an isochoric heating process along the passages in the cooling zone, the insulation zone and the heating zone. The heated working fluid enters the expansion chamber, and expands as the pressure and temperature in the chamber increase, pushing the gas distribution piston downward, and driving the power piston to move downward at the same time. After completing the expansion work, the working fluid will be cooled along the passages in the heating zone, the insulation zone and the cooling zone, and the cooled working fluid enters the compression chamber.

[0007] Preferably, the linear motor includes a motor mover and a motor stator, and the power piston is coupled with the motor mover during the up and down movement, and then the motor mover cooperates with the motor stator to realize power generation by cutting magnetic flux lines.

[0008] Preferably, the heating zone includes a working fluid heating pipe, the insulation zone includes a regenerator, and the cooling zone includes a working fluid cooling pipe.

[0009] Preferably, the cooling medium is cooling oil.

[0010] Through the above technical solution, the heat energy of the aircraft's heating wall can be used to output mechanical energy through the Stirling cycle of the working fluid, and then converted into electrical energy for external output through the linear stepper generator. In this way, the heat generated by the high-heat components inside the aircraft can be reduced, and electrical energy can be provided for the equipment on the aircraft, making the overall structure of the equipment more compact and improving the reliability of the equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] The included drawings are used to provide a further understanding of the embodiments of the present invention, which constitute a part of the specification, are used to illustrate the embodiments of the present invention, and together with the text description, explain the principles of the present invention. Obviously, the drawings in the following description are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0012] Figure 1 A three-dimensional diagram of a thermal protection and power generation integrated device based on a thermodynamic cycle provided by an embodiment of the present invention;

[0013] Figure 2 It is a cross-sectional view of a thermal protection power generation integrated device in an embodiment of the present invention;

[0014] Figure 3 It is a cross-sectional view of the integrated thermal protection and power generation device in an embodiment of the present invention.

[0015] Description of Reference Numerals

[0016] 1 heating zone, 2 insulation zone, 3 cooling zone, 4 linear motor, 5 conformal heating surface, 6 working fluid charging port, 7 gas distribution piston, 8 power piston, 9 cooling channel, 10 motor mover, 11, motor stator, 12 expansion chamber, 13 working fluid heating tube, 14 regenerator, 15 working fluid cooling tube, 16 compression chamber. DETAILED DESCRIPTION

[0017] Below in conjunction with accompanying drawing, specific embodiment of the present invention is described in detail.In the following description, for explanation and not limiting purpose, set forth specific details, to help fully understand the present invention.But it is obvious to those skilled in the art that also can practice the present invention in other embodiment that breaks away from these specific details.

[0018] It should be noted that, in order to avoid obscuring the present invention due to unnecessary details, only the device structure and / or processing steps closely related to the solution according to the present invention are shown in the accompanying drawings, while other details that are not closely related to the present invention are omitted.

[0019] like Figure 1-3 As shown, an embodiment of the present invention provides an integrated thermal protection and power generation device based on a thermodynamic cycle, wherein the device includes a Stirling thermodynamic cycle component for converting thermal energy into mechanical energy and a linear motor 4 for converting mechanical energy into electrical energy, the Stirling thermodynamic cycle component is connected to the linear motor 4, the Stirling thermodynamic cycle component includes a heating zone 1, an insulation zone 2, a cooling zone 3, a conformal heating surface 5, a working fluid charging port 6 and a cooling channel 9, the heating zone 1 and the cooling zone 3 are connected through the insulation zone 2, the Stirling thermodynamic cycle component is arranged (fixed) on the inner wall of the aircraft through the conformal heating surface 5, the heat (i.e., heat source) on the inner wall of the aircraft is transferred to the heating zone 1 through the conformal heating surface 5, the cooling medium is connected to the cooling channel 9 to provide a cold source for the cooling zone 3, and the working fluid is charged into the Stirling thermodynamic cycle component through the working fluid charging port 6 to perform a Stirling cycle.

[0020] That is, before use, the working fluid is charged into the Stirling thermal cycle component part through the working fluid charging port 6 , and the cooling medium is connected to the cooling flow channel 9 .

[0021] Through the above technical solution, the heat energy of the aircraft's heating wall can be used to output mechanical energy through the Stirling cycle of the working fluid, and then converted into electrical energy for external output through the linear stepper generator. In this way, the heat generated by the high-heat components inside the aircraft can be reduced, and electrical energy can be provided for the equipment on the aircraft, making the overall structure of the equipment more compact and improving the reliability of the equipment.

[0022] According to one embodiment of the present invention, the Stirling thermal cycle component also includes a gas distribution piston 7, a power piston 8, an expansion chamber 12 and a compression chamber 16. When the power piston 8 is at the lowest point, the working fluid is in the compression chamber 16, and as the power piston 8 rises, the working fluid is compressed. Subsequently, the working fluid undergoes an isochoric heating process along the passages of the cooling zone 3, the insulation zone 2 and the heating zone 1. The heated working fluid enters the expansion chamber 12, and expands as the pressure and temperature in the chamber increase, pushing the gas distribution piston 7 downward, and driving the power piston 8 to move downward at the same time. After completing the expansion work, the working fluid will be cooled along the passages of the heating zone 1, the insulation zone 2 and the cooling zone 3, and the cooled working fluid enters the compression chamber 16.

[0023] According to one embodiment of the present invention, the linear motor 4 includes a motor mover 10 and a motor stator 11, and the power piston 8 is coupled with the motor mover 10 during the up and down movement, and then the motor mover 10 cooperates with the motor stator 11 to realize cutting magnetic flux lines to generate electricity.

[0024] According to an embodiment of the present invention, the heating zone 1 includes a working fluid heating pipe 13 , the insulation zone 2 includes a regenerator 14 , and the cooling zone 3 includes a working fluid cooling pipe 15 .

[0025] Specifically, when the power piston 8 is at the lowest point, the working fluid is in the compression chamber 16, and as the power piston 8 rises, the working fluid is compressed. Subsequently, the working fluid undergoes an isochoric heating process along the passages of the working fluid cooling tube 15, the regenerator 14 and the heating tube 13. The heated working fluid enters the expansion chamber 12, and expands as the pressure and temperature in the chamber increase, pushing the valve piston 7 downward, and driving the power piston 8 to move downward at the same time. After completing the expansion work, the working fluid will be cooled along the passages of the working fluid heating tube 13, the regenerator 14 and the working fluid cooling tube 15, and the cooled working fluid enters the compression chamber 16, after which a new cycle can begin.

[0026] That is, after a temperature difference is generated between the high-temperature wall and the cooling medium, the working fluid circulates between the expansion chamber 12, the working fluid heating pipe 13, the regenerator 14, the working fluid cooling pipe 15 and the compression chamber 16 to complete the Stirling cycle.

[0027] According to an embodiment of the present invention, the cooling medium is cooling oil.

[0028] In this way, the circulation of the working medium can be guaranteed.

[0029] By iteratively optimizing the design parameters, it is possible to further ensure that the overall structure of the device is compact and the conversion efficiency meets the requirements. Specifically, the thermal protection and power generation integrated device can perform parameterized design on the thermal cycle components for different environments. The method is a combination of numerical simulation virtual calculation, finite element simulation verification and experimental verification. The present invention provides a method for designing parameters of a thermal protection and power generation integrated device based on a thermal cycle, comprising the following steps:

[0030] 1. According to the typical one-dimensional analysis method, it is assumed that the working frequency of the Stirling cycle is constant, the heat transfer efficiency is 100%, the volume of the working chamber changes according to the sinusoidal law, and the working fluid is regarded as an ideal gas. According to the given cold source and heat source temperature, the numerical relationship between the Stirling cycle output work and the dead volume ratio, pressure, scavenging volume ratio, and piston phase angle parameters is obtained. Under the dimensions limited by the specific case, the appropriate parameters are determined as the initial design parameters;

[0031] 2. Based on the determined parameters, the law of conservation of energy is used as the basis for analysis, and the heat loss of the regenerator and the loss of the fluid flowing in the pipeline are considered to establish a mathematical model of the Stirling cycle. The output and efficiency of the Stirling cycle are calculated based on this mathematical model to obtain specific design parameters, such as the scavenging volume of the expansion chamber 12 and the compression chamber 16, and the length and cross-section of the working fluid heating pipe 13 and the working fluid cooling pipe 15;

[0032] 3. According to the design parameters obtained from the model, determine the appropriate arrangement scheme for different aircraft internal environments, design the appropriate shape of the conformal heating surface 5, and establish a three-dimensional model;

[0033] 4. Use CFD software to perform thermal simulation and fluid simulation on the three-dimensional model of the Stirling cycle to verify the heating and cooling effects of the heat source and cold source on the working fluid heating pipe 13 and the working fluid cooling pipe 15, as well as the heat recovery efficiency of the regenerator 14, and the pressure changes inside the expansion chamber 12 and the compression chamber 16;

[0034] 5. Since the previous mathematical model equates the temperature of the heat source and the cold source to the working fluid temperature, after completing step 4, the more accurate working fluid temperature is substituted into the mathematical model of step 2 to iteratively verify the output efficiency and output power;

[0035] 6. Select a suitable linear motor 4 according to the output work of the iterative Stirling cycle and the size of the Stirling cycle components;

[0036] 7. Conduct physical tests to verify whether the output efficiency and output power of the integrated thermal protection power generation device meet the requirements.

[0037] Those skilled in the art should understand that the above design method is merely exemplary and is not intended to limit the present invention.

[0038] It can be seen from the above embodiments that the thermal protection and power generation integrated device of the present invention can provide electrical energy for the equipment in the aircraft and reduce the thermal environment input. Specifically, the Stirling thermal cycle is used to absorb thermal energy, and the linear motor is used as a tool for power generation. Through the compact structural design and the optimized design of the Stirling cycle, the severe thermal environment problem of the electronic devices inside the aircraft is solved.

[0039] Features described and / or illustrated above for one embodiment may be used in the same or similar manner in one or more other embodiments, and / or combined with or used in place of features in other embodiments.

[0040] It should be emphasized that the term “include / comprises” when used herein refers to the presence of features, integers, steps or components, but does not exclude the presence or addition of one or more other features, integers, steps, components or combinations thereof.

[0041] The above devices and methods of the present invention can be implemented by hardware, or by hardware combined with software. The present invention relates to such a computer-readable program, which, when executed by a logic component, enables the logic component to implement the above-mentioned devices or components, or enables the logic component to implement the above-mentioned various methods or steps. The present invention also relates to a storage medium for storing the above-mentioned program, such as a hard disk, a magnetic disk, an optical disk, a DVD, a flash memory, etc.

[0042] The many features and advantages of these embodiments are apparent from this detailed description, and thus the appended claims are intended to cover all such features and advantages of these embodiments that fall within their true spirit and scope. Furthermore, since numerous modifications and changes will readily occur to those skilled in the art, it is not intended that the embodiments of the invention be limited to the exact construction and operation illustrated and described, but rather all suitable modifications and equivalents falling within the scope thereof are intended to be covered.

[0043] Parts of the present invention that are not described in detail are well known to those skilled in the art.

Claims

1. A thermal protection power generation integrated device based on a thermodynamic cycle, characterized in that: The device comprises a Stirling thermal cycle component for converting thermal energy into mechanical energy and a linear motor (4) for converting mechanical energy into electrical energy. The Stirling thermal cycle component is connected to the linear motor (4). The Stirling thermal cycle component comprises a heating zone (1), an insulating zone (2), a cooling zone (3), a conformal heating surface (5), a working fluid charging port (6) and a cooling channel (9). The heating zone (1) and the cooling zone (3) are connected via the insulating zone (2). The Stirling thermal cycle component is arranged on the inner wall surface of the aircraft via the conformal heating surface (5). The heat on the inner wall surface of the aircraft is transferred to the heating zone (1) via the conformal heating surface (5). A cooling medium is connected to the cooling channel (9) to provide a cold source for the cooling zone (3). The working fluid is charged into the Stirling thermal cycle component via the working fluid charging port (6) to perform a Stirling cycle.

2. The device according to claim 1, characterized in that The Stirling thermal cycle assembly further comprises a gas distribution piston (7), a power piston (8), an expansion chamber (12) and a compression chamber (16). When the power piston (8) is at the lowest point, the working medium is compressed in the compression chamber (16) as the power piston (8) rises. Subsequently, the working medium undergoes an isochoric heating process along the passages of the cooling zone (3), the adiabatic zone (2) and the heating zone (1). The heated working medium enters the expansion chamber (12) and expands as the pressure and temperature in the chamber increase, pushing the gas distribution piston (7) downward and driving the power piston (8) to move downward. After completing the expansion work, the working medium is cooled along the passages of the heating zone (1), the adiabatic zone (2) and the cooling zone (3). The cooled working medium enters the compression chamber (16).

3. The device according to claim 2, characterized in that The linear motor (4) comprises a motor mover (10) and a motor stator (11), and the power piston (8) is coupled with the motor mover (10) during the process of moving up and down, so that the motor mover (10) cooperates with the motor stator (11) to realize cutting magnetic flux lines to generate electricity.

4. The device according to claim 3, characterized in that The heating zone (1) comprises a working fluid heating pipe (13), the heat-insulating zone (2) comprises a heat regenerator (14), and the cooling zone (3) comprises a working fluid cooling pipe (15).

5. The device according to claim 4, characterized in that The cooling medium is cooling oil.

Images