A structure for high-pressure initiation of a detonation combustion chamber by using a Tesla turbine

Abstract

The application discloses a structure for realizing high-pressure detonation of a detonation combustion chamber by using a Tesla turbine, comprising a detonation combustion chamber, a Tesla turbine and a motor; the inlet of the Tesla turbine is connected with the outlet of the detonation combustion chamber; and the motor provides a starting rotating speed for the rotor of the Tesla turbine. The radial pressure gradient of the Tesla turbine is used to create an atmosphere of high pressure and low flow rate in the detonation combustion chamber, so that the initial detonation pressure is improved. Meanwhile, the Tesla turbine can convert most of the energy of detonation gas pulsation in a period into shaft work for output by using viscous force, and the slit scale of the Tesla turbine is far smaller than the detonation wave propagation limit criterion, so that the Tesla turbine can be used for quenching of detonation waves, and has great performance gain and application value.

Description

Technical Field

[0001] The present invention relates to the technical field of detonation turbine engines, and in particular to a structure that utilizes a Tesla turbine to achieve high-pressure detonation in a detonation combustion chamber. Background Art

[0002] With the development of society and industry, the requirements for power plant efficiency, power density, and adaptability to new fuels are increasing. An internal combustion engine is a device that burns fuel internally and uses gas to directly generate work. Common types, such as reciprocating piston engines, triangular rotor engines, turbine engines, and pulse engines, all fall under this category. They convert the thermal energy of fuel into mechanical energy, offering a convenient and reliable method. The internal combustion engine has a century-long history. As a representative power plant, it serves every aspect of our lives and is a vital component of modern society. Combustion is one of the core elements of the internal combustion engine, and the development of internal combustion engine technology is inseparable from the advancement of combustion science and technology. Deflagration waves and detonation waves are two types of combustion waves found in nature. Due to their theoretical advantages over deflagration, the study of detonation combustion has received significant attention in recent decades. Due to the self-pressurization properties of detonation waves, detonation combustion can reach higher temperatures than isobaric combustion at the same initial pressure, resulting in higher thermal efficiency.

[0003] There are three main existing detonation combustion application methods: pulse detonation, rotating detonation, and stationary detonation. The first two are relatively easy to implement technically, and numerous technical solutions have been developed to date. In these solutions, whether it is a pure detonation engine that directly uses the products of detonation combustion for propulsion, or a detonation turbine engine that combines a detonation combustion chamber with a traditional turbine engine, the achievable initial detonation pressure within the detonation combustion chamber is generally atmospheric pressure. This means that while detonation combustion has the advantage of self-pressurization compared to isobaric combustion, an isobaric combustion chamber can achieve higher pressure and thermal efficiency under the action of the compressor, and the efficiency of a detonation combustion chamber paired with a traditional bladed turbine is also lower than that of an isobaric combustion chamber. Furthermore, increasing the initial detonation pressure of the detonation combustion chamber can make the DDT (Deflagration to Detonation Transition) and detonation wave propagation process faster and more stable, making increasing the initial detonation pressure of the detonation combustion chamber of great significance. However, in existing engines based on detonation combustion, increasing the initial detonation pressure in the combustion chamber often leads to unstable flow field and difficulty in ignition. Therefore, there is an urgent need for a solution to create a high-pressure, low-flow-velocity atmosphere in the detonation combustion chamber that is easy to ignite using means with application value. Summary of the Invention

[0004] The purpose of the present invention is to overcome the deficiencies of the above-mentioned prior art and provide a structure that utilizes a Tesla turbine to achieve high-pressure initiation of a detonation combustion chamber. The Tesla turbine is arranged at the outlet of the detonation combustion chamber based on the principle that a radial pressure gradient can be generated during operation. The high-speed rotation of the Tesla turbine is utilized to increase the static pressure of the premixed combustible gas in the detonation combustion chamber and reduce the flow rate, thereby achieving high-pressure initiation of the detonation combustion chamber.

[0005] To achieve the above object, the technical solution of the present invention is:

[0006] A structure for achieving high-pressure detonation in a detonation combustion chamber using a Tesla turbine, comprising a detonation combustion chamber, a Tesla turbine, and a motor;

[0007] The inlet of the Tesla turbine is connected to the outlet of the detonation combustion chamber;

[0008] The electric motor provides the starting speed for the rotor of the Tesla turbine.

[0009] Furthermore, the Tesla turbine is used to increase the static pressure in the detonation combustion chamber and reduce the gas flow rate at the ignition moment, while converting the kinetic energy of the detonation gas into mechanical energy for output.

[0010] Furthermore, the Tesla turbine is composed of a plurality of coaxially rotating discs, the centers of the discs are open, and gaps are left between the discs; the inlet at the outer diameter of the Tesla turbine disc is connected to the outlet of the detonation combustion chamber.

[0011] Furthermore, high-speed fluid enters tangentially from the gap along the outer diameter of the disk, and low-speed fluid is discharged from the opening at the center of the disk. Under the action of viscous force, momentum exchange occurs between the fluid and the disk, and part of the kinetic energy of the fluid is converted into shaft work of the Tesla turbine and output to the outside world.

[0012] Furthermore, the detonation combustion chamber is a pulse detonation combustion chamber, and a plurality of them are provided to form a pulse detonation combustion chamber group; the plurality of pulse detonation combustion chambers are arranged in a ring around the Tesla turbine and each outlet thereof is connected to an inlet corresponding to the outer diameter of the Tesla turbine.

[0013] Furthermore, each of the pulse detonation combustion chambers adopts a valve and isolation control strategy, and its working cycle is divided into three stages: isolation, filling, and detonation; the Tesla turbine adjusts the initial detonation pressure during the isolation and filling stages, and the gas or gas-liquid mixture entering the pulse detonation Tesla turbine engine flows through the detonation combustion chamber group and the Tesla turbine and is discharged to the atmosphere. At this time, the static pressure and flow rate of the fluid in the combustion chamber channel are determined by the intake pressure and the rotational speed of the Tesla turbine.

[0014] Furthermore, the flow passages between the Tesla turbine discs are used to extinguish the detonation wave.

[0015] Furthermore, the motor is used as a generator after the fuel starts to burn and the Tesla turbine reaches a specified speed, generating electrical energy and outputting it to the outside.

[0016] Furthermore, the detonation combustion chamber is a rotating detonation combustion chamber, and a plurality of them are provided to form a rotating detonation combustion chamber group; the plurality of rotating detonation combustion chambers are arranged in a ring around the Tesla turbine and each outlet thereof is connected to an inlet corresponding to the outer diameter of the Tesla turbine.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] 1. The Tesla turbine utilizes the radial pressure gradient to create a high-pressure, low-velocity atmosphere within the detonation combustion chamber, increasing the initial detonation pressure. Furthermore, the Tesla turbine utilizes viscous forces to convert most of the energy within the detonation gas pulsation cycle into shaft power for output. Furthermore, the Tesla turbine's slit dimensions are far smaller than the detonation wave propagation limit, allowing it to be used to extinguish detonation waves, resulting in significant performance gains and application value.

[0019] 2. The detonation Tesla turbine device proposed in the present invention can achieve precise control of the initial detonation pressure in the detonation combustion chamber by adjusting the rotational speed of the Tesla turbine and the intake pressure of the combustion chamber. The initial detonation pressure can be as high as several times the atmospheric pressure.

[0020] 3. The present invention increases the initial detonation pressure of the detonation combustion chamber, multiplies the power density of the detonation combustion chamber within a limited frequency, and enhances the stability of the detonation combustion. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is the basic matching structure of the detonation combustion chamber and the Tesla turbine;

[0022] Figure 2 For the coordination of pulse detonation combustion chamber and Tesla turbine;

[0023] Figure 3 The ideal static pressure curve of the pressure measuring point at the tail end of the combustion chamber of the pulse detonation Tesla turbine engine;

[0024] Figure 4 The radial pressure gradient generated in the Tesla turbine and the increased static pressure in the adjacent combustion chamber channel;

[0025] Figure 5 For the coordination of the rotating detonation combustion chamber and the Tesla turbine;

[0026] Figure 6 The ideal static pressure curve of the pressure measuring point at the tail end of the combustion chamber of a rotating detonation Tesla turbine engine;

[0027] In the figure: 1. Detonation combustion chamber (pulse detonation); 2. Tesla turbine (spoke structure); 3. Pulse detonation combustion chamber group; 4. Combustion chamber and turbine sealing cover; 5. Tesla turbine (cantilever structure); 6. High-speed motor; 7. Cantilever structure Tesla turbine single-layer flow channel; 8. Rotating detonation combustion chamber group; 9. Turbine sealing cover; 10. Tesla turbine (hollow shaft structure); 11. High-speed motor. DETAILED DESCRIPTION

[0028] The technical solution of the present invention is further described below with reference to the accompanying drawings and embodiments.

[0029] Example 1:

[0030] See Figure 1 As shown, the basic matching structure of the detonation combustion chamber and the Tesla turbine mainly includes the detonation combustion chamber 1, the Tesla turbine 2 and the high-speed motor.

[0031] Among them, the detonation combustion chamber is used for detonation combustion; the inlet of the Tesla turbine is connected to the outlet of the detonation combustion chamber to increase the static pressure in the detonation combustion chamber and reduce the gas flow rate at the ignition moment, and at the same time, the kinetic energy of the detonation gas can be converted into mechanical energy for output. The high-speed motor is used to provide the starting speed for the Tesla turbine rotor so that the initial detonation pressure in the detonation combustion chamber reaches the specified value.

[0032] In this way, the principle that the Tesla turbine can generate a radial pressure gradient during operation is adopted, and a Tesla turbine is set at the outlet of the detonation combustion chamber. The high-speed rotation of the Tesla turbine is used to increase the static pressure of the premixed combustible gas in the detonation combustion chamber and reduce the flow rate, thereby achieving high-pressure initiation of the detonation combustion chamber.

[0033] Specifically, the Tesla turbine 2 consists of multiple coaxially rotating discs with gaps between them. The discs are open at their centers, leaving gaps between them. The inlet at the outer diameter of the Tesla turbine discs is connected to the outlet of the detonation combustion chamber. High-speed fluid enters tangentially through the gaps along the outer diameter of the discs, while low-speed fluid exits through the opening at the center. Viscous forces exchange momentum between the fluids and the discs, converting most of the fluid's kinetic energy into shaft work for the Tesla turbine and outputting it to the outside. It should be noted that the terms "high-speed fluid" and "low-speed fluid" in this application are relative terms, meaning that the high-speed fluid is faster than the low-speed fluid, and there are no specific speed limits. Furthermore, the gaps between the Tesla turbine discs can be used to quench the detonation wave. The Tesla turbine can also be driven by isolation gas, auxiliary gas, or other means to provide a starting speed. After the engine starts, the high-speed motor can function as a generator, generating electrical energy for output. Engine start-up refers to the initiation of fuel combustion and the start of Tesla turbine rotation.

[0034] The structure of the Tesla turbine 2 can be a spoke structure, a cantilever structure, a hollow shaft structure, etc. The spoke structure is that the connection between the disc and the rotating shaft is designed to be spoke-shaped, and the gap between the spokes is used for exhaust; the cantilever structure is that the rotating shaft is fixed in the center hole of the bottom disc, and multiple penetrating pillars are fixed on the bottom disc in a circular array, and the upper disc is arranged and fixed on the penetrating pillars in a coaxial and parallel manner without contact; the hollow shaft structure is that a hollow main shaft with openings on the side passes through and is fixed in the center holes of multiple discs, and the openings on the side of the hollow main shaft are used for exhaust.

[0035] Example 2:

[0036] The structure of the detonation combustion chamber high pressure detonation using the Tesla turbine involved in this embodiment is as follows Figure 2 As shown, its main body consists of a pulse detonation combustion chamber group 3, a combustion chamber and turbine sealing cover 4, a Tesla turbine 5, and a high-speed motor 6. The pulse detonation combustion chamber group 3 has multiple pulse detonation combustion chambers arranged in a ring around the Tesla turbine 5, and each outlet thereof is connected to the outer diameter of the Tesla turbine 5, forming a Figure 2 The flow path shown by the thick solid arrow is a pulse detonation Tesla turbine engine.

[0037] To avoid wasting fuel during the filling process, each combustion chamber in the pulse detonation combustion chamber group 3 adopts a valve and isolation control strategy, and its working cycle is divided into three stages: isolation, filling, and detonation. Isolation refers to using non-combustible gas (air or inert gas) to purge the exhaust gas in the combustion chamber channel, cool it, and prevent the next combustible gas entering from being directly ignited by the high-temperature exhaust gas from the previous round; filling refers to the combustible gas filling the detonation tube; detonation refers to the spark plug igniting the premixed combustible gas in the tube to produce deflagration. The deflagration flame accelerates in the detonation tube, and when its speed reaches a certain level, it will turn into a detonation flame, that is, the DDT (Deflagration to Detonation Transition) process, and the detonation is successful at this time. The Tesla turbine 5 adjusts the initial detonation pressure during the isolation and filling stages. The gas or gas-liquid mixture entering the pulse detonation Tesla turbine engine flows through the detonation combustion chamber group 3 and the Tesla turbine 5 and is discharged into the atmosphere. At this time, the static pressure and flow rate of the fluid in the combustion chamber channel are determined by the intake pressure and the rotational speed of the Tesla turbine 5. The static pressure of the fluid in the combustion chamber channel is positively correlated with the intake pressure and the rotational speed of the Tesla turbine 5. The flow rate of the fluid in the combustion chamber channel is positively correlated with the intake pressure and the rotational speed of the Tesla turbine 5.

[0038] In the process of pulse detonation Tesla turbine engine from starting to entering the cycle, the ideal static pressure curve of any pressure measuring point at the tail (exit) of pulse detonation combustion chamber group 3 is as follows: Figure 3As shown, the isolation gas takes high-pressure air as an example, and the fuel gas takes ethylene-air high-pressure premixed gas as an example. The fuel gas pressure is higher than the isolation gas pressure. When the engine is started, step a is to open the isolation gas intake valve (the fuel gas intake valve remains closed), and the isolation gas quickly flows into one of the pulse detonation combustion chamber group 3. The flow rate at the measuring point increases due to the increase in total gas pressure, and the static pressure at the measuring point increases to a certain stable value. Step b is to start the high-speed motor 6 to gradually increase the speed of the Tesla turbine 5 to the specified speed of step c. Thereafter, the Tesla turbine 5 maintains the speed at step c unchanged. In the process of increasing the speed of the Tesla turbine 5, the radial pressure gradient and flow resistance continue to increase, so that the back pressure at the outlet of the pulse detonation combustion chamber group 3 becomes higher and higher, thereby reducing the gas flow rate in the combustion chamber channel and increasing the static pressure at the pressure measuring point. Figure 4 As shown, at this time, the static pressure at the measuring point is cd platform, step d is to close the isolation gas intake valve and open the fuel gas intake valve instantly at the same time, the sudden increase in intake pressure causes the static pressure at the measuring point to rise to de platform, and the fuel gas begins to enter the combustion chamber channel, step e is to close the fuel gas intake valve (the isolation gas intake valve remains closed), at this time the fuel gas in the combustion chamber channel loses the push of the high-pressure gas source and further fills the combustion chamber channel by its own high-pressure expansion, the isolation gas before the fuel gas front is pushed out of the combustion chamber channel and discharged into the atmosphere, the static pressure at the measuring point also gradually decays due to this process similar to the degassing of a high-pressure container, at this time the flow velocity in the combustion chamber channel is also decreasing, and when the flow velocity in the combustion chamber channel drops to a certain ignitable value, step f makes the pulse The spark plug at the air inlet of the impulse detonation combustion chamber ignites, and DDT starts in the combustion chamber channel and detonation occurs. The detonation wave sweeps across the pressure measuring point at the tail of the combustion chamber channel, causing its pressure to surge and decay rapidly. The detonation wave extinguishes after entering the narrow gap of the Tesla turbine 5. The high-speed airflow further expands and accelerates through the nozzle at the tail of the combustion chamber channel and enters the Tesla turbine 5 to perform work. When the pressure at the gas discharge measuring point in the combustion chamber channel decays to a certain set value, step a' can be started. Step a' is to open the isolation gas intake valve (the fuel gas intake valve remains closed), and then a cycle is started again with a'def as the period. There may be operating phase differences between the pulse detonation combustion chambers in the pulse detonation combustion chamber group 3.

[0039] This mechanical structure and working method realizes pulse detonation combustion with an initial detonation pressure higher than atmospheric pressure and adjustable initial detonation pressure, and at the same time has the ability to extinguish the explosion with a detonation wave and perform work with detonation gas.

[0040] Example 3:

[0041] The structure of the detonation combustion chamber high pressure detonation using the Tesla turbine involved in this embodiment is as follows Figure 5As shown, its main body consists of a rotating detonation combustion chamber group 8, a turbine sealing cover 9, a Tesla turbine 10, and a high-speed motor 11. The rotating detonation combustion chamber group 8 consists of multiple rotating detonation combustion chambers, which are arranged in a ring around the Tesla turbine 10 and each outlet thereof is connected to the outer diameter of the Tesla turbine 10, forming a Figure 5 The flow path shown by the thick solid arrow is the structure of the rotating detonation Tesla turbine engine.

[0042] During the startup process of the rotating detonation Tesla turbine engine, the Tesla turbine 10 provides back pressure and flow resistance for the rotating detonation combustion chamber group 8, thereby increasing the initial detonation pressure. The ideal static pressure curve of any pressure measuring point at the head of the rotating detonation combustion chamber (at the inlet of the rotating detonation combustion chamber group 8) is as follows: Figure 6 As shown in the figure, the auxiliary gas takes high-pressure air as an example, and the fuel gas takes high-pressure hydrogen-oxygen premixed gas as an example. The fuel gas pressure is higher than the auxiliary gas pressure. In step a, the auxiliary gas is introduced into the rotating detonation combustion chamber group 8. The flow rate at the measuring point increases due to the increase in the total pressure of the airflow, and the static pressure at the measuring point increases to a certain stable value. In step b, the high-speed motor 11 is started to gradually increase the speed of the Tesla turbine 10 to the specified speed of step c. Thereafter, if there is no need to change the initial detonation pressure, the Tesla turbine 10 maintains the speed at step c unchanged. As the radial pressure gradient and flow resistance of the Tesla turbine 10 increase, the gas flow rate in the rotating detonation combustion chamber group 8 decreases and the static pressure increases. At this time, the static pressure at the measuring point is platform cd. In step d, the auxiliary gas intake is stopped and the fuel gas intake is instantly started. The sudden increase in intake pressure causes the static pressure at the measuring point to rise to platform de. The fuel gas continues to enter the combustion chamber channel. In step e, the fuel gas is detonated to generate a detonation wave. Subsequently, continuous detonation combustion begins in each annular combustion chamber channel of the rotating detonation combustion chamber group 8, and the rotating detonation Tesla turbine engine is started.

[0043] This structural method realizes rotating detonation combustion with an initial detonation pressure higher than atmospheric pressure and adjustable initial detonation pressure, and the detonation gas can further expand and accelerate in the nozzle to drive the Tesla turbine to do work.

[0044] The above embodiments are intended only to illustrate the technical concepts and features of the present invention. Their purpose is to enable those skilled in the art to understand the contents of the present invention and implement them accordingly. They are not intended to limit the scope of protection of the present invention. Any equivalent changes or modifications made based on the essence of the present invention are intended to be covered by the scope of protection of the present invention.

Claims

1. A structure for realizing high-pressure detonation in a detonation combustion chamber by utilizing a Tesla turbine, characterized in that: Including detonation combustion chamber, Tesla turbine and electric motor; The inlet of the Tesla turbine is connected to the outlet of the detonation combustion chamber; the outlet of the detonation combustion chamber is a gradually expanding structure; The motor provides the starting speed for the rotor of the Tesla turbine; The Tesla turbine is used to increase the static pressure in the detonation combustion chamber and reduce the gas flow rate at the ignition moment, while converting the kinetic energy of the detonation gas into mechanical energy for output; The Tesla turbine is composed of a plurality of coaxially rotating discs, each of which is open at the center and has gaps between the discs; the inlet at the outer diameter of the Tesla turbine disc is connected to the outlet of the detonation combustion chamber; The flow passages between the Tesla turbine discs are used to extinguish the detonation wave; The detonation combustion chamber is a pulse detonation combustion chamber, and a plurality of them are provided to form a pulse detonation combustion chamber group; A plurality of pulse detonation combustion chambers are arranged in an annular manner around the Tesla turbine, and each outlet of the pulse detonation combustion chambers is connected to an inlet corresponding to the outer diameter of the Tesla turbine; Each of the pulse detonation combustion chambers adopts a valve and isolation control strategy, and its working cycle is divided into three stages: isolation, filling, and detonation; the Tesla turbine adjusts the initial detonation pressure during the isolation and filling stages, and the gas or gas-liquid mixture entering the pulse detonation Tesla turbine engine flows through the detonation combustion chamber group and the Tesla turbine and is discharged to the atmosphere. At this time, the static pressure and flow rate of the fluid in the combustion chamber channel are determined by the intake pressure and the rotational speed of the Tesla turbine.

2. The structure for realizing high-pressure detonation in a detonation combustion chamber using a Tesla turbine as claimed in claim 1, characterized in that: High-speed fluid enters tangentially from the gap along the outer diameter of the disk, and low-speed fluid is discharged from the opening at the center of the disk. Under the action of viscous force, momentum exchange occurs between the fluid and the disk, and part of the kinetic energy of the fluid is converted into shaft work of the Tesla turbine and output to the outside world.

3. The structure for realizing high-pressure detonation in a detonation combustion chamber using a Tesla turbine as claimed in claim 1, characterized in that: The motor acts as a generator after the fuel starts to burn and the Tesla turbine reaches a specified speed, generating electrical energy and outputting it to the outside world.

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