A high-efficiency combustion system and method for a PD-9S rocket engine combustion chamber

Abstract

The present application relates to the technical field of rocket combustion chamber, in particular to a kind of rocket engine PD-9S combustion chamber high-efficiency combustion system and method, including control module, supply module and combustion chamber module, control module is connected with supply module and combustion chamber module respectively, supply module is connected with combustion chamber module, control module real-time monitoring the working condition parameter of combustion chamber, and according to the algorithm of pre-set adjustment supply module and the operation of combustion chamber module, the flow of fuel and the supply speed and flow of oxidant are controlled by supply module, and the mixed combustion of fuel and oxidant is controlled by combustion chamber module, and the mixing ratio of fuel and oxidant is accurately controlled according to the operating state of engine by control module, so that fuel is fully combusted, and the combustion efficiency is improved.

Description

Technical Field

[0001] This invention relates to the field of rocket combustion chamber technology, and in particular to a high-efficiency combustion system and method for the PD-9S rocket engine combustion chamber. Background Technology

[0002] The rocket combustor is one of the most important components of a rocket engine, responsible for mixing and burning fuel and oxidizer to generate enormous thrust. The structural design of the combustor directly affects the performance and reliability of the rocket engine, thus playing a crucial role in the development of rocket technology.

[0003] However, rocket engine combustion chambers need to operate at extremely high temperatures and pressures, which limits the efficiency of fuel combustion. Summary of the Invention

[0004] The purpose of this invention is to provide a high-efficiency combustion system and method for the PD-9S rocket engine combustor, which solves the problem that the efficiency of fuel combustion is limited because the rocket engine combustor needs to operate under extremely high temperatures and pressures.

[0005] To achieve the above objectives, the present invention provides a high-efficiency combustion system for the PD-9S rocket engine combustor, comprising a control module, a supply module, and a combustor module, wherein the control module is connected to both the supply module and the combustor module, and the supply module is connected to the combustor module. The control module is used to monitor the operating parameters of the combustion chamber in real time and adjust the operation of the supply module and the combustion chamber module according to a preset algorithm. The supply module is used to control the flow rate of fuel and the supply rate and flow rate of oxidant; The combustion chamber module is used to enhance the mixed combustion of fuel and oxidizer, thereby improving combustion efficiency.

[0006] The PD-9S rocket engine combustion chamber high-efficiency combustion system also includes an ignition module, which is connected to the control module. The ignition module is used to receive instructions from the control module and perform ignition control.

[0007] The supply module includes an oxidant supply unit and a fuel supply unit. The oxidant supply unit is connected to the control module and the combustion chamber module, respectively, and the fuel supply unit is connected to the control module and the combustion chamber module, respectively. The oxidant supply unit is used to receive instructions from the control module and control the supply speed and flow rate of the oxidant. The fuel supply unit is used to receive instructions from the control module and control the fuel flow rate.

[0008] The combustion chamber module includes an atomization unit and an exhaust gas discharge unit. The atomization unit is connected to the oxidant supply unit and the fuel supply unit, respectively, and the exhaust gas discharge unit is connected to the control module. The atomizing unit is used to atomize the fuel and oxidant; The exhaust gas discharge unit is used to receive instructions from the control module and control the exhaust gas to be discharged from the combustion chamber.

[0009] The control module includes a calculation unit and an instruction unit. The calculation unit is connected to the instruction unit, and the instruction unit is connected to the ignition module, the oxidant supply unit, the fuel supply unit, and the exhaust gas discharge unit, respectively. The calculation unit is used to calculate the mixing ratio of fuel and oxidant; The instruction unit is used to generate corresponding control instructions according to the mixing ratio, and upload the instructions to the ignition module, the oxidant supply unit, the fuel supply unit and the exhaust gas discharge unit.

[0010] The control module further includes a data acquisition unit, which is connected to the computing unit. The acquisition unit is used to acquire the temperature, pressure and gas composition of the combustion chamber, and upload the acquired data to the calculation unit.

[0011] A high-efficiency combustion method for the PD-9S rocket engine combustion chamber includes the following steps: Real-time monitoring of combustion chamber operating parameters; Based on operating parameters, adjust the fuel flow rate and the oxidant supply rate and flow rate; The fuel and oxidizer are atomized before combustion; During combustion, the discharge of exhaust gas from the combustion chamber is controlled to maintain stable pressure in the combustion chamber.

[0012] This invention discloses a high-efficiency combustion system and method for a PD-9S rocket engine combustor. The control module monitors the operating parameters of the combustor in real time and adjusts the operation of the supply module and the combustor module according to a preset algorithm. The supply module controls the fuel flow rate and the supply rate and flow rate of the oxidizer, and controls the combustor module to enhance the mixed combustion of fuel and oxidizer. The control module precisely controls the mixing ratio of fuel and oxidizer according to the engine's operating status, so that the fuel is fully combusted and the combustion efficiency is improved. Attached Figure Description

[0013] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the accompanying drawings used in the description of the embodiments or the prior art will be briefly introduced below.

[0014] Figure 1 This is a structural block diagram of the high-efficiency combustion system of the PD-9S rocket engine combustion chamber according to the first embodiment of the present invention.

[0015] Figure 2 This is a structural block diagram of the control module according to the first embodiment of the present invention.

[0016] Figure 3 This is a flowchart illustrating the steps of the high-efficiency combustion method in the combustion chamber of the rocket engine PD-9S according to the second embodiment of the present invention.

[0017] In the diagram: 101-Control module, 102-Supply module, 103-Combustion chamber module, 104-Ignition module, 105-Oxidant supply unit, 106-Fuel supply unit, 107-Atomization unit, 108-Exhaust gas discharge unit, 109-Calculation unit, 110-Command unit, 111-Data acquisition unit, 112-Adaptive unit. Detailed Implementation

[0019] The embodiments of the present invention are described in detail below. Examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, but should not be construed as limiting the present invention.

[0020] The first embodiment of this application is as follows: Please see Figure 1 and Figure 2 ,in, Figure 1 This is a structural block diagram of the high-efficiency combustion system of the PD-9S rocket engine combustion chamber according to the first embodiment of the present invention. Figure 2 This is a structural block diagram of the control module 101 according to the first embodiment of the present invention. The present invention provides a high-efficiency combustion system for the PD-9S rocket engine combustion chamber: including a control module 101, a supply module 102, a combustion chamber module 103, and an ignition module 104. The supply module 102 includes an oxidizer supply unit 105 and a fuel supply unit 106. The combustion chamber module 103 includes an atomization unit 107 and an exhaust gas discharge unit 108. The control module 101 includes a calculation unit 109, a command unit 110, a data acquisition unit 111, and an adaptive unit 112.

[0021] In this specific embodiment, the control module 101 is connected to the supply module 102 and the combustion chamber module 103 respectively, and the supply module 102 is connected to the combustion chamber module 103. The control module 101 is used to monitor the operating parameters of the combustion chamber in real time and adjust the operation of the supply module 102 and the combustion chamber module 103 according to a preset algorithm. The supply module 102 is used to control the flow rate of fuel and the supply rate and flow rate of oxidant; The combustion chamber module 103 is used to enhance the mixed combustion of fuel and oxidant, thereby improving combustion efficiency.

[0022] The control module 101 monitors the operating parameters of the combustion chamber in real time, including temperature, pressure, and fuel composition, and then adjusts the supply of fuel and oxidant, supply rate, and temperature and pressure of the combustion chamber to ensure stable and efficient combustion. The supply module 102 controls the fuel flow rate and the supply rate and flow rate of oxidant according to the instructions issued by the control module 101. The combustion chamber module 103 further enhances the mixed combustion of fuel and oxidant to improve combustion efficiency.

[0023] The ignition module 104 is connected to the control module 101. The ignition module 104 is used to receive instructions from the control module 101 and perform ignition control. Ignition control is a critical step in starting the rocket combustion chamber. The ignition module 104 controls the voltage or current of the ignition electrode to generate an electric spark in the ignition plug, igniting the fuel and oxidizer mixture in the combustion chamber, thereby starting the engine. Ignition control needs to ensure the reliability and safety of ignition and avoid accidents during the ignition process.

[0024] Secondly, the oxidant supply unit 105 is connected to the control module 101 and the combustion chamber module 103 respectively, and the fuel supply unit 106 is connected to the control module 101 and the combustion chamber module 103 respectively. The oxidant supply unit 105 is used to receive instructions from the control module 101 and control the supply speed and flow rate of the oxidant. The fuel supply unit 106 is used to receive instructions from the control module 101 and control the fuel flow rate.

[0025] The fuel supply unit 106 selects a suitable fuel type, designs an efficient fuel pump and a reasonable fuel pipeline, etc., to improve the fuel supply speed and accurately control the fuel flow rate. The oxidant supply unit 105 optimizes the oxidant supply speed and flow rate to ensure that the fuel and oxidant are stably supplied to the engine in the designed ratio.

[0026] Meanwhile, the atomizing unit 107 is connected to the oxidant supply unit 105 and the fuel supply unit 106 respectively, and the exhaust gas discharge unit 108 is connected to the control module 101; The atomizing unit 107 is used to atomize the fuel and oxidant; The exhaust gas discharge unit 108 is used to receive instructions from the control module 101 and control the exhaust gas to be discharged from the combustion chamber.

[0027] After the fuel and oxidant enter the combustion chamber, the atomization unit 107 atomizes them, that is, converts the liquid fuel into tiny droplets so that they can come into full contact with the oxidant and accelerate the combustion reaction. The exhaust gas discharge unit 108 controls the exhaust gas generated by combustion to be discharged from the combustion chamber in order to maintain the pressure stability of the combustion chamber. This process is usually achieved through the exhaust system.

[0028] In addition, the computing unit 109 is connected to the instruction unit 110, and the instruction unit 110 is connected to the ignition module 104, the oxidant supply unit 105, the fuel supply unit 106 and the exhaust gas discharge unit 108 respectively. The calculation unit 109 is used to calculate the mixing ratio of fuel and oxidant; The instruction unit 110 is used to generate corresponding control instructions according to the mixing ratio and upload the instructions to the ignition module 104, the oxidant supply unit 105, the fuel supply unit 106, and the exhaust gas discharge unit 108.

[0029] The calculation unit 109 can predict parameters such as combustion efficiency, temperature distribution, and pressure fluctuation under different mixture ratios by establishing a mathematical model of the combustion chamber and simulating it using CFD software, thereby guiding the determination of the mixture ratio. The instruction unit 110 generates corresponding control instructions based on the calculated mixture ratio, and then controls the fuel and oxidant by controlling the oxidant supply unit 105, the fuel supply unit 106, and the exhaust gas discharge unit 108.

[0030] Meanwhile, the acquisition unit 111 is connected to the computing unit 109; The acquisition unit 111 is used to acquire the temperature, pressure and gas composition of the combustion chamber and upload the acquired data to the calculation unit 109.

[0031] The acquisition unit 111 senses the temperature, pressure and gas composition of the combustion chamber in real time through sensors and uploads the data to the calculation unit 109. The calculation unit 109 generates the optimal mixing ratio based on the changes in temperature, pressure and gas composition.

[0032] Finally, the adaptive unit 112 is connected to the computing unit 109; The adaptive unit 112 is used to predict the performance and stability of the engine based on historical data and real-time monitoring data, and to autonomously learn and adjust the calculations of the calculation unit 109.

[0033] The adaptive unit 112 enables the computing unit 109 to learn and adjust autonomously based on the actual operating status and conditions of the engine, and to predict the engine's performance and stability based on historical data and real-time monitoring data, thereby further improving the rocket's controllability and safety.

[0034] Using the PD-9S high-efficiency combustion system of a rocket engine combustion chamber according to this embodiment, the fuel and oxidizer must be fully mixed in the combustion chamber to ensure stable and efficient combustion. The atomization unit 107 atomizes the fuel and oxidizer after they enter the combustion chamber, converting the liquid fuel into tiny droplets to facilitate full contact with the oxidizer and accelerate the combustion reaction. The fuel and oxidizer undergo a chemical reaction under high temperature and pressure conditions, releasing a large amount of energy. The exhaust gas discharge unit 108 controls the discharge of exhaust gases generated during combustion from the combustion chamber to maintain stable pressure. This process is typically achieved through an exhaust system. The control module 101 precisely controls the supply quantity and rate of fuel and oxidizer, as well as the temperature and pressure of the combustion chamber, to ensure stable and efficient combustion.

[0035] The second embodiment of this application is as follows: Based on the first embodiment, please refer to Figure 3 ,in, Figure 3 This is a flowchart illustrating the steps of a high-efficiency combustion method for a PD-9S rocket engine combustor according to a second embodiment of the present invention. This embodiment of a high-efficiency combustion method for a PD-9S rocket engine combustor includes the following steps: S201: Real-time monitoring of combustion chamber operating parameters; S202: Adjust the fuel flow rate and the supply rate and flow rate of the oxidant based on operating parameters; S203: Combustion of fuel and oxidizer after atomization; S204: During combustion, it controls the discharge of exhaust gas from the combustion chamber and maintains stable pressure in the combustion chamber.

[0036] Specifically, the acquisition unit 111 monitors the operating parameters of the combustion chamber in real time. Based on the changes in the operating parameters, the calculation unit 109 adjusts the fuel flow rate and the supply rate and flow rate of the oxidant. Then, the command unit 110 issues commands to the oxidant supply unit 105 and the fuel supply unit 106 to adjust the fuel flow rate and the supply rate and flow rate of the oxidant. After entering the combustion chamber, the fuel and oxidant are atomized by the atomization unit 107 to ensure sufficient contact with the oxidant and accelerate the combustion reaction. At the same time, the exhaust gas discharge unit 108 controls the exhaust gas generated by combustion to be discharged from the combustion chamber to maintain the pressure stability of the combustion chamber. The control module 101 precisely controls the supply amount and supply rate of fuel and oxidant, as well as the temperature and pressure of the combustion chamber, to ensure the stability and efficiency of the combustion process.

[0037] The above-disclosed embodiments are merely one or more preferred embodiments of this application and should not be construed as limiting the scope of this application. Those skilled in the art can understand that all or part of the processes for implementing the above embodiments and equivalent changes made in accordance with the claims of this application still fall within the scope of this application.

Claims

1. A high-efficiency combustion system for the PD-9S combustion chamber of a rocket engine, characterized in that, It includes a control module, a supply module, and a combustion chamber module. The control module is connected to both the supply module and the combustion chamber module, and the supply module is connected to the combustion chamber module. The control module is used to monitor the operating parameters of the combustion chamber in real time and adjust the operation of the supply module and the combustion chamber module according to a preset algorithm. The supply module is used to control the flow rate of fuel and the supply rate and flow rate of oxidant; The combustion chamber module is used to enhance the mixed combustion of fuel and oxidizer, thereby improving combustion efficiency.

2. The high-efficiency combustion system of the PD-9S rocket engine combustion chamber as described in claim 1, characterized in that, The high-efficiency combustion system of the PD-9S rocket engine combustion chamber also includes an ignition module, which is connected to the control module. The ignition module is used to receive instructions from the control module and perform ignition control.

3. The high-efficiency combustion system of the PD-9S rocket engine combustion chamber as described in claim 2, characterized in that, The supply module includes an oxidant supply unit and a fuel supply unit. The oxidant supply unit is connected to the control module and the combustion chamber module, respectively, and the fuel supply unit is connected to the control module and the combustion chamber module, respectively. The oxidant supply unit is used to receive instructions from the control module and control the supply speed and flow rate of the oxidant. The fuel supply unit is used to receive instructions from the control module and control the fuel flow rate.

4. The high-efficiency combustion system of the PD-9S rocket engine combustion chamber as described in claim 3, characterized in that, The combustion chamber module includes an atomization unit and an exhaust gas discharge unit. The atomization unit is connected to the oxidant supply unit and the fuel supply unit, respectively, and the exhaust gas discharge unit is connected to the control module. The atomizing unit is used to atomize the fuel and oxidant; The exhaust gas discharge unit is used to receive instructions from the control module and control the exhaust gas to be discharged from the combustion chamber.

5. The high-efficiency combustion system of the PD-9S rocket engine combustion chamber as described in claim 4, characterized in that, The control module includes a calculation unit and an instruction unit. The calculation unit is connected to the instruction unit, and the instruction unit is connected to the ignition module, the oxidant supply unit, the fuel supply unit, and the exhaust gas discharge unit, respectively. The calculation unit is used to calculate the mixing ratio of fuel and oxidant; The instruction unit is used to generate corresponding control instructions according to the mixing ratio, and upload the instructions to the ignition module, the oxidant supply unit, the fuel supply unit and the exhaust gas discharge unit.

6. The high-efficiency combustion system of the PD-9S rocket engine combustion chamber as described in claim 5, characterized in that, The control module further includes a data acquisition unit, which is connected to the computing unit. The acquisition unit is used to acquire the temperature, pressure and gas composition of the combustion chamber, and upload the acquired data to the calculation unit.

7. A high-efficiency combustion method for the PD-9S combustor of a rocket engine, applicable to the high-efficiency combustion system of the PD-9S combustor of a rocket engine as described in claim 1, characterized in that, Includes the following steps: Real-time monitoring of combustion chamber operating parameters; Based on operating parameters, adjust the fuel flow rate and the oxidant supply rate and flow rate; The fuel and oxidizer are atomized before combustion; During combustion, the discharge of exhaust gas from the combustion chamber is controlled to maintain stable pressure in the combustion chamber.

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