Tail gas energy efficient utilization system of liquid rocket engine test bed

Abstract

The invention belongs to the technical field of liquid rocket engine tests, and relates to a liquid rocket engine test bed tail gas energy efficient utilization system which comprises a gas source, an adjustable throat area spray pipe assembly, a turbine power generation device and a controller. The air source is connected with one end of the throat area adjustable spray pipe assembly through a first pipeline, and the other end of the throat area adjustable spray pipe assembly is connected with the turbine power generation device through a second pipeline. The controller is connected with the first pipeline, the second pipeline and the throat area adjustable spray pipe assembly so as to control the throat area change of the throat area adjustable spray pipe assembly according to monitored pipeline parameters, and then the outlet speed of a nozzle is adjusted, so that a turbine can work at a high working efficiency point. The power generation efficiency of the power generation device can be improved.

Description

Technical Field

[0001] The present application relates to the field of liquid rocket engine test technology, and in particular to a liquid rocket engine test bench exhaust gas energy efficient utilization system. Background Art

[0002] Cryogenic non-toxic propellants are highly competitive in the international rocket commercial market, and their development mainly depends on their two characteristics: high performance and low cost. With the growing demand for aerospace and national defense, especially the long-term in-orbit deep space exploration flights, reusable round-trip flights between the earth and the sky, and other mission requirements, cryogenic propellant liquid rocket engines represented by liquid oxygen / liquid hydrogen and liquid oxygen / methane are gradually gaining attention.

[0003] The development of cryogenic liquid rocket engines requires a large number of ground tests. Hydrogen and methane are two flammable and explosive propellants, and the system pipelines need to be purged before and after the test to ensure safety. Unlike normal temperature propellants, cryogenic propellants have a very low boiling point. At standard atmospheric pressure, the boiling point of liquid hydrogen is only 20.38 K, and the boiling point of liquid oxygen is 90.15 K. They are in a gaseous state at room temperature and are easily vaporized during storage and transportation, and gas-liquid two-phase flow occurs, causing adverse or even destructive effects on the engine and pressurized delivery system. The complete ground hot test includes propellant pipeline cleaning, gas purge, and pipeline precooling, which require high-pressure gas as a power source. After completing the above process, most of the mechanical energy of the gas is not fully released, but is directly discharged into the atmosphere. How to optimize the process and recover this part of the energy is of great significance.

[0004] Relevant data show that from the perspective of energy quality, of the total heat energy generated by the combustion of fuel in the cylinder of an automobile engine, only 20% to 45% of the heat energy is converted into effective mechanical work, and the remaining heat energy is lost in the form of exhaust gas, cooling medium and heat dissipation on the surface of components, of which the energy carried away by exhaust gas accounts for 30% to 40% of the total energy. As for measures such as gas blowing and precooling during ground tests of rocket engines, the high-pressure gas only loses a small part of its mechanical energy due to pipeline flow resistance.

[0005] In the prior art, the main methods for realizing engine exhaust gas energy recovery include turbo compounding technology, Rankine cycle technology, and thermoelectric exchange technology.

[0006] Among them, the turbocompounding technology, especially the turbogenerating technology, is used to recycle the high-pressure gas mechanical energy through the combined cycle with the turbine. The high-pressure exhaust gas discharged from the pipeline drives the power turbine installed in the exhaust pipe to rotate at high speed, converting the energy contained in the exhaust gas into the mechanical energy of the power turbine. The high-speed rotating power turbine drives the generator to rotate to charge the battery, etc., which has good engineering application prospects. The implementation and system structure of the turbocompounding technology are relatively simple, the modification of the engine structure is small, and it can be flexibly controlled. It has always been widely concerned by the industry. The turbocompounding technology is of great significance for the recovery of engine exhaust energy and has considerable potential. At the same time, the combination of turbine and engine is not single. The combination of turbine and engine mainly includes electric-assisted compound turbine, series compound turbine, parallel compound turbine and pure electric compound turbine.

[0007] However, the structure of the turbine in the current turbine power generation system is fixed, which results in the turbine not working at the design point most of the time, and the turbine is at a low efficiency level, which in turn makes the power generation efficiency of the entire turbine power generation device low. How to achieve adaptive adjustment of the turbine device according to the upstream flow conditions of the turbine is an effective way to improve the power generation efficiency of the turbine power generation device. Summary of the invention

[0008] Based on this, it is necessary to provide a liquid rocket engine test bench exhaust energy efficient utilization system to address the above-mentioned technical problems, which can improve the power generation efficiency of the power generation device.

[0009] Liquid rocket engine test bench tail gas energy efficient utilization system, including: gas source, adjustable throat area nozzle assembly, turbine generator device and controller; The gas source is connected to one end of the adjustable throat area nozzle assembly through a first pipeline, and the other end of the adjustable throat area nozzle assembly is connected to the turbine generator through a second pipeline; The controller is connected to the first pipeline, the second pipeline and the adjustable throat area nozzle assembly respectively to control the change of the throat area of ​​the adjustable throat area nozzle assembly according to the monitored pipeline parameters.

[0010] In one embodiment, the adjustable throat area nozzle assembly comprises: a motor, a needle cone and a nozzle; The motor is detachably connected to one end of the needle cone; The central axis of the needle cone is collinear with the center of the throat of the nozzle, and there is a gap between the other end of the needle cone and the throat of the nozzle; The controller is connected to the motor, and takes the pipeline parameters as input, outputs a control signal, and controls the movement of the motor to control the needle cone to move in a direction toward or away from the nozzle throat, so as to achieve a change in the throat area of ​​the adjustable throat area nozzle assembly.

[0011] In one embodiment, the nozzle comprises a convergent section, a throat section and a divergent section which are connected in sequence.

[0012] In one embodiment, the convergent section adopts a double arc design.

[0013] In one embodiment, the expansion section adopts a special nozzle design. In one embodiment, a temperature sensor and a pressure sensor are provided on the first pipeline; The temperature sensor and the pressure sensor are both connected to the controller so that the controller controls the throat of the nozzle according to the temperature monitored by the temperature sensor and the pressure monitored by the pressure sensor.

[0014] In one embodiment, the turbine power generation device comprises: turbine blades, a transmission mechanism and a generator; One end of the turbine moving blade is connected to the nozzle, and the other end is connected to the generator through the transmission mechanism.

[0015] In one embodiment, the turbine buckets adopt a single-stage impulse turbine.

[0016] In one embodiment, the isentropic expansion work of the working fluid of the turbine blades in a single-stage turbine satisfies the equation:

[0017] In the formula, L ad is the isentropic expansion work, Ω is the turbine reaction force, R is the universal gas constant, k is the specific heat ratio of the turbine working fluid, is the total temperature at the turbine inlet, π It is the isentropic expansion work done by the turbine pressure ratio gas in the nozzle.

[0018] In one embodiment, the tangential velocity of the airflow at the average diameter of the turbine blades satisfies:

[0019] In the formula, is the tangential velocity of the airflow at the mean diameter, is the actual nozzle outlet velocity, is the nozzle outlet angle.

[0020] The above-mentioned liquid rocket engine test bench exhaust gas energy efficient utilization system adjusts the nozzle outlet velocity under different upstream conditions by adjusting the adjustable nozzle throat area, and then adjusting the nozzle expansion ratio, and then adjusting the nozzle outlet air flow velocity, so that the turbine blades always work at a higher efficiency level; through the perception of pressure and temperature sensors and the mutual cooperation of PID controllers, the movement of the adjustable nozzle needle cone is realized, and then the intelligent adjustment of the device is realized; through the efficient design of turbine blades and the mutual cooperation of turbine blades and adjustable nozzles, the efficient operation of the entire turbine engine device is realized. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 A schematic diagram of a liquid rocket engine test bench exhaust energy efficient utilization system in one embodiment; Figure 2 A cross-sectional view of a nozzle in a liquid rocket engine test bench exhaust energy efficient utilization system in one embodiment; Figure 3 A schematic diagram of a nozzle convergence section in a liquid rocket engine test bench exhaust energy efficient utilization system in one embodiment; Figure 4 A schematic diagram of a nozzle expansion section in a liquid rocket engine test bench exhaust energy efficient utilization system in one embodiment; Figure 5 The control schematic diagram of the liquid rocket engine test bench exhaust energy efficient utilization system in one embodiment. DETAILED DESCRIPTION

[0022] In order to make the purpose, technical solutions and advantages of the present application more clearly understood, the present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not intended to limit the present application. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work are within the scope of protection of the present application.

[0023] It should be noted that all directional indications in the embodiments of the present application (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0024] In addition, the descriptions of "first", "second", etc. in this application are only for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of the features. In the description of this application, "multiple groups" means at least two groups, such as two groups, three groups, etc., unless otherwise clearly and specifically defined.

[0025] In this application, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0026] In addition, the technical solutions between the various embodiments of the present application can be combined with each other, but it must be based on the fact that ordinary technicians in the field can implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by this application.

[0027] The present application provides a liquid rocket engine test bench tail gas energy efficient utilization system, such as Figure 1 As shown, in one embodiment, it includes: an air source, a first pipeline, an adjustable throat area nozzle assembly, a second pipeline, a turbine generator and a controller. The gas source is connected to one end of the adjustable throat area nozzle assembly through a first pipeline, and the other end of the adjustable throat area nozzle is connected to the turbine generator through a second pipeline.

[0028] The controller is connected to the first pipeline, the second pipeline and the adjustable throat area nozzle assembly respectively to control the change of the throat area of ​​the adjustable throat area nozzle assembly according to the monitored pipeline parameters.

[0029] A temperature sensor and a pressure sensor are provided on the first pipeline; the temperature sensor and the pressure sensor are both connected to the controller, so that the controller controls the throat of the adjustable throat area nozzle assembly according to the temperature monitored by the temperature sensor and the pressure monitored by the pressure sensor.

[0030] like Figure 2 As shown, in one embodiment, the adjustable throat area nozzle assembly includes: a motor 1, a needle cone 2 and a nozzle 3.

[0031] The motor is detachably connected to one end of the needle cone, such as a threaded connection 4, and the motor may be a stepping motor.

[0032] The central axis of the needle cone is collinear with the center of the throat of the nozzle, and there is a gap between the other end of the needle cone and the throat of the nozzle, and 5 is the diameter of the needle cone.

[0033] The nozzle is a Laval nozzle with a fixed profile.

[0034] The controller is connected to the motor, and takes the pipeline parameters as input, outputs a control signal, and controls the movement of the motor to control the needle cone to move in a direction toward or away from the nozzle throat, so as to achieve a change in the throat area of ​​the adjustable throat area nozzle assembly.

[0035] like Figure 3 as well as Figure 4 As shown in the figure, since the exhaust gas generated during the test is often at a high pressure, in order to simplify the structure and reduce the processing cost, a circular convergent-divergent nozzle, i.e., a Laval nozzle commonly used in liquid rocket engines, is used. The nozzle includes a convergent section, a throat, and a divergent section connected in sequence. The convergent section adopts a double arc design, and the length of the cylindrical section is L c1 , the length of the convergence section is L c2 , the nozzle throat radius is R t The radius of the arc at the connection between the nozzle inlet and the combustion chamber is R2, i.e. the throat arc, and the arc with a radius of R1 is directly tangent to the throat arc. The expansion section adopts a double arc special nozzle design, and the length of the nozzle expansion section is L c3 , the nozzle throat radius is R t , the nozzle outlet radius is R e The nozzle throat profile is a nozzle with a radius of R3, and the expansion section is an arc with a radius of R4. The two arcs are tangent at point β e is the nozzle exit expansion angle.

[0036] In one embodiment, the turbine device includes: turbine blades, a transmission mechanism and a generator; for a small-power turbine, the focus is on simple structure, good processability and reliable operation, so the turbine blades adopt a single-stage impulse turbine, one end of the turbine blades is connected to the nozzle, and the other end is connected to the generator through the transmission mechanism. The reaction degree of the turbine device is taken as 0, that is, the expansion of the gas in the turbine device only occurs in the nozzle assembly. Since the design speed of the turbine is generally high, in order to make the generator allowable speed range match the turbine speed, a transmission device is installed between the turbine and the generator.

[0037] like Figure 5As shown, the working process of the present application is: after the liquid rocket engine test is completed, the test blow-off exhaust gas flows out from the upstream as the gas source, and at the same time the high-pressure solenoid valve is opened, and the gas is discharged into the ambient atmosphere after flowing through the adjustable throat area nozzle assembly and the turbine blades, and then the blades are accelerated to rotate, and the rotation of the blades drives the transmission mechanism to rotate, and then drives the generator to rotate to generate electricity. When the upstream intake parameters change, the temperature and pressure sensors along the pipeline measure the intake parameters, and at the same time input the changed parameters into the PID controller. The PID controller outputs a control signal according to the input parameters to control the stepper motor to control the movement of the needle cone. By adjusting the nozzle throat area, the airflow expands in the nozzle, and the outlet pressure is equal to the ambient pressure, so that the gas is fully expanded, the nozzle outlet gas velocity is increased, and the power generation efficiency of the turbine generator is also improved.

[0038] The above-mentioned liquid rocket engine test bench exhaust gas energy efficient utilization system adjusts the nozzle outlet velocity under different upstream conditions by adjusting the adjustable nozzle throat area, and then adjusting the nozzle expansion ratio, and then adjusting the nozzle outlet air flow velocity, so that the turbine blades always work at a higher efficiency level; through the perception of pressure and temperature sensors and the mutual cooperation of PID controllers, the movement of the adjustable nozzle needle cone is realized, and then the intelligent adjustment of the device is realized; through the efficient design of turbine blades and the mutual cooperation of turbine blades and adjustable nozzles, the efficient operation of the entire turbine engine device is realized.

[0039] Compared with the traditional fixed structure turbine generator, this application has higher efficiency, simple structure, easy implementation and low cost. In addition to the exhaust energy recovery of the test device, it can also be used in the following scenarios: 1) Industrial boilers: The exhaust gas produced by industrial boilers is often of high pressure and temperature and contains a large amount of energy.

[0040] 2) Used in thermal power generation devices; thermal power generation will produce a large amount of high-temperature, high-pressure exhaust gas, and these exhaust gases are the energy source for the device to generate electricity.

[0041] 3) Used in transportation vehicles: Cars, ships and other transportation vehicles will continuously produce a large amount of high-temperature, high-pressure exhaust gas. Applying this device to vehicles can greatly reduce the loss of exhaust gas energy and improve the utilization efficiency of fossil energy.

[0042] In a specific embodiment, a system for efficiently utilizing the exhaust energy of a liquid rocket engine test bench is designed.

[0043] First, the design conditions of the turbine generator are clarified, and the design points of the turbine and the nozzle are determined. As shown in Tables 1 and 2, the design conditions of the device are assumed based on the energy utilization of the exhaust gas after the test. Since the device uses four adjustable nozzles, the flow rate of a single nozzle is 0.33 kg / s.

[0044] The design requirements of the nozzle subsonic convergent section are to ensure uniform acceleration of the airflow, uniform flow field at the throat section, and no flow separation. At the same time, the outer dimensions should be minimized to reduce the structural mass of the nozzle convergent section and reduce friction losses. Therefore, the nozzle convergent section adopts a double arc design.

[0045] The nozzle expansion section adopts the design of a special nozzle. The generatrix of the special nozzle is a curve. From the perspective of geometry and processing, the simplest curve is an arc. When the nozzle expansion is relatively small, the special nozzle with a double arc profile is widely used. The double arc nozzle is used here.

[0046] Therefore, according to the upstream flow parameters and the nozzle design criteria, the nozzle technical indicators, i.e., the design parameters, are obtained as shown in Table 3. The pointed cone type needle cone can produce a fast response, and the smaller the surface taper, the stronger the area adjustment ability and the faster the system response.

[0047] Since the expansion of the gas only occurs in the nozzle (i.e., nozzle) assembly, the flow process of the working fluid in the adjustable throat area nozzle assembly is regarded as an isentropic process. The isentropic expansion work of the working fluid in the adjustable throat area nozzle assembly is Satisfies the equation:

[0048] In the formula, k is the specific heat ratio of the turbine working fluid, R For universal gas Changshu, is the total temperature at the turbine inlet, π It is the isentropic expansion work done by the turbine pressure ratio gas in the nozzle.

[0049] According to the flow conditions in Table 1, the specific heat ratio can be determined k And the total temperature at the nozzle inlet (i.e. the total temperature at the turbine inlet) According to the turbine expansion ratio (i.e. turbine pressure ratio) in Table 1, the inlet and outlet pressure ratio of the adjustable throat area nozzle assembly can be determined. .

[0050] Then, the actual velocity at the outlet of the adjustable throat area nozzle assembly is:

[0051] in It can be 0.92-0.95; but, satisfy:

[0052] Introducing the concept of wheel efficiency, wheel efficiency That is, the cyclic work generated when a unit flow passes through a certain stage The ideal energy available at this level The parameter that has the greatest impact on the circumferential efficiency is the circumferential speed of the moving blades. The actual velocity at the nozzle outlet Ratio .

[0053] For impulse turbines, hour( is the nozzle outlet airflow angle), the wheel circumference efficiency takes the extreme value. Then, the tangential velocity of the airflow at the average diameter is satisfy:

[0054] in, It is the nozzle outlet angle, generally 20-25 degrees.

[0055] Based on the above calculation, the average diameter of the turbine rotor can be obtained as:

[0056] Height of rotor blade inlet:

[0057] in, and are the upper and lower covers of the leaves, is the nozzle height, i.e. the diameter of the circular nozzle. The value of the blade coverage can be found in the literature. For impulse turbines, , .

[0058] Working impeller airflow outlet angle:

[0059] In the formula, is the turbine working fluid flow rate, , is the relative motion stagnation temperature at the inlet of the working impeller cascade, is the total relative motion pressure at the working impeller inlet, is the reduced velocity at the working impeller outlet. The above parameters can be obtained based on the flow conditions in Table 1 and the nozzle structure parameters in Table 3. is the nozzle total pressure recovery coefficient, is the partial air intake of the nozzle.

[0060] Working impeller air flow inlet angle:

[0061] Width of moving blade Related to its ability to resist bending and loss of blade shape, usually for longer blades , for longer leaves .

[0062] Working blade chord length:

[0063] The number of rotor blades can be calculated using the Zweifel coefficient. Zweifel (1945) established a formula for calculating the optimal pitch / chord ratio, from which the blade pitch can be obtained as:

[0064] in, is the blade pitch, is the axial chord length of the blade, which is the value obtained above. , , are the axial velocity components at the inlet and outlet of the channel, respectively. After studying a large number of turbine blade cascade experimental results, Zweifel found that the optimal load factor is between 0.8 and 1.2. Therefore, the blade cascade pitch can be calculated, and then the number of blades can be obtained.

[0065] Through the above design calculations, the average diameter of the turbine rotor, the chord length of the working blades, the blade placement angle, the number of rotor blades, and the blade inlet and outlet angles can be obtained. , The parameters of turbine blades are shown in Table 3.

[0066] That is to say, according to the flow rate, pressure ratio, inlet pressure, and outlet pressure in Table 1, the contraction ratio, expansion ratio, cylinder section diameter, throat diameter, and nozzle outlet diameter of the nozzle assembly shown in Table 2 can be calculated, and then based on the selected double arc contraction section design and special nozzle expansion section design, the cylinder section length and other detailed structural dimension parameters can be obtained. Based on the impulse turbine assumption, the nozzle outlet velocity can be obtained according to the inlet temperature and turbine pressure ratio parameters in Table 1, and the average diameter of the turbine rotor in Table 2 can be obtained according to the nozzle outlet angle and outlet velocity. The rotor blade height can be calculated according to the nozzle diameter, the number of blades can be calculated according to the Zweifel coefficient, and the blade chord length can be calculated according to the calculated placement angle (i.e.: working impeller airflow outlet angle, working impeller airflow inlet angle). Finally, based on the nozzle outlet angle and parameters such as outlet velocity, rotation speed, and rotor diameter, combined with the turbine design criteria, the inlet and outlet angles of the blades are calculated.

[0067] In summary, based on the relationship between throat area and turbine design, the throat area of ​​the nozzle without a needle cone and the nozzle outlet velocity are determined based on the expansion ratio and flow rate of the design operating conditions. Some design parameters of the turbine can be determined based on the nozzle outlet velocity and nozzle outlet angle. When the operating conditions change, the outlet velocity can be adjusted by adjusting the throat area, so that the turbine rotor can operate at the design point (including: flow rate, speed, outlet pressure, outlet temperature, calculated nozzle outlet temperature and outlet pressure).

[0068] For the adjustable turbine generator, the nozzle inlet airflow parameters are first sensed through pressure and temperature sensors. The control system adopts the PI algorithm commonly used in the adjustable venturi of liquid rocket engines, and uses a PLC controller to realize the control of the needle cone.

[0069] Table 1 Design conditions of turbine generator

[0070] Table 2 Turbine device structural design parameters

[0071] Table 3 Nozzle structure design parameters

[0072] Table 4 Turbine blade parameters

[0073] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0074] The above-mentioned embodiments only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the present application. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the attached claims.

Claims

1. Liquid rocket engine test bench tail gas energy efficient utilization system, characterized by: include: Air source, adjustable throat area nozzle assembly, turbine generator and controller; The gas source is connected to one end of the adjustable throat area nozzle assembly through a first pipeline, and the other end of the adjustable throat area nozzle assembly is connected to the turbine generator through a second pipeline; The controller is connected to the first pipeline, the second pipeline and the adjustable throat area nozzle assembly respectively to control the change of the throat area of ​​the adjustable throat area nozzle assembly according to the monitored pipeline parameters.

2. The liquid rocket engine test bench tail gas energy efficient utilization system according to claim 1, characterized in that: The adjustable throat area nozzle assembly comprises: a motor, a needle cone and a nozzle; The motor is detachably connected to one end of the needle cone; The central axis of the needle cone is collinear with the center of the throat of the nozzle, and there is a gap between the other end of the needle cone and the throat of the nozzle; The controller is connected to the motor, and takes the pipeline parameters as input, outputs a control signal, and controls the movement of the motor to control the needle cone to move in a direction toward or away from the nozzle throat, so as to achieve a change in the throat area of ​​the adjustable throat area nozzle assembly.

3. The liquid rocket engine test bench tail gas energy efficient utilization system according to claim 1 or 2, characterized in that: The nozzle comprises a convergent section, a throat section and an expansion section which are connected in sequence.

4. The liquid rocket engine test bench tail gas energy efficient utilization system according to claim 3, characterized in that: The convergent section adopts a double arc design.

5. The liquid rocket engine test bench tail gas energy efficient utilization system according to claim 4, characterized in that: The expansion section adopts a special nozzle design.

6. The liquid rocket engine test bench tail gas energy efficient utilization system according to claim 1 or 2, characterized in that: The first pipeline is provided with a temperature sensor and a pressure sensor; The temperature sensor and the pressure sensor are both connected to the controller so that the controller controls the throat of the nozzle according to the temperature monitored by the temperature sensor and the pressure monitored by the pressure sensor.

7. The liquid rocket engine test bench tail gas energy efficient utilization system according to claim 1 or 2, characterized in that: The turbine power generation device comprises: turbine blades, a transmission mechanism and a generator; One end of the turbine moving blade is connected to the nozzle, and the other end is connected to the generator through the transmission mechanism.

8. The liquid rocket engine test bench tail gas energy efficient utilization system according to claim 7, characterized in that: The turbine moving blades adopt a single-stage impulse turbine.

9. The liquid rocket engine test bench tail gas energy efficient utilization system according to claim 8, characterized in that: The isentropic expansion work of the working fluid of the turbine moving blade in the single-stage turbine satisfies the equation: In the formula, L ad is the isentropic expansion work, Ω is the turbine reaction force, R is the universal gas constant, k is the specific heat ratio of the turbine working fluid, is the total temperature at the turbine inlet, π It is the isentropic expansion work done by the turbine pressure ratio gas in the nozzle.

10. The liquid rocket engine test bench tail gas energy efficient utilization system according to claim 9, characterized in that: The tangential velocity of the airflow at the average diameter of the turbine blades satisfies: In the formula, u is the tangential velocity of the airflow at the mean diameter, is the actual nozzle outlet velocity, α 1 is the nozzle outlet angle.

Images