CN115898697A - Open expansion cycle engine and parameter estimation method and device thereof - Google Patents
Open expansion cycle engine and parameter estimation method and device thereof Download PDFInfo
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- 238000000034 method Methods 0.000 title claims abstract description 40
- 239000000446 fuel Substances 0.000 claims abstract description 179
- 239000007800 oxidant agent Substances 0.000 claims abstract description 156
- 230000001590 oxidative effect Effects 0.000 claims abstract description 149
- 238000001816 cooling Methods 0.000 claims abstract description 43
- 238000002485 combustion reaction Methods 0.000 claims abstract description 27
- 238000004364 calculation method Methods 0.000 claims description 11
- 238000002347 injection Methods 0.000 claims description 7
- 239000007924 injection Substances 0.000 claims description 7
- 239000000126 substance Substances 0.000 claims description 7
- 239000007921 spray Substances 0.000 claims description 3
- 238000013461 design Methods 0.000 abstract description 13
- 239000007788 liquid Substances 0.000 abstract description 7
- 238000005457 optimization Methods 0.000 abstract description 4
- 230000008878 coupling Effects 0.000 abstract description 3
- 238000010168 coupling process Methods 0.000 abstract description 3
- 238000005859 coupling reaction Methods 0.000 abstract description 3
- 230000000007 visual effect Effects 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 13
- 238000004590 computer program Methods 0.000 description 9
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Natural products C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 6
- 239000003380 propellant Substances 0.000 description 5
- 238000010521 absorption reaction Methods 0.000 description 3
- 239000002826 coolant Substances 0.000 description 3
- 239000002737 fuel gas Substances 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000007123 defense Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005485 electric heating Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000002195 synergetic effect Effects 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
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Abstract
The invention relates to an open expansion cycle engine and a parameter estimation method and device thereof, belonging to the technical field of liquid rocket engine overall scheme design. The engine disclosed by the invention divides fuel, wherein one path of fuel is heated by the cooling channel while cooling the combustion chamber, and then works on the fuel pump and the oxidant pump through the fuel turbine and the oxidant turbine in sequence to improve the pressure of the fuel and the oxidant, and the other path of fuel directly enters the thrust chamber to provide thrust through combustion work; the coupling between the chamber pressure and the turbine pressure ratio is greatly reduced, and the engine thrust is improved. On the basis of the engine structure, the method further takes turbine pump power matching as a condition, carries out key node parameter estimation based on given engine design parameters, facilitates visual understanding of different node state parameter distribution rules of the engine by people, and facilitates overall scheme design and parameter optimization of the engine, thereby developing structural parameter design of expansion cycle engine components (such as a turbine, a pump, a thrust chamber and the like).
Description
Technical Field
The disclosure relates to the technical field of expansion cycle engines in liquid rocket engines, in particular to an open expansion cycle engine and a parameter estimation method and device thereof.
Background
The circulation mode is one of the most important technical characteristics of the liquid rocket engine, and directly determines the performance, the application range and the corresponding technical scheme of the liquid rocket engine. The expansion cycle is one of three typical cycles of the liquid rocket engine, and has certain advantages compared with the other two cycle modes (gas generator cycle and afterburning cycle). Compared with the circulation of a fuel gas generator, the closed circulation is adopted, on one hand, complex thermodynamic components such as the fuel gas generator and the like are not needed, on the other hand, the waste of fuel gas which does not fully work is avoided, and the specific impulse performance is higher. Compared with afterburning circulation, complex thermodynamic components such as a precombustion chamber and the like are not needed, and the structure is simple.
Although the expansion cycle method has certain advantages, the defects are also obvious. The literature (research on a parallel type electric heating synergistic pressure-increasing variable thrust rocket engine scheme. Manned space, 2020, 26 (6): 702-9) indicates that in the mode, a propellant absorbs heat from a cooling channel, then drives a turbine to do work, and finally enters a combustion chamber for combustion, the propellant has limited work capacity after heat absorption compared with high-temperature and high-pressure gas generated after combustion, the turbine ratio is not too large, so that the expansion cycle engine chamber pressure is low, the thrust is low, and the parallel type electric heating synergistic pressure-increasing variable thrust rocket engine scheme is mainly applied to the upper stage and cannot be used in the core stage or the boosting of a carrier rocket. Therefore, the full open expansion cycle engine with the patent number of 202211255422.4 is provided with the technical scheme that the fuel absorbing heat through a cooling channel is divided into two paths, one path drives a turbine to do work and then is discharged into the environment, and the other path enters a thrust chamber to be combusted to generate thrust; so as to improve the pressure of the combustion chamber, increase the specific impulse and improve the thrust. However, the engine still has the problem of limited work capacity of the propellant after heat absorption.
Disclosure of Invention
The purpose of this disclosure is to provide an open expansion cycle engine for the problem that the structural chamber pressure of the existing full open expansion cycle engine is not high enough, thrust is not big enough; on the basis, in order to enable people to intuitively know the engine and know the change rule of the state parameter, a state parameter estimation method and a state parameter estimation device based on the engine are provided.
The purpose of the present disclosure is achieved by the following technical solutions.
In a first aspect, the present disclosure provides an open expansion cycle engine comprising a fuel turbine, a fuel pump, a fuel valve, a cooling channel, an injector, a combustion chamber, a nozzle, an oxidant turbine, an oxidant pump, an oxidant valve; the fuel is pressurized by a fuel pump and then is divided into two paths through a fuel valve, one path of the fuel enters a cooling channel to absorb heat from a combustion chamber and then sequentially drives a fuel turbine and an oxidant turbine to do work, and the other path of the fuel and the oxidant pressurized by an oxidant pump are injected into the combustion chamber through an injector through an oxidant of an oxidant valve and then are ejected out through a spray pipe to push a rocket to fly; the fuel turbine and the oxidant turbine respectively drive the fuel pump and the oxidant pump to work.
In a second aspect, the present disclosure provides a parameter estimation method, based on the engine provided in the first aspect, including:
thrust chamber pressure based on enginep c Thrust chamber mixing ratioMRAnd nozzle outlet pressurep e Calculating thrust chamber specific impulseI spc ；
Based on engine thrustF、MRFlow ratio of thrust chamber of engine
AndI spc the flow of the oxidant in the thrust chamber is calculated by>
And the fuel flow is greater or less>
And turbo functional flow>
：/>
Initializing a fuel turbo-pressure ratio and an oxidant turbo-pressure ratio;
obtaining cooling channel exit temperatureT rc ；
Calculating the power of a fuel pump, calculating the power of a fuel turbine based on the outlet temperature of the cooling channel, comparing the power of the fuel pump with the power of the fuel turbine, if the power of the fuel pump is not matched with the power of the fuel turbine, adjusting the pressure ratio of the fuel turbine, and repeating the steps until the power of the fuel pump is matched with the power of the fuel turbine;
and calculating and comparing the power of the oxidant pump and the power of the oxidant turbine, and if the power of the oxidant pump is not matched with the power of the oxidant turbine, adjusting the pressure ratio of the oxidant turbine until the power of the oxidant pump is matched with the power of the oxidant turbine.
In a third aspect, the present disclosure provides a parameter estimation apparatus, based on the engine provided in the first aspect, including:
input module for obtaining engine thrustFNozzle outlet pressurep e And the working condition parameters are as follows: room pressurep c Mixing ratio ofMRFlow ratio of
Cooling channel outlet temperatureT rc ；
Thrust chamber specific impulse calculation module for calculating the thrust based onp c 、MRAndp e calculating thrust chamber specific impulseI spc ；
A flow calculation module for calculating a flow based onF、MR、
AndI spc the flow of the oxidant in the thrust chamber is calculated by>
And the fuel flow is greater or less>
And turbo functional flow->
：
The turbine pressure ratio initialization module: for initializing a fuel turbo-pressure ratio and an oxidant turbo-pressure ratio;
the fuel turbine pump matching module is used for calculating the power of the fuel pump, giving the outlet temperature of the cooling channel, calculating the power of the fuel turbine, comparing the power of the fuel pump with the power of the fuel turbine, if the power of the fuel pump is not matched with the power of the fuel turbine, adjusting the pressure ratio of the fuel turbine, and repeating the module until the power of the fuel pump is matched with the power of the fuel turbine;
and the oxidant turbine pump matching module is used for calculating and comparing the power of the oxidant pump and the power of the oxidant turbine, and if the power of the oxidant pump is not matched with the power of the oxidant turbine, adjusting the pressure ratio of the oxidant turbine until the power of the oxidant pump is matched with the power of the oxidant turbine.
In a fourth aspect, the present disclosure provides an electronic device comprising:
at least one processor; and the number of the first and second groups,
a memory communicatively coupled to the at least one processor; wherein the memory stores instructions executable by the at least one processor to enable the at least one processor to perform the method of any of the embodiments of the second aspect.
In a fifth aspect, the present disclosure provides a computer readable storage medium having stored thereon a computer program which, when executed by a processor, causes the processor to perform the method according to any of the embodiments of the second aspect.
In a sixth aspect, the present disclosure provides a computer program product comprising a computer program/instructions which, when executed by a processor, cause the processor to perform the method of any of the embodiments of the second aspect.
Advantageous effects
Compared with the prior art, the fuel is divided, one path of the fuel is heated by self heat absorption while cooling the combustion chamber through the cooling channel, the fuel pump and the oxidant pump are driven to rotate by the fuel turbine and the oxidant turbine in sequence, the pressure of the fuel and the oxidant is increased, and the other path of the fuel directly enters the thrust chamber to provide thrust through combustion expansion work; when the coupling between the chamber pressure and the turbine pressure ratio is reduced, the working medium acting capacity of the turbine driving the fuel pump and the oxidant pump to rotate is improved, so that the pressure of fuel and oxidant entering the thrust chamber is improved, the chamber pressure is further improved, the specific impulse is increased, and the engine thrust is improved. On the basis of the engine, in order to facilitate visual understanding of the change rule of different node state parameters of the engine, a parameter estimation method is provided, based on given engine design and working condition parameters, node state parameter estimation is carried out by taking turbine pump power matching as a condition and taking a turbine pressure ratio as an adjustment variable (different from the determination of overall structure parameters during thrust adjustment of the existing expansion cycle engine, and the estimation of the node state parameters is carried out by taking the flow of a driving turbine as the adjustment variable, such as Trypop, liqing, cheng, et al. Liquid oxygen methane expansion cycle variable thrust engine system scheme contrast research [ J ]. University of defense science and technology, 2020, 42 (3): 106-15), overall scheme design and parameter optimization are conveniently carried out on the engine, so that the design of the structure parameters of subsequent expansion cycle engine components (such as a turbine, a pump, a thrust chamber and the like) is facilitated.
Drawings
FIG. 1 is a schematic illustration of an open expansion cycle engine according to an embodiment of the present disclosure;
FIG. 2 is a schematic flow chart of a parameter estimation method based on the engine shown in FIG. 1 according to an embodiment of the present disclosure;
FIG. 3 is a schematic illustration of a distribution of state parameters for an open expansion cycle engine provided in accordance with an embodiment of the present disclosure;
fig. 4 is a schematic structural diagram of an electronic device according to an embodiment of the present disclosure.
Detailed Description
The present disclosure will be described in detail below with reference to specific embodiments shown in the drawings. These embodiments are not limited to the disclosure, and structural, methodological, or functional changes made by those skilled in the art according to these embodiments are all included in the scope of the disclosure.
In the description of the present disclosure, it is to be understood that the terms "central," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings, which are based on the orientations and positional relationships indicated in the drawings, and are used merely to facilitate the description of the disclosure and to simplify the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the disclosure. Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or to implicitly indicate a number of the indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present disclosure, the meaning of "a plurality" is two or more unless otherwise specified.
For the purpose of illustrating the objects, technical solutions and advantages of the embodiments of the present disclosure, the technical solutions in the embodiments of the present disclosure will be clearly and completely described below with reference to the drawings in the embodiments of the present disclosure.
Fig. 1 is an open expansion cycle engine provided by the present disclosure, which as shown comprises a fuel turbine 2, a fuel pump 1, a fuel valve 3, a cooling channel 5, an injector 7, a combustion chamber 6, a nozzle 4, an oxidant turbine 10, an oxidant pump 9, an oxidant valve 8. Wherein the cooling channel 5, the injector 7, the combustion chamber 6 and the nozzle 4 form a thrust chamber. The fuel pump 1 is respectively connected with the fuel turbine 2 and the fuel valve 3, the oxidant pump 9 is respectively connected with the oxidant turbine 10 and the oxidant valve 8, the cooling channel 5 is arranged at the periphery of the thrust chamber to cool the thrust chamber, the outlet of the cooling channel 5 is connected with the fuel turbine 2, the fuel turbine 2 is connected with the oxidant turbine 10, the fuel is divided into two paths at the outlet of the fuel valve 3, one path enters the cooling channel 5, the other path and the oxidant at the outlet of the oxidant valve 8 enter the injector 7 together, the injector 7 injects the fuel and the oxidant into the combustion chamber 6, and high-temperature and high-pressure gas generated by combustion is discharged from the nozzle 4.
As can be seen from the above, the fuel is pressurized by the fuel pump 1 and divided into two paths by the fuel valve 3, one path enters the cooling channel 5 to absorb heat from the combustion chamber 6 and then sequentially drives the fuel turbine 2 and the oxidant turbine 10 to do work, and the other path and the oxidant pressurized by the oxidant pump 9 and passing through the oxidant valve 8 are injected into the combustion chamber 6 by the injector 7 and then are injected by the nozzle 4 to push the rocket to fly; the fuel turbine 2 and the oxidizer turbine 10 drive the fuel pump 1 and the oxidizer pump 9 to operate, respectively.
The engine chamber pressure is not high enough to current full open type expansion cycle engine chamber, thrust big problem inadequately, this disclosure proposes the improvement scheme to current full open type expansion cycle, through the promotion acting ability that can be better after the coolant temperature of analysis drive turbine acting promotes, only introduce the fuel of driving turbine acting one way into cooling channel and absorb heat, another way directly gets into the combustion chamber burning, thereby when keeping reducing the coupling between room pressure and the turbine pressure ratio, the working medium acting ability of the turbine of drive fuel pump and oxidant pump promotes, and then promote the pressure of fuel and oxidant, reach the effect that promotes the combustion chamber pressure, increase specific impulse, promote engine thrust. In the circulation mode, most of propellant (such as liquid hydrogen) directly enters the thrust chamber after passing through the main valve, and a small part of propellant absorbs heat to become high-temperature and high-pressure gas after passing through the cooling channel, so that the working capacity is enhanced, and the high-temperature and high-pressure gas is directly discharged into the atmosphere after driving the turbine.
In order to have an intuitive overall understanding of the open expansion cycle engine, state parameter calculations are first performed by power balancing to obtain the state parameters (flow, pressure, temperature, power) of the key nodes of the engine. The scheme contrast research [ J ] of a liquid oxygen methane expansion cycle variable thrust engine system, the university of national defense science and technology, 2020, 42 (3): 106-15.) shows a state parameter calculation method of an expansion cycle engine, because the flow rate of a coolant in an expansion cycle is the flow rate of fuel in a thrust chamber, and therefore working condition parameters in the method only need to consider the chamber pressure and the mixing ratio and do not need to consider the flow rate ratio, and the power balance is realized by adjusting the turbine flow rate ratio (the ratio of the flow rate of methane driving a turbine to the total flow rate of methane). Because of their different structures, the above state parameter calculation methods cannot be applied to the expansion cycle engine proposed by the present disclosure, and a parameter estimation method suitable for an open expansion cycle engine is needed to develop a general scheme design and parameter optimization based on room pressure, mixture ratio, flow ratio (coolant flow rate/thrust chamber flow rate) for the open expansion engine, so as to further develop a structural parameter design of expansion cycle engine components (including turbine, pump, thrust chamber, etc.).
FIG. 2 illustrates a parameter estimation method based on the open expansion cycle engine of FIG. 1, including the following:
1. thrust chamber pressure based on enginep c Thrust chamber mixing ratioMRAnd nozzle outlet pressurep e Calculating thrust chamber specific impulseI spc 。
I spc Can be obtained by a thermodynamic calculation method and can be referred to as a reference (liquid rocket engine design published in Beijing aerospace university Press in 2011 of Caizian national Biao, li Jia Wen, tian Aimei, zhang lihui and the like); software may also be available, such as rocket engine performance analysis software. This example was obtained using Rocket engine performance Analysis software, socket performance Analysis (RPA, www.
2. Based on engine thrustF、MRFlow ratio of thrust chamber of engine
AndI spc the flow of the oxidant in the thrust chamber is calculated by>
And the fuel flow is greater or less>
And turbo functional flow->
：/>
3. A fuel turbo-pressure ratio and an oxidant turbo-pressure ratio are initialized.
It can be initialized according to a preset value, or can be an externally given value, i.e. an input value. This value is continually adjusted in subsequent steps to accommodate the relevant design parameters given in 1.
4. Calculating fuel pump power based on cooling gallery outlet temperatureT rc And calculating the power of the fuel turbine, comparing the power of the fuel pump with the power of the fuel turbine, if the power of the fuel pump is not matched with the power of the fuel turbine, adjusting the pressure ratio of the fuel turbine, and repeating the steps until the power of the fuel pump is matched with the power of the fuel turbine.
In particular, fuel pump powerP pf Can be calculated by the following formula:
wherein, the first and the second end of the pipe are connected with each other,
for fuel injection pressure drop, by formula>
Obtaining; />
For the fuel valve pressure drop, by means of the formula>
Obtaining; />
And &>
Is a constant coefficient; />
Is the fuel pump inlet pressure, at a preset constant; />
Is the fuel density; />
Is the fuel pump efficiency, is a predetermined constant.
In particular, fuel turbine powerP tf Can be calculated by the following formula:
wherein the content of the first and second substances,
based on pressure, for a fuel turbine gas specific heat ratio>
And cooling channel exit temperatureT rc Get->
For cooling the channel pressure drop, by means of the formula>
Get and->
Is a constant coefficient; />
Based on pressure->
AndT rc obtaining; />
Is a predetermined constant for fuel turbine efficiency.
When in useP pf And withP tf When not equal, i.e. not matching, the fuel turbo pressure ratio needs to be adjustedπ f Post-recalculationP tf Until the two match. The adjustment mode can be external resetting or adjustment according to a preset step length. Furthermore, in order to improve the matching efficiency, the step length is set to be a variable step length. Step size according toP pf AndP tf the difference value of (a) is calculated according to a preset proportion.
The gas specific heat ratio and the gas constant can be obtained by using query software, in this example
And &>
Utilizing thermophysical property query software REFPROP (w. Boulder. Last. Gov/div838/the same/refop/frequencyly) according to the input
AndT rc and (4) obtaining.
5. And calculating and comparing the power of the oxidant pump and the power of the oxidant turbine, if the power of the oxidant pump is not matched with the power of the oxidant turbine, adjusting the pressure ratio of the oxidant turbine, and repeating the steps until the power of the oxidant pump is matched with the power of the oxidant turbine.
In particular, the oxidant pump powerP pox Can be calculated by the following formula:
wherein, the first and the second end of the pipe are connected with each other,
for oxidant injection pressure drop, by formula>
Obtaining; />
For oxidant valve pressure drop, by formula>
Obtaining; />
And &>
Is a constant coefficient; />
Is the oxidizer pump inlet pressure, at a predetermined constant; />
Is the oxidant density; />
Is the oxidizer pump efficiency, is a predetermined constant.
In particular, oxidant turbine powerP tox Can be calculated by the following formula:
wherein the content of the first and second substances,
based on pressure, is the oxidant turbo gas specific heat ratio>
And oxidant turbine inlet temperature->
Get and->
Pass and/or>
Calculating a formula; />
Is an oxidant turbine gas constant, based on pressure
And &>
Obtaining; />
For oxidant turbine efficiency, a predetermined constant is used.
When in useP pox AndP tox when not equal, i.e. not matching, the oxidant turbo pressure ratio needs to be adjustedπ ox Post-recalculationP tox Until the two match. The adjustment mode can be external resetting or adjustment according to a preset step length. In the same way as above, to improve the matching efficiency, the step length is set to be a variable step length. Step size is according toP pox AndP tox the difference value of (a) is calculated according to a preset proportion.
The same as the above, this example
And &>
Using thermophysical property query software REFPROP to input according to
And &>
And (4) obtaining.
Through the process, after the respective turbopump powers of the fuel and the oxidant are equal, the engine reaches the optimal state under the given parameter combination, and the state parameters of each key node can be obtained according to the optimal state parameters.
In a specific embodiment, the method further includes a step of outputting the key node state parameter. Specifically, the key node state parameters include flow, pressure, temperature and turbopump power at the following nodes: fuel pump front, fuel pump back, fuel valve back (injector front), cooling channel inlet, cooling channel outlet, fuel turbine back, oxidant valve back, oxidant pump front, combustion chamber.
The state parameters of each key node can be obtained by a person skilled in the art according to the relevant knowledge of the engine design. It can also be obtained from the following provided in this example:
for the flow rate:
the flow rates of the oxidant behind the oxidant valve, the oxidant pump and the oxidant pump are equal to the flow rate of the oxidant in the thrust chamber
Equal;
flow rate of combustion chamber
；
The flow rates before and after the fuel pump are the same, is
；
The inlet of the cooling channel, the outlet of the cooling channel, the flow behind the fuel turbine and the flow behind the oxidant turbine are all equal to the flow of the turbine work mass
Equal;
fuel valve back (injector front) flow and fuel flow
Are equal.
For the pressure:
the pressure before the fuel pump is the above
The pressure before the oxidant pump is equal to>
；
The pressure of the combustion chamber is as abovep c ；
Post fuel pump pressure of
；
Fuel valveBoth door back (injector front) and cooling channel entrance pressures
；
Cooling channel outlet pressure of
；
Oxidant post-pump pressure of
；
Oxidant valve back pressure of
；/>
Fuel turbine back pressure of
；
Oxidant turbine back pressure of
。
For the temperature:
combustion chamber temperature based onp c 、MRAndp e calculated by a thermodynamic calculation method or software (such as RPA);
oxidant after-turbine temperature of
；
The outlet temperature of the cooling channel is as described aboveT rc ；
The inlet temperature of the cooling channel, the temperature behind the fuel valve (in front of the injector) and the temperature behind the fuel pump are the same as the temperature in front of the fuel pump and are set values;
the temperature behind the oxidant valve and the temperature behind the oxidant pump are the same as the temperature before the oxidant pump and are set values;
fuel post-turbine temperature as above
。
Specific calculation examples are given below according to the above-described method.
The input parameters are shown in the following table:
TABLE 1 input parameters
| Serial number | Parameter (Unit) | Numerical value | Serial number | Parameter(s) | Numerical value |
| 1 | F（kN） | 1000 | 11 |
 |
0.1 |
| 2 | p e （MPa） | 0.06 | 12 | η tf | 0.6 |
| 3 | p c （MPa） | 10 | 13 | η tox | 0.6 |
| 4 |
|
6 | 14 | η pf | 0.7 |
| 5 | α | 0.17 | 15 | η pox | 0.7 |
| 6 |
 |
0.1 | 16 |  |
70.37 |
| 7 |
 |
0.2 | 17 |  |
1142.6 |
| 8 |
 |
0.1 | 18 |  |
0.3 |
| 9 |
 |
0.2 | 19 |  |
0.3 |
| 10 | T rc （K） | 500 |
Using the above method, the open expansion cycle engine state parameter profiles, including flow, pressure, temperature at each node, and turbopump power, can be calculated according to the conditions in the table, as shown in FIG. 3. When the turbine and pump powers are matched separately, the oxygen turbine power reaches 3670kW and the fuel turbine power reaches 10706kW. The overall recipe design and parameter optimization can then be adjusted based on the parameter distribution.
The present disclosure also provides a parameter estimation device based on the engine shown in fig. 1, including:
input module for obtaining engine thrustFNozzle outlet pressurep e And cooling channel exit temperatureT rc And the working condition parameters are as follows: room pressurep c And mixing ratio ofMRFlow ratio of
；
A thrust chamber specific impulse calculating module for calculating a thrust based onp c 、MRAndp e calculating thrust chamber specific impulseI spc ；
A flow calculation module for calculating a flow based onF、MR、
AndI spc the flow of the oxidant in the thrust chamber is calculated by>
And the fuel flow is greater or less>
And turbo functional flow->
：/>
The turbine pressure ratio initialization module: for initializing a fuel turbo-pressure ratio and an oxidant turbo-pressure ratio;
the fuel turbine pump matching module is used for calculating the power of the fuel pump, calculating the power of the fuel turbine based on the outlet temperature of the cooling channel, comparing the power of the fuel pump with the power of the fuel turbine, if the power of the fuel pump is not matched with the power of the fuel turbine, adjusting the pressure ratio of the fuel turbine, and repeating the module until the power of the fuel pump is matched with the power of the fuel turbine;
and the oxidant turbine pump matching module is used for calculating and comparing the power of the oxidant pump and the power of the oxidant turbine, if the power of the oxidant pump and the power of the oxidant turbine are not matched, adjusting the pressure ratio of the oxidant turbine, and repeating the module until the power of the oxidant pump and the power of the oxidant turbine are matched.
Alternatively, the fuel and oxidant turbine pressure ratios are initialized according to preset values or inputs.
Optionally, the adjustment is according to a preset step length.
Optional, fuel pump powerP pf Calculated by the following formula:
wherein the content of the first and second substances,
for fuel injection pressure drop, by formula>
Obtaining; />
For the fuel valve pressure drop, by means of the formula>
Obtaining; />
And &>
Is a constant coefficient; />
Is the fuel pump inlet pressure, at a preset constant; />
Is the fuel density; />
Is the fuel pump efficiency, is a preset constant.
Alternatively, said fuel turbine powerP tf Calculated by the following formula:
wherein the content of the first and second substances,
based on pressure, for a fuel turbine gas specific heat ratio>
And cooling channel exit temperatureT rc Get and->
For cooling the channel pressure drop, by means of the formula>
Get and->
Is a constant coefficient; />
Based on pressure->
AndT rc obtaining; />
Is a predetermined constant for fuel turbine efficiency.
Optionally, oxidant pump powerP pox Calculated by the following formula:
wherein the content of the first and second substances,
for oxidant injection pressure drop, by formula>
Obtaining; />
For oxidant valve pressure drop, by formula>
Obtaining; />
And &>
Is a constant coefficient; />
The oxidant pump inlet pressure is a preset constant; />
Is the oxidant density; />
Is the oxidizer pump efficiency, is a predetermined constant.
Optionally, said oxidant turbine powerP tox Calculated by the following formula:
wherein the content of the first and second substances,
based on pressure, is the oxidant turbo gas specific heat ratio>
And oxidant turbine inlet temperature->
Get and->
Pass and/or>
Calculating a formula; />
Is an oxidant turbine gas constant, based on pressure
And &>
Obtaining; />
For oxidant turbine efficiency, a predetermined constant is set.
Optionally, the apparatus further includes a key node state parameter output module, where the key node state parameters include flow, pressure, temperature, and power of the following nodes: fuel pump front, fuel pump back, fuel valve back (injector front), cooling channel inlet, cooling channel outlet, fuel turbine back, oxidant valve back, oxidant pump front, combustion chamber.
For the apparatus embodiment, since it is substantially similar to the method embodiment, the description is relatively simple, and reference may be made to the partial description of the method embodiment for relevant points.
Fig. 4 is a schematic structural diagram of an electronic device according to an embodiment of the present disclosure, where the electronic device may execute the processing flow provided by the foregoing method embodiment, and as shown in fig. 4, the electronic device 110 includes: memory 111, processor 112, computer programs, and communications interface 113; wherein the computer program is stored in the memory 111 and is configured to be executed by the processor 112 for performing the method as described above.
In addition, the embodiment of the present disclosure also provides a computer readable storage medium, on which a computer program is stored, where the computer program is executed by a processor to implement the method described in the above embodiment.
Embodiments of the present disclosure also provide a computer program product comprising a computer program/instructions which, when executed by a processor, cause the processor to perform the method as described above.
Those of ordinary skill in the art will understand that: all or a portion of the steps of implementing the above-described method embodiments may be performed by hardware associated with program instructions. The foregoing program may be stored in a computer-readable storage medium. When executed, the program performs steps comprising the method embodiments described above; and the aforementioned storage medium includes: various media that can store program codes, such as ROM, RAM, magnetic or optical disks.
Specific examples are given in this specification for the purpose of illustrating the disclosure and the manner of practicing the disclosure. The details introduced in the examples are not intended to limit the scope of the claims but rather to aid in understanding the present disclosure. Those skilled in the art will understand that: although the description is given in terms of embodiments, not every embodiment includes only a single embodiment, and such description is for clarity only, and those skilled in the art will recognize that the embodiments described herein may be combined as a whole to form other embodiments as would be understood by those skilled in the art. And that various modifications, changes, or alterations to the steps of the preferred embodiments are possible without departing from the spirit and scope of this disclosure and the appended claims. Therefore, the disclosure should not be limited to the disclosure of the preferred embodiment and the drawings.
Claims (10)
1. An open expansion cycle engine characterized by: the method comprises the following steps:
the fuel injection device comprises a fuel turbine (2), a fuel pump (1), a fuel valve (3), a cooling channel (5), an injector (7), a combustion chamber (6), a spray pipe (4), an oxidant turbine (10), an oxidant pump (9) and an oxidant valve (8);
the fuel is pressurized by a fuel pump (1) and then is divided into two paths after passing through a fuel valve (3); one path enters a cooling channel (5) to absorb heat from a combustion chamber (6) and then sequentially drives a fuel turbine (2) and an oxidant turbine (10) to do work and discharge the work into the environment; the other path of the mixed gas is pressurized by an oxidant pump (9) and is injected into a combustion chamber (6) by an oxidant valve (8) through an injector (7) and then is sprayed out by a spray pipe (4); the fuel turbine (2) and the oxidant turbine (10) respectively drive the fuel pump (1) and the oxidant pump (9) to work.
2. A parameter estimation method based on the open expansion cycle engine of claim 1, characterized in that: the method comprises the following steps:
thrust chamber pressure based on enginep c Thrust chamber mixing ratioMRAnd nozzle outlet pressurep e Calculating thrust chamber specific impulseI spc ；
Based on engine thrustF、MRFlow ratio of thrust chamber of engine
AndI spc calculating the oxidant flow in the thrust chamber by>
And the fuel flow is greater or less>
And turbo functional flow->
：
Initializing fuel turbo pressure ratioπ f And turbo pressure ratio of oxidantπ ox ；
Calculating fuel pump power based on cooling gallery outlet temperatureT rc Calculating the power of a fuel turbine, comparing the power of the fuel pump with the power of the fuel turbine, if the power of the fuel pump is not matched with the power of the fuel turbine, adjusting the pressure ratio of the fuel turbine, and repeating the contents of the sections until the power of the fuel pump is matched with the power of the fuel turbine;
and calculating and comparing the power of the oxidant pump and the power of the oxidant turbine, if the power of the oxidant pump and the power of the oxidant turbine are not matched, adjusting the pressure ratio of the oxidant turbine, and repeating the content of the segments until the power of the oxidant pump and the power of the oxidant turbine are matched.
3. The parameter estimation method according to claim 2, characterized in that: the initialization fuel and oxidant turbine pressure ratios are initialized according to preset values or input values.
4. The parameter estimation method according to claim 2, characterized in that: the adjustment is according to the preset step length adjustment.
5. The parameter estimation method according to claim 2, characterized in that: the fuel pump powerP pf Calculated by the following formula:
wherein the content of the first and second substances,
for fuel injection pressure drop, by formula>
Obtaining; />
For fuel valve pressure drop, by formula
Obtaining; />
And &>
Is a constant coefficient; />
Is the fuel pump inlet pressure, at a preset constant; />
Is the fuel density; />
Is the fuel pump efficiency, is a predetermined constant.
6. The parameter estimation method according to claim 5, characterized in that: the fuel turbine powerP tf Calculated by the following formula:
wherein, the first and the second end of the pipe are connected with each other,
based on pressure, for a fuel turbine gas specific heat ratio>
AndT rc get and->
For cooling the channel pressure drop, by means of the formula>
Get and->
Is a constant coefficient; />
Is a fuel turbine gas constant based on pressure
AndT rc obtaining; />
Is a predetermined constant for fuel turbine efficiency.
7. The parameter estimation method according to claim 6, characterized in that: the oxidant pump powerP pox Calculated by the following formula:
wherein, the first and the second end of the pipe are connected with each other,
for oxidant injection pressure drop, by formula>
Obtaining; />
For oxidant valve pressure drop, by formula>
Obtaining; />
And &>
Is a constant coefficient; />
The oxidant pump inlet pressure is a preset constant; />
Is the oxidant density; />
Is the oxidizer pump efficiency, is a predetermined constant.
8. The parameter estimation method according to claim 7, characterized in that: the oxidant turbine powerP tox Calculated by the following formula:
wherein, the first and the second end of the pipe are connected with each other,
based on pressure on the specific heat ratio of the oxidant turbine gas>
And oxidant turbine inlet temperature>
Get->
By>
Calculating a formula; />
Is oxidant turbine gas constant, based on pressure
And &>
Obtaining; />
For oxidant turbine efficiency, a predetermined constant is set.
9. The parameter estimation method according to claim 8, characterized in that: the method also comprises a step of outputting the state parameters of the key nodes.
10. A parameter estimation device based on the open expansion cycle engine of claim 1, characterized in that: the method comprises the following steps:
input module for obtaining engine thrustFNozzle outlet pressurep e And cooling channel exit temperatureT rc And the working condition parameters are as follows: room pressurep c Mixing ratio ofMRFlow rate ratio
；
Thrust chamber specific impulse calculation module for calculating the thrust based onp c 、MRAndp e calculating thrust chamber specific impulseI spc ；
A flow calculation module for calculating a flow based onF、MR、
AndI spc calculating the oxidant flow in the thrust chamber by>
And the fuel flow is greater or less>
And turbo functional flow->
：
The turbine pressure ratio initialization module: for initializing a fuel turbo-pressure ratio and an oxidant turbo-pressure ratio;
the fuel turbine pump matching module is used for calculating the power of the fuel pump, calculating the power of the fuel turbine based on the outlet temperature of the cooling channel, comparing the power of the fuel pump with the power of the fuel turbine, if the power of the fuel pump is not matched with the power of the fuel turbine, adjusting the pressure ratio of the fuel turbine, and repeating the module until the power of the fuel pump is matched with the power of the fuel turbine;
and the oxidant turbine pump matching module is used for calculating and comparing the power of the oxidant pump and the power of the oxidant turbine, if the power of the oxidant pump is not matched with the power of the oxidant turbine, adjusting the pressure ratio of the oxidant turbine, and repeating the module until the power of the oxidant pump is matched with the power of the oxidant turbine.
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