CN114046213B - Open type liquid oxygen kerosene engine system and thrust adjusting method thereof - Google Patents
Open type liquid oxygen kerosene engine system and thrust adjusting method thereof Download PDFInfo
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- CN114046213B CN114046213B CN202111563145.9A CN202111563145A CN114046213B CN 114046213 B CN114046213 B CN 114046213B CN 202111563145 A CN202111563145 A CN 202111563145A CN 114046213 B CN114046213 B CN 114046213B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
- F02K9/48—Feeding propellants using pumps driven by a gas turbine fed by propellant combustion gases or fed by vaporized propellants or other gases
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
- F02K9/58—Propellant feed valves
Abstract
The invention belongs to an engine system and a thrust adjusting method thereof, and provides an open type liquid oxygen kerosene engine system and a thrust adjusting method thereof, aiming at solving the technical problems that the existing open type circulating liquid oxygen kerosene engine system does not have thrust adjusting capability, cannot meet the multi-task requirement of a carrier rocket, and can realize single function.
Description
Technical Field
The invention belongs to an engine system and a thrust adjusting method thereof, and particularly relates to an open type liquid oxygen kerosene engine system and a thrust adjusting method thereof.
Background
The conventional carrier rocket mostly adopts a conventional propellant open cycle engine, the engine system has simple structure and convenient use and maintenance, but the used conventional propellant has high toxicity and price and is faced with the requirement of being updated. The new generation of carrier rocket mainly adopts a liquid oxygen kerosene propellant afterburning cycle engine, the propellant has high specific impulse performance, low cost, convenient use and maintenance, no toxicity and no pollution, but the afterburning cycle engine has high system pressure, complex structure and high maintenance cost.
Chinese patent publication No. CN111502864 discloses an open cycle liquid oxygen kerosene engine system and a use method thereof, wherein a liquid oxygen kerosene propellant with high specific impulse performance and low cost is used to achieve nontoxic launching, the structural complexity of the engine system is greatly reduced, but the thrust of the engine system is fixed, the thrust adjusting capability is not provided, the multitask requirement of a carrier rocket cannot be met, and the function singleness can be achieved.
Disclosure of Invention
The invention provides an open type liquid oxygen kerosene engine system and a thrust adjusting method thereof, aiming at solving the technical problems that the existing open type circulating liquid oxygen kerosene engine system does not have thrust adjusting capability, cannot meet the multi-task requirement of a carrier rocket, and can realize single function.
In order to achieve the purpose, the invention adopts the following technical scheme to realize the purpose:
an open type liquid oxygen kerosene engine system comprises a thrust chamber, a turbine, a fuel pump, an oxidant pump, a fuel generator, an oxygen auxiliary pipeline and a fuel auxiliary pipeline;
the turbine, the fuel pump and the oxidant pump are coaxially connected;
the outlet of the oxidant pump is connected with the thrust chamber through an oxygen main pipeline, and an oxygen main valve is arranged on the oxygen main pipeline;
the fuel pump outlet is connected with the thrust chamber through a fuel main pipeline, and a fuel main valve is arranged on the fuel main pipeline;
it is characterized in that the device is characterized in that,
the inlet end of the oxygen auxiliary pipeline is connected with an oxygen main pipeline positioned between an oxidant pump outlet and an oxygen main valve, the outlet end of the oxygen auxiliary pipeline is connected with a fuel gas generator, and an oxygen auxiliary pipeline double-station valve is arranged on the oxygen auxiliary pipeline;
the inlet end of the fuel secondary pipeline is connected with a fuel main pipeline between the fuel pump and the fuel main valve, the outlet end of the fuel secondary pipeline is connected with the fuel gas generator, a fuel secondary pipeline regulator and a fuel secondary valve are arranged on the fuel secondary pipeline, and the fuel secondary valve is arranged close to the fuel gas generator.
Further, an exhaust line of the turbine communicates with the thrust chamber.
The invention also provides a thrust adjusting method of the open type liquid oxygen kerosene engine system, which is characterized by comprising the following steps:
s1, keeping the oxygen secondary path double-station valve in a high-opening state, increasing the flow resistance coefficient of the fuel secondary path regulator, increasing the mixing ratio of the fuel gas generator to a first preset value, and simultaneously increasing the thrust generated by a thrust chamber; wherein the first preset value is a corresponding maximum mixing ratio of acceptable upper limit of carbon deposit formed by combustion of the gas generator;
s2, switching the oxygen secondary path double-station valve to a low-opening state to reduce the mixing ratio of the gas generator to a second preset value; the value of the second preset value is the minimum mixing ratio of stable combustion of the gas generator;
s3, continuously increasing the flow resistance coefficient of the fuel secondary path regulator until the mixing ratio of the fuel gas generator reaches a third preset value, and simultaneously enabling the thrust generated by the thrust chamber to reach a preset working condition; wherein the third preset value is the design mixing ratio of the gas generator when the engine system works in a steady state.
Further, in step S1, the value of the first preset value is 0.4 to 0.45.
Further, in step S2, the value of the second preset value is 0.25 to 0.26.
Further, in step S3, the value of the third preset value is 0.37 to 0.40.
Furthermore, the flow resistance coefficient of the oxygen secondary path double-station valve in the low opening state is 4.2-8.6 times of the flow resistance coefficient of the oxygen secondary path double-station valve in the high opening state.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the open type liquid oxygen kerosene engine system, the oxygen secondary channel double-station valve is arranged on the oxygen secondary pipeline, the fuel secondary pipeline is provided with the fuel secondary channel regulator, and the flow and the mixing ratio of a propellant entering the fuel generator can be regulated through the oxygen secondary channel double-station valve and the fuel secondary channel regulator, so that the engine system can carry out thrust regulation according to task requirements.
2. In the engine system, the turbine exhaust pipeline is communicated with the thrust chamber, so that exhaust of the turbine enters the thrust chamber, and the thrust generated by the thrust chamber can be effectively improved.
3. The thrust adjusting method comprises two-stage adjustment, wherein the flow and the mixing ratio of the propellant entering the fuel gas generator are adjusted and controlled by the fuel secondary path regulator and the oxygen secondary path double-station valve, and the temperature and the flow of the fuel gas generated by the fuel gas generator are changed, so that the power of a turbine is influenced, the flow and the pressure of the propellant entering a thrust chamber are changed, and the aim of adjusting the thrust of the engine in a large range is fulfilled. The thrust of the open liquid oxygen kerosene engine can be adjusted in a large range only by a small-flow normal-temperature fuel secondary path regulator and an oxygen secondary path double-station valve.
4. The invention adjusts the thrust of the engine system by adjusting the flow of the oxygen secondary pipeline and the fuel secondary pipeline, the oxygen main pipeline and the fuel main pipeline do not need to be adjusted, the adjusting logic is simple, the reliability is high, the other working flows of the engine system are not influenced, and the mixing ratio of the thrust chamber and the fuel generator can be in the normal working range.
5. The values of the first preset value and the second preset value enable the fuel gas generator to stably burn and not to generate excessive carbon deposition to influence the operation of an engine system in the thrust adjusting process.
Drawings
FIG. 1 is a schematic structural diagram of an open liquid oxygen kerosene engine system according to an embodiment of the present invention;
FIG. 2 is a graph of the change in the mixture ratio of the gas generator during the conditioning process using the thrust force conditioning method of the embodiment of FIG. 1;
FIG. 3 is a graph showing a variation of a relative value of a turbine speed during a thrust adjusting process according to the embodiment of FIG. 1;
FIG. 4 is a graph showing the variation of the thrust relative value during the adjustment process using the thrust adjustment method of the embodiment of FIG. 1.
Wherein: 1-thrust chamber, 2-gas generator, 3-oxidant pump, 4-fuel pump, 5-turbine, 6-oxygen secondary double-station valve, 7-fuel secondary valve, 8-fuel secondary regulator, 9-fuel main valve, 10-oxygen main valve, 11-oxygen main pipeline, 12-fuel main pipeline, 13-oxygen secondary pipeline, 14-fuel secondary pipeline and 15-exhaust pipeline.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
The invention provides an open type liquid oxygen kerosene engine system capable of carrying out large-range thrust adjustment and a thrust adjustment method thereof aiming at the variable thrust requirement in the actual use of an open type circulation liquid oxygen kerosene engine, which are used for meeting the requirements of different flight tasks and improving the adaptability of the engine to various different flight tasks.
Referring to fig. 1, an open liquid oxygen kerosene engine system according to an embodiment of the present invention includes a thrust chamber 1, a gas generator 2, an oxidizer pump 3, a fuel pump 4, a turbine 5, a main fuel valve 9, a main oxygen valve 10, a fuel secondary regulator 8, a secondary oxygen position valve 6, and a secondary fuel valve 7.
The propellant of the engine system consists of liquid oxygen as an oxidant and kerosene as a fuel, wherein the liquid oxygen and the kerosene are respectively introduced into the engine system from the outside through pipelines, are respectively pressurized through the oxidant pump 3 and the fuel pump 4 after entering from inlets of the oxidant pump 3 and the fuel pump 4, the liquid oxygen enters the thrust chamber 1 through the oxygen main pipeline 11, the kerosene enters the thrust chamber 1 through the fuel main pipeline 12, and the liquid oxygen and the kerosene are combusted in the thrust chamber 1 to generate the thrust of the engine. The oxygen main valve 10 is arranged on an oxygen main pipeline 11 between the outlet of the oxidant pump 3 and the thrust chamber 1, an oxygen auxiliary pipeline 13 is led out from the oxygen main pipeline 11 between the outlet of the oxidant pump 3 and the oxygen main valve 10 at the rear side of the oxidant pump 3, the other end of the oxygen auxiliary pipeline 13 is connected with the fuel gas generator 2, so that part of liquid oxygen enters the fuel gas generator 2, and the oxygen auxiliary pipeline double-station valve 6 is arranged on the oxygen auxiliary pipeline 13. The fuel main valve 9 is arranged on a fuel main pipeline 12 between the outlet of the fuel pump 4 and the thrust chamber 1, a fuel secondary pipeline 14 is led out from the fuel main pipeline 12 between the outlet of the fuel pump 4 and the fuel main valve 9 at the rear side of the fuel pump 4, the other end of the fuel secondary pipeline 14 is connected with the fuel gas generator 2 to lead part of kerosene to enter the fuel gas generator 2, the fuel secondary pipeline regulator 8 and the fuel secondary valve 7 are both arranged on the fuel secondary pipeline 14, and the fuel secondary valve 7 is arranged at one side close to the fuel gas generator 2. The liquid oxygen and the kerosene entering the gas generator 2 are combusted in the gas generator 2, and the generated fuel-rich gas provides a driving working medium for the turbine 5. The turbine 5, the fuel pump 4 and the oxidant pump 3 are coaxially connected, and the turbine 5 provides driving power for the oxidant pump 3 and the fuel pump 4 to drive the oxidant pump 3 and the fuel pump 4 to synchronously rotate. The fuel secondary regulator 8 is used for controlling the flow of fuel entering the gas generator 2, and the oxygen secondary double-station valve 6 is used for controlling the flow of liquid oxygen entering the gas generator 2.
In addition, in order to maximize the thrust force of the thrust chamber 1, the exhaust line 15 of the turbine 5 is connected to the thrust chamber 1, and the exhaust gas of the turbine 5 is discharged into the thrust chamber 1.
The following is a specific example of the thrust adjusting method of the present invention, in which the preset condition to be adjusted is a low condition of 55%:
when the engine system is in a steady state working condition, corresponding to a 100% thrust working condition, the mixing ratio of the steady state working of the gas generator 2 is in a design range of 0.37-0.40, the oxygen secondary path double-station valve 6 is in a low-opening state, and the flow resistance coefficient is kept to be 270 plus one charge of 500MPa/(kg/s)2. According to the actual task requirement, at the moment, the thrust of the engine is adjusted, firstly, the flow resistance coefficient of the fuel secondary path regulator 8 is increased, the mixing ratio of the fuel gas generator 2 is increased to 0.438, the thrust generated by the thrust chamber 1 is increased to 103.2%, the oxygen secondary path double-station valve 6 is switched to a low opening state, and the corresponding flow resistance coefficient is 2100-2At this time, the mixing ratio of the gas generator 2 is rapidly reduced to 0.253, and the flow resistance coefficient of the fuel secondary regulator 8 is continuously increased until the thrust of the thrust chamber 1 reaches a low condition of 55%, and the mixing ratio of the gas generator 2 is restored to a design range of 0.37-0.40.
In the embodiment of the regulation method described above, 0.253 is the minimum mixing ratio at which the gas generator 2 can stabilize combustion, and in this embodiment, if the mixing ratio is higher than 0.438, excessive soot is generated in the gas generator 2. In other embodiments of the invention, the two values, as well as the design mix ratio of the gas generator 2 at steady state operation of the engine system, corresponding to 0.37-0.40, can be adjusted according to the actual conditions and mission requirements of the engine system.
By adopting the engine system and the thrust adjusting method of the open-type liquid oxygen kerosene engine system to adjust the thrust, a static characteristic calculation model is established, and static balance calculation is performed on each node in the thrust adjusting process of the engine system. Wherein, the mixing ratio variation curve of the gas generator 2 in the thrust adjusting process is shown in fig. 2, and as can be seen from fig. 2, the mixing ratio variation range of the gas generator 2 is between 0.25 and 0.45, which meets the working requirement of the liquid oxygen kerosene propellant rich gas generator 2. Fig. 3 shows a variation curve of the rotation speed of the turbine 5 relative to the value in the thrust adjustment process, and the generated rich gas physical property parameter changes along with the change of the mixing ratio of the gas generator 2, so that the rotation speed of the turbine 5 changes along with the change, and the change range is in a range in which the turbine can normally work (according to the characteristics of the existing turbine 5, the rotation speed of the turbine 5 should not be higher than 12000 r/min), thereby meeting the working requirements of the turbine 5. The thrust relative value change curve in the thrust adjustment process is shown in fig. 4, after the rotation speed of the turbine 5 changes, the work capacities of the oxidizer pump 3 and the fuel pump 4 also change, so that the pressure and the flow of the propellant entering the thrust chamber 1 change, the thrust generated by combustion also changes, and as can be seen from fig. 4, under a low working condition, the thrust adjustment can meet the 55% working condition requirement.
The open liquid oxygen kerosene engine system can realize large-range thrust adjustment, meet the requirements of different flight tasks and improve the adaptability of the engine system to various different flight tasks. Aiming at the engine system which can not adjust the thrust at present, the function of adjusting the thrust can be realized only by adding the fuel secondary path regulator 8 and the oxygen secondary path double-station valve 6 with small flow, the structure change amount is small, and the large-range adjustment of the thrust can be realized.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. A thrust adjustment method of an open liquid oxygen kerosene engine system, the open liquid oxygen kerosene engine system comprises a thrust chamber (1), a turbine (5), a fuel pump (4), an oxidant pump (3), a fuel generator (2), and an oxygen secondary pipeline (13) and a fuel secondary pipeline (14);
the turbine (5), the fuel pump (4) and the oxidant pump (3) are coaxially connected;
the outlet of the oxidant pump (3) is connected with the thrust chamber (1) through an oxygen main pipeline (11), and an oxygen main valve (10) is arranged on the oxygen main pipeline (11);
the outlet of the fuel pump (4) is connected with the thrust chamber (1) through a fuel main pipeline (12), and a fuel main valve (9) is arranged on the fuel main pipeline (12);
it is characterized in that the preparation method is characterized in that,
the inlet end of the oxygen auxiliary pipeline (13) is connected with an oxygen main pipeline (11) positioned between the outlet of the oxidant pump (3) and the oxygen main valve (10), the outlet end of the oxygen auxiliary pipeline is connected with the fuel gas generator (2), and the oxygen auxiliary pipeline (13) is provided with an oxygen auxiliary double-station valve (6);
the inlet end of the fuel secondary pipeline (14) is connected with a fuel main pipeline (12) positioned between the fuel pump (4) and the fuel main valve (9), the outlet end of the fuel secondary pipeline is connected with the gas generator (2), a fuel secondary pipeline regulator (8) and a fuel secondary valve (7) are arranged on the fuel secondary pipeline (14), and the fuel secondary valve (7) is arranged close to the gas generator (2);
the adjusting method comprises the following steps:
s1, keeping the oxygen secondary path double-station valve (6) in a high-opening state, increasing the flow resistance coefficient of the fuel secondary path regulator (8), increasing the mixing ratio of the fuel gas generator (2) to a first preset value, and simultaneously increasing the thrust generated by the thrust chamber (1); wherein the first preset value is a corresponding maximum mixing ratio of acceptable upper limit of carbon deposit formed by combustion of the gas generator (2);
s2, switching the oxygen secondary path double-station valve (6) to a low-opening state to reduce the mixing ratio of the gas generator (2) to a second preset value; the value of the second preset value is the minimum mixing ratio of the stable combustion of the gas generator (2);
s3, continuously increasing the flow resistance coefficient of the fuel secondary regulator (8) until the mixing ratio of the gas generator (2) reaches a third preset value, and simultaneously enabling the thrust generated by the thrust chamber (1) to reach a preset working condition; wherein the third preset value is the design mixing ratio of the gas generator (2) when the engine system works in a steady state.
2. The thrust force adjusting method of an open liquid oxygen kerosene engine system according to claim 1, characterized in that: in step S1, the first preset value is 0.4 to 0.45.
3. The thrust force adjusting method of an open liquid oxygen kerosene engine system according to claim 2, characterized in that: in step S2, the value of the second preset value is 0.25 to 0.26.
4. The thrust force adjusting method of an open liquid oxygen kerosene engine system according to claim 3, characterized in that: in step S3, the value of the third preset value is 0.37 to 0.40.
5. The thrust force adjusting method of an open liquid oxygen kerosene engine system according to claim 4, characterized in that: the flow resistance coefficient of the oxygen secondary path double-station valve (6) in the low opening state is 4.2-8.6 times of the flow resistance coefficient of the oxygen secondary path double-station valve (6) in the high opening state.
6. The thrust force adjusting method of an open liquid oxygen kerosene engine system according to claim 5, characterized in that: the exhaust line (15) of the turbine (5) is in communication with the thrust chamber (1).
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| JPH08338313A (en) * | 1995-06-09 | 1996-12-24 | Mitsubishi Heavy Ind Ltd | Liquid rocket engine |
| RU2010144105A (en) * | 2010-10-28 | 2012-05-10 | Открытое акционерное общество "НПО Энергомаш имени академика В.П. Глушко" (RU) | OPEN DIAGRAM LIQUID ROCKET ENGINE |
| CN210738696U (en) * | 2019-10-21 | 2020-06-12 | 西安未来空天引擎科技有限公司 | Open-cycle variable-thrust liquid rocket engine system |
| CN111502864A (en) * | 2020-04-16 | 2020-08-07 | 西安航天动力研究所 | Open-cycle liquid oxygen kerosene engine system and use method thereof |
| CN112800562A (en) * | 2021-03-29 | 2021-05-14 | 星河动力(北京)空间科技有限公司 | Thrust control method, thrust control device, electronic device, and storage medium |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08338313A (en) * | 1995-06-09 | 1996-12-24 | Mitsubishi Heavy Ind Ltd | Liquid rocket engine |
| RU2010144105A (en) * | 2010-10-28 | 2012-05-10 | Открытое акционерное общество "НПО Энергомаш имени академика В.П. Глушко" (RU) | OPEN DIAGRAM LIQUID ROCKET ENGINE |
| CN210738696U (en) * | 2019-10-21 | 2020-06-12 | 西安未来空天引擎科技有限公司 | Open-cycle variable-thrust liquid rocket engine system |
| CN111502864A (en) * | 2020-04-16 | 2020-08-07 | 西安航天动力研究所 | Open-cycle liquid oxygen kerosene engine system and use method thereof |
| CN112800562A (en) * | 2021-03-29 | 2021-05-14 | 星河动力(北京)空间科技有限公司 | Thrust control method, thrust control device, electronic device, and storage medium |
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