CN116044610B - Double-expansion circulation liquid rocket engine system - Google Patents
Double-expansion circulation liquid rocket engine system Download PDFInfo
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- CN116044610B CN116044610B CN202211706428.9A CN202211706428A CN116044610B CN 116044610 B CN116044610 B CN 116044610B CN 202211706428 A CN202211706428 A CN 202211706428A CN 116044610 B CN116044610 B CN 116044610B
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- fuel
- oxidant
- turbine
- cooling jacket
- pump
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- 239000007788 liquid Substances 0.000 title claims abstract description 38
- 239000000446 fuel Substances 0.000 claims abstract description 201
- 239000007800 oxidant agent Substances 0.000 claims abstract description 197
- 230000001590 oxidative effect Effects 0.000 claims abstract description 188
- 238000001816 cooling Methods 0.000 claims abstract description 73
- 238000002485 combustion reaction Methods 0.000 claims abstract description 48
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 11
- 239000001301 oxygen Substances 0.000 claims abstract description 11
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 11
- 230000001105 regulatory effect Effects 0.000 claims description 14
- 230000009977 dual effect Effects 0.000 claims description 13
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 8
- 230000001276 controlling effect Effects 0.000 claims description 4
- 238000002156 mixing Methods 0.000 claims description 4
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 3
- 230000008859 change Effects 0.000 claims description 3
- 239000001257 hydrogen Substances 0.000 claims description 3
- 229910052739 hydrogen Inorganic materials 0.000 claims description 3
- 238000007789 sealing Methods 0.000 abstract description 4
- 239000007789 gas Substances 0.000 description 4
- 230000033228 biological regulation Effects 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 239000003380 propellant Substances 0.000 description 3
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
Classifications
-
- 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
-
- 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
-
- 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
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
Abstract
The invention discloses a double-expansion circulation liquid rocket engine system, which comprises: a fuel pump, a fuel turbine, a fuel cooling jacket, an oxidant cooling jacket, a combustion device, an oxidant turbine, an oxidant pump, an oxidant main valve, a fuel control valve, and a fuel bypass; the fuel pump, the fuel cooling jacket, the fuel turbine and the burner head cavity form a fuel passage; a main fuel valve is arranged on a connecting pipeline between the fuel turbine and the head cavity of the combustion device; one end of the fuel bypass is communicated with the pipeline A, and the other end of the fuel bypass is communicated with the pipeline B; the fuel control valve is arranged on the fuel bypass path; the oxidant pump, the oxidant cooling jacket and the head cavity of the combustion device of the oxidant turbine form an oxidant passage; an oxidant main valve is arranged on a connecting pipeline between the oxidant turbine and the head cavity of the combustion device. The invention changes the turbine working medium of the oxygen turbine pump into oxygen, simplifies the sealing structure of the oxygen turbine pump, and improves the working safety and the inherent reliability of the oxygen turbine pump.
Description
Technical Field
The invention belongs to the technical field of liquid rocket engines, and particularly relates to a double-expansion-cycle liquid rocket engine system.
Background
The pressure of the combustion chamber of the pump-type liquid rocket engine is higher than the pressure of the storage tank, and the propellant needs to be pressurized by a pressurizing device and then is conveyed into the thrust chamber for combustion.
The conventional supercharging device of the active pump type rocket engine is a turbine pump, a part of fuel and oxidant are combusted to generate gas to drive a turbine, and the turbine drives a booster pump through a shafting, so that the purpose of supercharging the propellant is achieved. In low temperature liquid rocket engines, the fuel is used to drive the turbo pump after heat exchange expansion in the thrust chamber cooling jacket. Therefore, the working medium of the turbine is usually rich in fuel gas or gaseous fuel, which causes the problem that the turbine pump for conveying the oxidant is incompatible with the pump medium, and once the two mediums meet through the gap of the turbine pump shaft system, destructive results are generated, so very complex sealing and isolating measures must be adopted to ensure absolute isolation of the two mediums, thus the structure of the oxidant turbine pump is complex, and reliability and safety risks exist.
Disclosure of Invention
The technical solution of the invention is as follows: the double-expansion-cycle liquid rocket engine system has the advantages that the defects of the prior art are overcome, the turbine working medium of the oxygen turbine pump is changed into oxygen, the sealing structure of the oxygen turbine pump is simplified, and the working safety and the inherent reliability of the oxygen turbine pump are improved.
In order to solve the technical problems, the invention discloses a double-expansion-cycle liquid rocket engine system, which comprises: a fuel pump, a fuel turbine, a fuel cooling jacket, an oxidant cooling jacket, a combustion device, an oxidant turbine, an oxidant pump, an oxidant main valve, a fuel control valve, and a fuel bypass;
the fuel pump is connected with the fuel turbine; the outlet of the fuel pump is connected with the inlet of the fuel cooling jacket, the outlet of the fuel cooling jacket is connected with the inlet of the fuel turbine, and the outlet of the fuel turbine is connected with the head cavity of the combustion device; a main fuel valve is arranged on a connecting pipeline between the fuel turbine and the head cavity of the combustion device;
one end of the fuel bypass is communicated with the pipeline A, and the other end of the fuel bypass is communicated with the pipeline B; the fuel control valve is arranged on the fuel bypass path; the pipeline A is a connecting pipeline between the outlet of the fuel cooling jacket and the inlet of the fuel turbine, and the pipeline B is a connecting pipeline between the fuel turbine and the main valve of the fuel;
the oxidant pump is connected with the oxidant turbine; the outlet of the oxidant pump is connected with the inlet of the oxidant cooling jacket, the outlet of the oxidant cooling jacket is connected with the inlet of the oxidant turbine, and the outlet of the oxidant turbine is connected with the head cavity of the combustion device; an oxidant main valve is arranged on a connecting pipeline between the oxidant turbine and the head cavity of the combustion device;
the fuel cooling jacket and the oxidant cooling jacket are disposed outside the combustion device, with the fuel cooling jacket being located above the oxidant cooling jacket.
In the above-mentioned double expansion cycle liquid rocket engine system, further comprising: an oxidant regulator valve and an oxidant bypass passage;
one end of the oxidant bypass is communicated with the pipeline C, and the other end of the oxidant bypass is communicated with the pipeline D; the oxidant regulating valve is arranged on the oxidant bypass path; the pipeline C is a connecting pipeline between an outlet of the oxidant cooling jacket and an inlet of the oxidant turbine, and the pipeline D is a connecting pipeline between the oxidant turbine and the main valve of the oxidant.
In the double-expansion-cycle liquid rocket engine system, a main fuel valve is used for adjusting the flow rate of fuel in a control pipeline.
In the double-expansion-cycle liquid rocket engine system, the main valve of the oxidant is used for adjusting the flow of the oxidant in the control pipeline.
In the above-described dual expansion cycle liquid rocket engine system, the fuel control valve is used to regulate and control the flow of medium into the fuel turbine.
In the double-expansion-cycle liquid rocket engine system, the oxidant regulating valve is used for regulating and controlling the flow of the medium entering the oxidant turbine.
In the above-described dual expansion cycle liquid rocket engine system, when the engine is operating,
the low-temperature fuel and the low-temperature oxidant flow into the fuel pump and the oxidant pump respectively from the fuel inlet and the oxidant inlet under the pressure of the storage tank; the low-temperature fuel and the low-temperature oxidant respectively enter a fuel cooling jacket and an oxidant cooling jacket after being pressurized by a fuel pump and an oxidant pump, heat exchange is carried out by means of a self heat sink of the fuel cooling jacket, a self heat sink of the oxidant cooling jacket and the relative high temperature of the surrounding environment, and then the fuel enters a combustion device after passing through a fuel turbine and a fuel main valve, and the oxidant enters the combustion device after passing through an oxidant turbine and an oxidant main valve; mixing, igniting and burning fuel and oxidant in a burning device; then, the temperature of the combustion device is gradually increased, the heat quantity absorbed by the fuel and the oxidant in the fuel cooling jacket and the oxidant cooling jacket is gradually increased, the enthalpy value of the fuel and the oxidant at the outlet of the fuel cooling jacket and the outlet of the oxidant cooling jacket is also gradually increased, the acting capability is enhanced until the fuel turbine and the oxidant turbine are driven to rotate, and then the fuel pump and the oxidant pump are driven by the shafting to boost the fuel and the oxidant, so that the mass of the fuel and the oxidant entering the fuel cooling jacket and the oxidant cooling jacket in unit time is increased; the mass of fuel and oxidant entering the combustion device in unit time is further increased, and the heat released in the combustion process is further increased; under the dual actions of flow increase and heat flow increase, the medium driving the fuel turbine and the oxidant turbine is further enhanced in function, so that the pressurizing capacity of the fuel pump and the oxidant pump is further improved, forward feedback is formed, and finally, the balanced state, namely the main-stage working condition of the engine, is achieved.
In the double-expansion-cycle liquid rocket engine system, when the engine enters a main-stage working condition and the mixing ratio of the engine, namely the ratio of the oxidant flow to the fuel flow is required to be adjusted, the opening of the fuel control valve is adjusted to increase or decrease the medium flow flowing through the fuel turbine so as to adjust the ratio of the output power of the fuel turbine to the output power of the oxidant turbine, and further the adjustment of the ratio of the oxidant flow to the fuel flow is realized.
In the double-expansion-cycle liquid rocket engine system, after the engine enters a main-stage working condition, when engine thrust adjustment needs to be carried out, the opening of the fuel control valve is adjusted, and simultaneously the opening of the oxidant adjusting valve is adjusted in cooperation with the opening change of the fuel control valve, so that the total power of the fuel turbine and the oxidant turbine is increased or reduced, and the engine thrust is changed.
In the double-expansion-cycle liquid rocket engine system, the fuel is hydrogen or methane, and the oxidant is oxygen.
The invention has the following advantages:
(1) The invention discloses a double-expansion circulation liquid rocket engine system, which is characterized in that an oxidant is introduced into an oxidant cooling jacket, and an oxidant turbine is driven after heat exchange expansion, so that the compatibility of an oxidant pump and an oxidant turbine medium is realized, the difficulty of sealing and isolating the oxidant turbine pump is simplified, the shafting structure is simplified, and the working safety and reliability of the double-expansion circulation liquid rocket engine system are greatly improved.
(2) The invention discloses a double-expansion circulation liquid rocket engine system, which introduces fuel and oxidant into a cooling jacket for heat exchange and expansion, turns into gas state and then drives a turbine, then enters a thrust chamber for combustion, turns liquid-liquid combustion or gas-liquid combustion under the normal condition of a pump pressure type liquid rocket engine into gas-gas combustion, reduces the energy required by ignition of the thrust chamber, improves the ignition reliability, and in addition, the gas-gas combustion also has better combustion stability, can reduce combustion pressure pulsation, realizes more stable thrust output, further improves the working reliability of the engine, and also reduces the possibility of longitudinal coupling vibration with a rocket propellant conveying system.
(3) The invention discloses a double-expansion-cycle liquid rocket engine system, wherein driving mediums of a fuel turbine and an oxidant turbine are mutually opposite, the fuel and oxidant supply system is completely decoupled, and the implementation difficulty of engine performance parameter adjustment is reduced.
(4) The invention discloses a double-expansion circulation liquid rocket engine system which can be applied to double low-temperature liquid rocket engines including oxyhydrogen engines and liquid oxygen/methane engines.
Drawings
FIG. 1 is a schematic diagram of a dual expansion cycle liquid rocket engine system in accordance with an embodiment of the present invention;
FIG. 2 is a schematic illustration of a further dual expansion cycle liquid rocket engine system in accordance with an embodiment of the present invention.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the embodiments of the present invention disclosed herein will be described in further detail with reference to the accompanying drawings.
As shown in fig. 1, in the present embodiment, the dual expansion cycle liquid rocket engine system includes: a fuel pump 1, a fuel turbine 2, a fuel cooling jacket 3, an oxidant cooling jacket 4, a combustion device 5, an oxidant turbine 7, an oxidant pump 8, an oxidant main valve 10, a fuel main valve 11, a fuel control valve 12, and a fuel bypass passage 14. Wherein the fuel pump 1 is connected with the fuel turbine 2; the outlet of the fuel pump 1 is connected with the inlet of the fuel cooling jacket 3, the outlet of the fuel cooling jacket 3 is connected with the inlet of the fuel turbine 2, and the outlet of the fuel turbine 2 is connected with the head cavity of the combustion device 5; a main fuel valve 11 is arranged on the connecting pipeline between the fuel turbine 2 and the head cavity of the combustion device 5. One end of the fuel bypass 14 is communicated with the pipeline A, and the other end is communicated with the pipeline B; the fuel control valve 12 is provided on the fuel bypass passage 14; the pipeline A is a connecting pipeline between the outlet of the fuel cooling jacket 3 and the inlet of the fuel turbine 2, and the pipeline B is a connecting pipeline between the fuel turbine 2 and the main fuel valve 11. The oxidant pump 8 is connected with the oxidant turbine 7; the outlet of the oxidant pump 8 is connected with the inlet of the oxidant cooling jacket 4, the outlet of the oxidant cooling jacket 4 is connected with the inlet of the oxidant turbine 7, and the outlet of the oxidant turbine 7 is connected with the head cavity of the combustion device 5; an oxidant main valve 10 is arranged on a connecting pipeline between the oxidant turbine 7 and the head cavity of the combustion device 5. A fuel cooling jacket 3 and an oxidant cooling jacket 4 are provided outside the combustion device 5, the fuel cooling jacket 3 being located above the oxidant cooling jacket 4.
In this embodiment, as shown in fig. 2, the dual expansion cycle liquid rocket engine system may further include: an oxidant regulating valve 6 and an oxidant bypass passage 15. Wherein, one end of the oxidant bypass passage 15 is communicated with the pipeline C18, and the other end is communicated with the pipeline D19; the oxidant regulating valve 6 is provided on the oxidant bypass passage 15; the line C18 is a connecting line between the outlet of the oxidant cooling jacket 4 and the inlet of the oxidant turbine 7, and the line D19 is a connecting line between the oxidant turbine 7 and the oxidant main valve 10.
In this embodiment, a fuel main valve 11 is used to regulate the flow of fuel in the control line. An oxidizer main valve 10 for regulating the flow of oxidizer in the control line. A fuel control valve 12 for regulating and controlling the flow of medium into the fuel turbine 2. An oxidant regulating valve 6 for regulating and controlling the flow of medium into the oxidant turbine 7.
In this embodiment, the working principle of the dual expansion cycle liquid rocket engine system is as follows:
when the engine works, low-temperature fuel and low-temperature oxidant respectively flow into the fuel pump 1 and the oxidant pump 8 through the fuel inlet 13 and the oxidant inlet 9 under the pressure of the storage tank; the low-temperature fuel and the low-temperature oxidant respectively enter the fuel cooling jacket 3 and the oxidant cooling jacket 4 after being pressurized by the fuel pump 1 and the oxidant pump 8, heat exchange is carried out by means of the self heat sink of the fuel cooling jacket 3, the self heat sink of the oxidant cooling jacket 4 and the relative high temperature of the surrounding environment, the fuel enters the combustion device 5 after passing through the fuel turbine 2 and the fuel main valve 11, and the oxidant enters the combustion device 5 after passing through the oxidant turbine 7 and the oxidant main valve 10; the fuel and the oxidant are mixed, ignited and combusted in the combustion device 5; subsequently, the temperature of the combustion device 5 gradually increases, the heat absorbed by the fuel and the oxidant in the fuel cooling jacket 3 and the oxidant cooling jacket 4 gradually increases, so that enthalpy values of the fuel and the oxidant at the outlet of the fuel cooling jacket 3 and the outlet of the oxidant cooling jacket 4 also gradually increase, the power-generating capacity is enhanced until the fuel turbine 2 and the oxidant turbine 7 are driven to rotate, and then the fuel pump 1 and the oxidant pump 8 are driven by a shafting to boost the fuel and the oxidant, so that the mass of the fuel and the oxidant entering the fuel cooling jacket 3 and the oxidant cooling jacket 4 in unit time is increased; so that the mass of fuel and oxidant entering the combustion device 5 in unit time is increased, and the heat released in the combustion process is further increased; under the dual actions of flow increase and heat flow increase, the medium driving the fuel turbine 2 and the oxidant turbine 7 is further enhanced in function, so that the pressurizing capacity of the fuel pump 1 and the oxidant pump 8 is further improved, forward feedback is formed, and finally, an equilibrium state, namely, the main-stage working condition of the engine is achieved.
In this embodiment, when the engine enters the main stage condition and the mixing ratio of the engine, that is, the ratio of the oxidant flow rate to the fuel flow rate needs to be adjusted, the opening of the fuel control valve 12 is adjusted to increase or decrease the flow rate of the medium flowing through the fuel turbine 2 so as to adjust the ratio of the output power of the fuel turbine 2 to the output power of the oxidant turbine 7, thereby realizing the adjustment of the ratio of the oxidant flow rate to the fuel flow rate.
In this embodiment, after the engine enters the main-stage working condition, when the engine thrust adjustment needs to be performed, the opening of the fuel control valve 12 is adjusted, and simultaneously, the opening of the oxidant adjusting valve 6 is adjusted in cooperation with the opening change of the fuel control valve 12, so that the total power of the fuel turbine 2 and the oxidant turbine 7 is increased or decreased, and the engine thrust is further changed. Note that, if the engine is not required to have thrust regulation capability (i.e., the engine is not required to perform wide-range parameter regulation), the oxidant-regulating valve 6 and the oxidant bypass passage 15 may not be provided, and the system may be further simplified as shown in fig. 1. If the engine needs to have thrust regulation capability, an oxidizer regulating valve 6 and an oxidizer bypass passage 15 are provided, as shown in fig. 2.
In this embodiment, the fuel is hydrogen or methane and the oxidant is oxygen.
Although the present invention has been described in terms of the preferred embodiments, it is not intended to be limited to the embodiments, and any person skilled in the art can make any possible variations and modifications to the technical solution of the present invention by using the methods and technical matters disclosed above without departing from the spirit and scope of the present invention, so any simple modifications, equivalent variations and modifications to the embodiments described above according to the technical matters of the present invention are within the scope of the technical matters of the present invention.
What is not described in detail in the present specification belongs to the known technology of those skilled in the art.
Claims (6)
1. A dual expansion cycle liquid rocket engine system, comprising: a fuel pump (1), a fuel turbine (2), a fuel cooling jacket (3), an oxidant cooling jacket (4), a combustion device (5), an oxidant regulating valve (6), an oxidant turbine (7), an oxidant pump (8), an oxidant main valve (10), a fuel main valve (11), a fuel control valve (12), a fuel bypass passage (14) and an oxidant bypass passage (15);
the fuel pump (1) is connected with the fuel turbine (2); the outlet of the fuel pump (1) is connected with the inlet of the fuel cooling jacket (3), the outlet of the fuel cooling jacket (3) is connected with the inlet of the fuel turbine (2), and the outlet of the fuel turbine (2) is connected with the head cavity of the combustion device (5); a fuel main valve (11) is arranged on a connecting pipeline between the fuel turbine (2) and the head cavity of the combustion device (5);
one end of the fuel bypass passage (14) is communicated with the pipeline A, and the other end is communicated with the pipeline B; a fuel control valve (12) is provided on the fuel bypass passage (14); the pipeline A is a connecting pipeline between an outlet of the fuel cooling jacket (3) and an inlet of the fuel turbine (2), and the pipeline B is a connecting pipeline between the fuel turbine (2) and the fuel main valve (11);
the oxidant pump (8) is connected with the oxidant turbine (7); the outlet of the oxidant pump (8) is connected with the inlet of the oxidant cooling jacket (4), the outlet of the oxidant cooling jacket (4) is connected with the inlet of the oxidant turbine (7), and the outlet of the oxidant turbine (7) is connected with the head cavity of the combustion device (5); an oxidant main valve (10) is arranged on a connecting pipeline between the oxidant turbine (7) and the head cavity of the combustion device (5);
the fuel cooling jacket (3) and the oxidant cooling jacket (4) are arranged outside the combustion device (5), and the fuel cooling jacket (3) is positioned above the oxidant cooling jacket (4);
one end of the oxidant bypass passage (15) is communicated with the pipeline C (18), and the other end is communicated with the pipeline D (19); the oxidant regulating valve (6) is arranged on the oxidant bypass passage (15); the pipeline C (18) is a connecting pipeline between an outlet of the oxidant cooling jacket (4) and an inlet of the oxidant turbine (7), and the pipeline D (19) is a connecting pipeline between the oxidant turbine (7) and the oxidant main valve (10);
when the engine works, low-temperature fuel and low-temperature oxidant respectively flow into the fuel pump (1) and the oxidant pump (8) through the fuel inlet (13) and the oxidant inlet (9) under the pressure of the storage tank; the low-temperature fuel and the low-temperature oxidant respectively enter a fuel cooling jacket (3) and an oxidant cooling jacket (4) after being pressurized by a fuel pump (1) and an oxidant pump (8), heat exchange is carried out by means of the self heat sink of the fuel cooling jacket (3), the self heat sink of the oxidant cooling jacket (4) and the relative high temperature of the surrounding environment, and then the fuel enters a combustion device (5) after passing through a fuel turbine (2) and a fuel main valve (11), and the oxidant enters the combustion device (5) after passing through an oxidant turbine (7) and an oxidant main valve (10); the fuel and the oxidant are mixed, ignited and combusted in the combustion device (5); subsequently, the temperature of the combustion device (5) is gradually increased, the heat absorbed by the fuel and the oxidant in the fuel cooling jacket (3) and the oxidant cooling jacket (4) is gradually increased, the enthalpy value of the fuel and the oxidant at the outlet of the fuel cooling jacket (3) and the outlet of the oxidant cooling jacket (4) is also gradually increased, the power doing capability is enhanced until the fuel turbine (2) and the oxidant turbine (7) are driven to rotate, and then the fuel pump (1) and the oxidant pump (8) are driven by a shafting to boost the pressure of the fuel and the oxidant, so that the mass of the fuel and the oxidant entering the fuel cooling jacket (3) and the oxidant cooling jacket (4) in unit time is increased; so that the mass of fuel and oxidant entering the combustion device (5) in unit time is increased, and the heat released in the combustion process is further increased; under the dual actions of flow increase and heat flow increase, the medium driving the fuel turbine (2) and the oxidant turbine (7) is further enhanced in function, so that the pressurizing capacity of the fuel pump (1) and the oxidant pump (8) is further improved, forward feedback is formed, and finally, an equilibrium state, namely the main-stage working condition of the engine is achieved;
when the engine enters a main-stage working condition and the mixing ratio of the engine, namely the ratio of the oxidant flow to the fuel flow is required to be adjusted, the opening of the fuel control valve (12) is adjusted to increase or decrease the medium flow flowing through the fuel turbine (2) so as to adjust the ratio of the output power of the fuel turbine (2) to the output power of the oxidant turbine (7), and further the adjustment of the ratio of the oxidant flow to the fuel flow is realized;
when the engine enters a main working condition, and when the engine thrust adjustment needs to be carried out, the opening of the fuel control valve (12) is adjusted, and simultaneously the opening of the oxidant adjusting valve (6) is adjusted in cooperation with the opening change of the fuel control valve (12), so that the total power of the fuel turbine (2) and the oxidant turbine (7) is increased or reduced, and the engine thrust is changed.
2. A double expansion cycle liquid rocket engine system according to claim 1, wherein the fuel main valve (11) is used for adjusting the flow rate of fuel in the control pipeline.
3. A double expansion cycle liquid rocket engine system according to claim 1, wherein the oxidizer main valve (10) is used for adjusting the flow rate of the oxidizer in the control pipeline.
4. A dual expansion cycle liquid rocket engine system according to claim 1, wherein the fuel control valve (12) is adapted to regulate and control the flow of medium into the fuel turbine (2).
5. A double expansion cycle liquid rocket engine system according to claim 1, wherein the oxidizer regulating valve (6) is used for regulating and controlling the flow of medium into the oxidizer turbine (7).
6. A dual expansion cycle liquid rocket engine system as recited in claim 1, wherein the fuel is hydrogen or methane and the oxidizer is oxygen.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211706428.9A CN116044610B (en) | 2022-12-29 | 2022-12-29 | Double-expansion circulation liquid rocket engine system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211706428.9A CN116044610B (en) | 2022-12-29 | 2022-12-29 | Double-expansion circulation liquid rocket engine system |
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| CN116044610A CN116044610A (en) | 2023-05-02 |
| CN116044610B true CN116044610B (en) | 2024-04-09 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08338313A (en) * | 1995-06-09 | 1996-12-24 | Mitsubishi Heavy Ind Ltd | Liquid rocket engine |
| US8250853B1 (en) * | 2011-02-16 | 2012-08-28 | Florida Turbine Technologies, Inc. | Hybrid expander cycle rocket engine |
| CN111005821A (en) * | 2019-11-29 | 2020-04-14 | 北京航天动力研究所 | Expansion cycle liquid oxygen methane upper-level engine system |
| CN114060170A (en) * | 2021-10-22 | 2022-02-18 | 陕西天回航天技术有限公司 | Open type staged combustion air-extraction circulation liquid rocket engine |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2981127B1 (en) * | 2011-10-11 | 2013-11-29 | Snecma | REACTION PROPULSION DEVICE AND FEEDING METHOD |
| FR2991391B1 (en) * | 2012-05-30 | 2014-07-04 | Snecma | DEVICE AND METHOD FOR SUPPLYING A PROPULSIVE ENGINE CHAMBER |
-
2022
- 2022-12-29 CN CN202211706428.9A patent/CN116044610B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08338313A (en) * | 1995-06-09 | 1996-12-24 | Mitsubishi Heavy Ind Ltd | Liquid rocket engine |
| US8250853B1 (en) * | 2011-02-16 | 2012-08-28 | Florida Turbine Technologies, Inc. | Hybrid expander cycle rocket engine |
| CN111005821A (en) * | 2019-11-29 | 2020-04-14 | 北京航天动力研究所 | Expansion cycle liquid oxygen methane upper-level engine system |
| CN114060170A (en) * | 2021-10-22 | 2022-02-18 | 陕西天回航天技术有限公司 | Open type staged combustion air-extraction circulation liquid rocket engine |
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| CN116044610A (en) | 2023-05-02 |
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