CN111005821A - Expansion cycle liquid oxygen methane upper-level engine system - Google Patents
Expansion cycle liquid oxygen methane upper-level engine system Download PDFInfo
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- CN111005821A CN111005821A CN201911206747.1A CN201911206747A CN111005821A CN 111005821 A CN111005821 A CN 111005821A CN 201911206747 A CN201911206747 A CN 201911206747A CN 111005821 A CN111005821 A CN 111005821A
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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
- F02K9/425—Propellants
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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
- F02K9/56—Control
- F02K9/563—Control of propellant feed 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
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
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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
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
Abstract
An expansion cycle liquid oxymethane upper stage engine system includes a propellant supply system, an ignition system, and a thrust chamber. The propellant supply system comprises a methane supply system and a liquid oxygen supply system, wherein the methane supply system is used for pressurizing low-temperature liquid methane from an external storage tank and then supplying the low-temperature liquid methane to the thrust chamber; the liquid oxygen supply system is used for pressurizing low-temperature liquid oxygen from the external storage tank and then supplying the low-temperature liquid oxygen to the thrust chamber; the ignition system is positioned at the head of the thrust chamber, the ignition system ignites under the control of the control system, liquid oxygen and methane entering the thrust chamber are ignited, and the generated high-temperature fuel gas is sprayed out from a nozzle of the thrust chamber to generate thrust. The invention takes liquid oxygen and liquid methane as propellant combination, adopts a scheme of a closed expansion circulating system, has simple system, high inherent reliability and high specific impulse performance, and is easy to realize multiple starting.
Description
Technical Field
The invention relates to an expansion circulation liquid oxymethane upper-level engine system, and belongs to the technical field of liquid carrier rocket engines.
Background
The upper stage refers to a relatively independent stage or stages of rockets added above a base stage rocket or a reusable vehicle, the working section usually already enters the earth orbit, and one or more spacecrafts can be directly sent to a predetermined working orbit or a predetermined space position. The task mode of the upper stage is between the carrier and the spacecraft, and has the technical characteristics of the carrier and the spacecraft; the working time can reach hours, days or even months, and the spacecraft can experience a space environment similar to that of a spacecraft; the engine needs to be started for many times, the task modes are multiple, and the task adaptability is strong; compared with spacecrafts such as satellites, the upper-stage engine has high thrust and requires strong orbital maneuverability.
The upper stage can directly launch the spacecraft to be accurately in orbit or greatly save the orbital transfer time. The lunar and mars exploration tasks need to carry out a large amount of lunar orbit and lunar landing test verification work, and various spacecrafts such as stars and ships need to be directly sent into the lunar orbit, so that clear requirements are provided for the upper-level application. The deep space exploration task adopts the upper stage, so that the final stage in-orbit weight of the carrier rocket can be reduced, and the carrying capacity can be greatly improved after the deep space exploration task is combined with a large rocket.
The upper stage has the capacity of long-term on-orbit, multiple starting and multi-task adaptation, and is the best choice of a space test platform, and the combined platform of the base stage carrier rocket and the upper stage can provide a solution with relatively low cost for various space test and weapon platforms. Based on the multiple starting, space maneuvering and long-term on-orbit maintaining capability of the upper-level technology foundation, the task and the function of the device can be expanded in a special period, and the requirement of entering and controlling the space can be met.
The above stages require that their engines must have the following capabilities: specific impulse height; (II) multiple start capability; and (III) the space can be stored for a long time.
The liquid oxygen methane engine has the comprehensive advantages of both the hydrogen-oxygen engine and the liquid oxygen kerosene engine, and has the following technical advantages besides no toxicity and pollution: methane is suitable for an expansion cycle engine, can be started by itself, and is easy to realize multiple times of starting of the engine; methane and liquid oxygen have low boiling points and can be used for self-generation pressurization of the storage tank, so that a rocket and an upper-stage pressurization conveying system are simplified; and (III) the performance is higher, methane is the highest-performance hydrocarbon fuel, and the specific impulse performance is second to that of liquid hydrogen. The liquid oxygen methane propellant combination theory specific impulse is only lower than that of the hydrogen and oxygen combination and higher than that of the liquid oxygen kerosene combination. The density specific impulse of the liquid oxygen methane propellant combination is lower than that of the liquid oxygen kerosene combination and higher than that of the hydrogen-oxygen combination. The liquid oxygen methane propellant combination has higher performance. And (IV) the use and maintenance are convenient, and the maintenance and use conditions of the methane are basically the same as those of the liquid oxygen. The coking temperature of the methane is 950K, which is 389K higher than that of the kerosene, and the methane serving as a regenerative coolant of the existing structural material is superior to that of the kerosene and is not coked. Hydrocarbon fuel gas generally has a tendency to deposit carbon, but methane deposits less. The boiling points of methane and liquid oxygen are respectively 112K and 90K, so that the methane and the liquid oxygen are easy to evaporate, only relatively simple blowing treatment is needed after test run, and complicated post-treatment procedures are not needed. The engine can be repeatedly used and tested by one machine. And (V) the cost is low, the methane source is wide, and the price is low. The source of the methane is wide, the methane content of the Liquefied Natural Gas (LNG) reaches more than 99 percent, the liquefied natural gas can be directly used as a propellant, and the use maintainability and the safety are better. Liquid methane is derived from Liquefied Natural Gas (LNG) and solid natural gas hydrates (combustible ice). Natural gas hydrate resources almost pure methane widely exist on the earth, and the estimated resource amount is 2 multiplied by 1013A ton oil equivalent, more than 2 times the current reserves of conventional fossil fuels on earth. Furthermore, methane pushThe cost of liquid methane is about 1/60 of liquid hydrogen and 1/3 of kerosene. And (VI) the space can be used for storing, and liquid oxygen and methane belong to the space can be used for storing the propellant. The boiling points of methane and liquid oxygen are respectively 112K and 90K, the temperature is close to the space temperature, the propellant can be stored in the space, and the long-term storage of the propellant in the space can be realized more easily. The using and maintaining temperatures of the methane propellant and the liquid oxygen propellant are equivalent, a common-bottom storage tank can be adopted, special heat insulation measures are not needed between the storage tanks, and the structural design of the storage tank can be effectively simplified.
After the cold war, particularly since the 20 th century, the liquid rocket engine is mainly developed due to no toxicity, no pollution, high performance and low price, and the development trend of aerospace power puts higher requirements on safety, use maintainability, economy and adaptability of a power system to multiple tasks in the future. The liquid oxygen methane engine has the advantages of space storage, higher performance, easy repeated starting and reuse, convenient use and maintenance, good economy, no toxicity, no pollution and the like, and is one of the development directions of future aerospace power. The research on liquid oxymethane engine technology has been conducted in countries such as the united states, russia, europe, japan, and korea, but has not yet achieved a real engineering application. The following are more typical: (1) in 2004, Puhui of the United states of America carries out the research on a system scheme of changing an RL10 engine into a liquid oxygen methane expansion cycle engine, the engine adopts a pump pressure type expansion cycle system scheme, the vacuum thrust is 97.86kN, the vacuum specific impulse is 353.2s, and the pressure of a thrust chamber is 3.45 MP. (2) The Russian chemical Automation design office (KBKhA) changed various existing engines into liquid oxygen methane engines and conducted hot test studies. In 1998, the RD-0110 liquid oxygen kerosene fuel gas generator circulating engine is transformed into a liquid oxygen methane engine with the code of RD-0110M, the system hot test is carried out, and the engine thrust is 245 kN; the RD-0146D oxyhydrogen expansion cycle engine is transformed by KBKHA in 2013 and then subjected to a 6-time liquid oxygen methane engine test, and the total working time is about 200 seconds; in 2005, Russian chemical mechanical design agency (KBKM) cooperated with Europe to transform the oxyhydrogen rich afterburning cycle engine 11D56 into a KVD-1 engine for the first liquid oxygen methane hot test. (3) In 8 months in 2019, flight tests are successfully carried out by a full-flow liquid oxygen methane afterburning cycle engine Raptor carrying a Starhopper prototype of the Raptor of SpaceX company, and the thrust of the Raptor engine is 3000kN, the room pressure is 30MPa, and the engine basically has engineering application conditions.
The liquid oxymethane rocket engines in China are still in a research and development stage, and the research on pumping pressure closed expansion cycle engines in a liquid oxymethane propellant combination mode is not developed at all before, so that the liquid oxymethane rocket engines are in a technical blank for a long time, and related research work needs to be developed to narrow the technical gap with foreign countries.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the defects of the prior art are overcome, and the expansion cycle liquid oxymethane upper-level engine system is provided.
The technical solution of the invention is as follows:
an expansion cycle liquid oxymethane upper stage engine system comprises a propellant supply system, an ignition system and a thrust chamber;
the propellant supply system comprises a methane supply system and a liquid oxygen supply system; the methane supply system is used for pressurizing low-temperature liquid methane from an external liquid methane storage tank and then supplying the low-temperature liquid methane to the thrust chamber; the liquid oxygen supply system is used for pressurizing low-temperature liquid oxygen from an external liquid oxygen storage tank and then supplying the low-temperature liquid oxygen to the thrust chamber; the ignition system is positioned at the head of the thrust chamber, the ignition system ignites under the control of the control system, liquid oxygen and methane entering the thrust chamber are ignited, and the generated high-temperature fuel gas is sprayed out from a nozzle of the thrust chamber to generate thrust.
The propellant supply system comprises a methane main valve, an oxygen main valve, a methane turbine pump, an oxygen turbine pump, a methane pump front valve, an oxygen discharge valve and a methane discharge valve;
a pump front pipeline of the methane turbopump is connected with an external liquid methane storage tank through a methane pump front valve, and a pump rear pipeline is connected with an inlet of a cooling jacket of the thrust chamber; a turbine inlet of the methane turbine pump is connected with an outlet of the cooling jacket of the thrust chamber, a turbine outlet of the methane turbine pump is connected with a turbine inlet of the oxygen turbine pump, and a turbine outlet of the oxygen turbine pump is connected with a methane head cavity of the thrust chamber through a methane main valve; a pump front end pipeline of the oxygen turbine pump is connected with an external liquid oxygen storage tank through an oxygen pump front valve, and a pump rear pipeline is connected with an oxygen head cavity of the thrust chamber through an oxygen main valve;
a methane discharge valve is arranged on a pipeline behind a pump of the methane turbopump and is used for discharging liquid methane before the engine is started and after the engine is shut down; an oxygen discharge valve is arranged on a pump rear pipeline of the oxygen turbine pump and is used for discharging liquid oxygen before the engine is started and after the engine is shut down.
The propellant supply system also comprises a first orifice plate and a second orifice plate, wherein the first orifice plate is arranged on a pump rear pipeline of the oxygen turbine pump and is used for regulating the flow of the oxygen path; the second pore plate is arranged on a pipeline behind a pump of the methane turbopump and used for adjusting the flow of the methane pipeline.
A first sonic nozzle is arranged on a turbine bypass of the methane turbopump and used for adjusting the flow entering a turbine of the methane turbopump.
And a second sonic nozzle is arranged on a turbine bypass of the oxygen turbine pump and used for regulating the flow entering the turbine of the oxygen turbine pump.
The ignition system comprises a torch igniter, an oxygen cylinder and a methane cylinder;
the methane gas bottle is connected with the methane cavity collector of the torch igniter through a methane pipeline, and the methane pipeline is provided with a methane ignition valve; the head of the torch igniter is provided with a spark plug for ignition, and the spark plug is controlled by an electric switch to realize ignition of an ignition medium.
The upper-level engine system further comprises an oxygen channel blowing system and a methane channel blowing system, when the engine is shut down, the oxygen channel blowing system is used for blowing residual oxygen in the propellant supply system and the thrust chamber, and the methane channel blowing system is used for blowing residual methane in the propellant supply system and the thrust chamber.
An implementation method of an expansion cycle liquid oxymethane upper-level engine system comprises the following steps:
(1) in the precooling starting stage of the engine, liquid methane is filled in front of a methane main valve, and a liquid methane vaporization product is discharged through a methane discharge valve; in the cavity from the pipeline behind the methane turbopump to the methane main valve, liquid methane exchanges heat with the system pipeline and the thrust chamber cooling jacket to reach a certain balance temperature to provide certain initial enthalpy for the working medium of the starting turbine, and meanwhile, liquid oxygen is filled in front of the oxygen main valve, and a liquid oxygen vaporization product is discharged through an oxygen discharge valve; when the engine meets the conditions of precooling starting temperature and pressure, closing the methane discharge valve and the oxygen discharge valve; the torch igniter is ignited, the methane main valve and the oxygen main valve are opened, gas methane with certain enthalpy entering the thrust chamber and liquid oxygen entering the thrust chamber are ignited under the pressure of the storage tank, low-pressure and low-mixture-ratio combustion is carried out, the formed high-temperature gas enables the temperature of the methane in the cooling jacket of the thrust chamber to rise in an accelerated mode, further the energy of the turbines of the methane turbine pump and the oxygen turbine pump is increased, the turbines are started and accelerated, a starting acceleration process is carried out for a period of time, and the engine is switched to a main-stage working condition.
(2) Under the working condition of the main stage, methane in the thrust chamber enters the cooling jacket from the cooling body inlet collector, cools the body of the thrust chamber, absorbs heat simultaneously to become gas methane, and flows out from the body outlet collector to be used as a working medium for driving a methane turbopump and an oxygen turbopump; gaseous methane sequentially flows through a turbine of the methane turbopump and a turbine of the oxygen turbopump, and converges into a methane head cavity of the thrust chamber, and the gaseous methane is subjected to uniform flow distribution and then enters the combustion chamber through a methane nozzle of the injector of the thrust chamber; meanwhile, liquid oxygen is pressurized by an oxygen turbine pump, enters a liquid oxygen head cavity of the thrust chamber, is subjected to uniform flow distribution and then enters the combustion chamber through a liquid oxygen nozzle of an injector of the thrust chamber; the gas methane and the liquid oxygen are fully mixed in the combustion chamber, and after being ignited by the torch igniter, high-temperature gas is generated and is fully expanded by the combustion chamber and the extension section of the spray pipe and then is sprayed out at a high speed.
(3) When the engine receives a shutdown instruction, firstly opening the methane discharge valve to reduce the working condition of the engine, then closing the methane main valve, rapidly reducing the rotating speed after the turbines of the methane turbine pump and the oxygen turbine pump lose driving energy, then opening the oxygen discharge valve to discharge liquid oxygen in a pipeline, and then closing the oxygen main valve; when the methane main valve and the oxygen main valve are closed, the methane path and the oxygen path blowing system of the thrust chamber are respectively opened, so that the propellant is discharged from the thrust chamber as soon as possible, and the engine is shut down in a program mode.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention adopts liquid oxygen and liquid methane as propellant combination, and the liquid oxygen methane combination has the comprehensive advantages of hydrogen, oxygen and liquid oxygen kerosene: 1) the environment is green and pollution-free, and liquid oxygen, methane and combustion products of the liquid oxygen and the methane are nontoxic and pollution-free; 2) the performance is higher, the theoretical specific impulse of the liquid oxygen methane propellant combination is only lower than that of an oxyhydrogen combination and higher than that of a liquid oxygen kerosene combination, and the density specific impulse of the liquid oxygen methane propellant combination is lower than that of the liquid oxygen kerosene combination and higher than that of the oxyhydrogen combination; 3) the space can be stored, the boiling points of methane and liquid oxygen are respectively 112K and 90K, the temperature is close to the space temperature, the propellant can be stored in the space, and the long-term storage of the propellant in the space can be realized more easily; 4) the use and maintenance are convenient, and the use and maintenance conditions of the methane are basically the same as those of the liquid oxygen. The coking temperature of the methane is 950K, which is 389K higher than that of the kerosene, and the methane is difficult to coke when being used as a regenerative coolant compared with the kerosene and has less carbon deposition when being used as a propellant compared with the kerosene for combustion. The boiling points of methane and liquid oxygen are low, the methane and the liquid oxygen are easy to evaporate, only relatively simple blowing treatment is needed after test run, complex post-treatment procedures are not needed, and the engine can be repeatedly used and can be tested by one machine. 5) The source is wide, the liquid methane mainly comes from Liquefied Natural Gas (LNG) and solid natural gas hydrate (combustible ice) at present, natural gas hydrate resources which are almost pure methane widely exist on the earth, and the estimated resource amount is 2 multiplied by 1013A ton oil equivalent which is more than 2 times of the conventional fossil fuel reserves on the earth at present; 6) the cost is low, the methane propellant is good in economy, and the cost of liquid methane is 1/60 of liquid hydrogen and 1/3 of kerosene. The content of methane in the liquefied natural gas reaches more than 99 percent, and the liquefied natural gas can be directly used.
(2) The invention adopts the scheme of the closed expansion circulation system, has simple system, high inherent reliability and high specific impulse performance, and is easy to realize multiple starting. The gas methane provided by the regenerative cooling jacket is used as a turbine working medium, the engine system can realize multiple self-starting of the engine without arranging an independent starting system, and the system has simple principle and high inherent reliability. The gas methane drives the turbine and then completely enters the thrust chamber combustion chamber to be fully mixed with the liquid oxygen for combustion, the propellant or the product thereof is not discharged or wasted in the intermediate process, the energy is fully utilized, the system performance loss is avoided, and the theoretical specific impulse is highest. The specific impulse loss can be reduced by about 11s (30%) using the expansion cycle scheme relative to the gasifier cycle scheme.
(3) The invention adopts a pump pressure type system scheme, and has simple system and small structural mass. Compared with an extrusion type system, the scheme of the pumping pressure type system does not need to be provided with a high-pressure propellant storage tank, an auxiliary pressurized gas cylinder or a high-pressure heat exchanger and other pressurization conveying systems, and is an optimal scheme for a system with a large propellant consumption when an engine works for a long time.
(4) The turbopump adopts a liquid oxygen and methane double-turbine pump scheme, so that the problem that a heavy gear box is used for the high rotating speed of the methane pump due to the adoption of a coaxial single-turbine pump scheme is avoided.
(5) The system can realize self-starting and repeated starting, has low methane boiling point, high heat capacity and good cooling performance, is easy to evaporate, is used as a regenerative coolant to change into gas after absorbing heat, is suitable for an expansion cycle engine, can effectively simplify the structure of the engine system, improves the reliability, starts the engine per se, and is easy to realize repeated starting of the engine.
(6) The system can realize self-generation pressurization, the engine can lead high-pressure methane out of the outlet of the regeneration cooling jacket, and the external liquid methane storage tank is pressurized after temperature and pressure are adjusted; high-pressure liquid oxygen is led out from the liquid oxygen pump, the liquid oxygen is gasified through the evaporator, and the external liquid oxygen storage tank is pressurized after the pressure is regulated. The propellant storage tank is pressurized automatically, so that the rocket and the upper-level pressurizing conveying system can be greatly simplified.
(7) The system can realize the work of a tank pressure idle mode and a pump idle mode, and the self-starting and the self-generating pressurization of the engine are combined, so that the liquid oxygen methane engine capable of working in the idle mode can be derived. Except for a main-stage working mode, the engine can work in a tank pressure no-load (1-1.5% rated thrust) mode and a pump no-load (5-25% rated thrust) mode, the storage tank propellant bottom sinking and engine low-working-condition working are achieved, a top-stage storage tank bottom sinking rocket system can be simplified, the structure weight is reduced, and the task carrying capacity is improved.
Drawings
FIG. 1 is a schematic view of the present invention.
Detailed Description
The invention provides a pumping pressure closed type expansion cycle upper-stage engine system which mainly comprises a propellant supply system, an ignition system and a thrust chamber 1. The propellant supply system comprises a methane supply system and a liquid oxygen supply system; the methane supply system is used for pressurizing low-temperature liquid methane from an external storage tank and then supplying the low-temperature liquid methane to the thrust chamber 1; the liquid oxygen supply system is used for pressurizing low-temperature liquid oxygen from an external storage tank and then supplying the low-temperature liquid oxygen to the thrust chamber 1; the ignition system is positioned at the head of the thrust chamber 1, and is ignited under the control of the control system to ignite the liquid oxygen and methane entering the thrust chamber 1, and the generated high-temperature fuel gas is sprayed out from a nozzle of the thrust chamber to generate thrust.
The thrust chamber 1 mainly comprises a methane head cavity, a liquid oxygen head cavity, an injector and a thrust chamber body (combustion chamber); meanwhile, the body inlet collector, the outlet collector and the thrust chamber body (combustion chamber) jointly form a cooling jacket; the liquid oxygen turbine pump and the methane turbine pump adopt basically the same scheme and mainly comprise a turbine, a pump and a shaft system.
As shown in fig. 1, the propellant supply system includes a methane main valve 2, an oxygen main valve 3, a methane turbo pump 4, an oxygen turbo pump 5, a methane pump pre-valve 6, an oxygen pump pre-valve 7, an oxygen bleed-out valve 11, and a methane bleed-out valve 12; a pump front pipeline of the methane turbopump 4 is connected with an external liquid methane storage tank through a methane pump front valve 6, and a pump rear pipeline is connected with an inlet of a thrust chamber cooling jacket; a turbine inlet of the methane turbine pump 4 is connected with an outlet of a cooling jacket of the thrust chamber, a turbine outlet of the methane turbine pump 4 is connected with a turbine inlet of the oxygen turbine pump 5, and a turbine outlet of the oxygen turbine pump 5 is connected with a methane head cavity of the thrust chamber through a methane main valve 2; the front end pipeline of the oxygen turbine pump 5 is connected with an external liquid oxygen storage tank through a front oxygen pump valve 7, and the rear end pipeline of the pump is connected with an oxygen head cavity of the thrust chamber through an oxygen main valve 3. A methane discharge valve 12 is arranged on a pipeline behind the methane turbopump 4 and is used for discharging liquid methane before the engine is started and after the engine is shut down; an oxygen discharge valve 11 is provided on the pump rear pipe of the oxygen turbo pump 5 for discharging liquid oxygen before the engine is started and after the engine is shut down.
The propellant supply system also comprises a first orifice plate 13 and a second orifice plate 14, wherein the first orifice plate 13 is arranged on a post-pump pipeline of the oxygen turbine pump 5 and used for regulating the flow of the oxygen path; the second orifice plate 14 is installed on the pump rear pipeline of the methane turbopump 4 and used for adjusting the flow rate of the methane pipeline. The first orifice plate 13 and the second orifice plate 14 can accurately control the flow of overflowing water so as to realize the control of the mixing ratio of the engine.
A first sonic nozzle 8 is arranged on a turbine bypass of the methane turbopump 4 and used for adjusting the flow entering the turbine of the methane turbopump 4. A second sonic nozzle 9 is provided on the turbine bypass of the turbo pump 5 for regulating the flow into the turbine of the turbo pump 5. The sonic nozzle can accurately control the flow of the turbine working medium so as to realize the thrust control of the engine.
The ignition system comprises a torch igniter 10, an oxygen cylinder and a methane cylinder; the oxygen cylinder is connected with an oxygen cavity collector of the torch igniter 10 through an oxygen pipeline, an oxygen ignition valve is arranged on the oxygen pipeline, the methane gas cylinder is connected with a methane cavity collector of the torch igniter 10 through a methane pipeline, and a methane ignition valve is arranged on the methane pipeline; the head of the torch igniter 10 is provided with a semiconductor spark plug for ignition, with ignition energy provided by a separate set of power supply and distribution energizing devices. The semiconductor spark plug is controlled by an electric switch to realize the ignition of the ignition medium.
The upper-level engine system further comprises an oxygen channel blowing system and a methane channel blowing system, when the engine is shut down, the oxygen channel blowing system is used for blowing residual oxygen in the thrust chamber, and the methane channel blowing system is used for blowing residual methane in the thrust chamber.
The engine propellant is in a self-generating pressurization mode. The pressurized gas of the external liquid oxygen storage tank is oxygen. High-pressure liquid oxygen is led out from a liquid oxygen pump of the engine, the liquid oxygen is gasified through an evaporator positioned behind a turbine, and the liquid oxygen is led into an external liquid oxygen storage tank for pressurization after pressure regulation. The pressurized gas of the external liquid methane storage tank is methane. High-pressure gas methane is led out from an outlet of the oxygen turbine, is mixed with a small strand of liquid methane led out after a methane pump, is decompressed and is led into an external methane storage tank for pressurization.
The invention is realized as follows:
(1) the engine is soaked and precooled by methane and liquid oxygen before ignition so as to save the propellant. And (4) carrying out discharge precooling before ignition starting, and precooling to the starting condition of the engine.
In the precooling starting stage of the engine, liquid methane is filled in front of the methane main valve 2, and liquid methane vaporization products are discharged through the methane discharge valve 12; in the methane turbopump 4, a pipeline is arranged behind the pump to reach the containing cavity of the methane main valve 2, liquid methane exchanges heat with a system pipeline and a cooling jacket of the thrust chamber 1 to reach a certain balance temperature, certain initial enthalpy is provided for a working medium for starting a turbine, meanwhile, liquid oxygen is filled in front of the oxygen main valve 3, and a liquid oxygen vaporization product is discharged through an oxygen discharge valve 11; when the engine meets the conditions of precooling starting temperature and pressure, closing the methane discharge valve 12 and the oxygen discharge valve 11; the torch igniter 10 is ignited, the methane main valve 2 and the oxygen main valve 3 are opened, gas methane with certain enthalpy entering the thrust chamber 1 and liquid oxygen entering the thrust chamber 1 are ignited under the pressure of the storage tank, low-pressure and low-mixing-ratio combustion is carried out, the temperature of a cooling jacket of the thrust chamber 1 is increased by gas, the energy of a methane turbine pump and an oxygen turbine pump driven by the gas methane is increased, the turbine is started and accelerated, a starting and accelerating process is carried out for a period of time, and the engine is switched to a main-stage working condition.
(2) As shown in fig. 1, under the main-stage working condition, methane in the thrust chamber 1 enters a regenerative cooling jacket from a regenerative cooling body inlet collector, cools the body of the thrust chamber, absorbs heat to become gas methane, and flows out from a body outlet collector to be used as a working medium for driving a methane turbopump and an oxygen turbopump; gaseous methane sequentially flows through a turbine of the methane turbopump 4 and a turbine of the oxygen turbopump 5 and is converged into a methane head cavity of the thrust chamber 1, and is sprayed out through a methane nozzle of a thrust chamber injector after uniform distribution and finally enters a combustion chamber; meanwhile, liquid oxygen is pressurized by an oxygen turbine pump, enters a liquid oxygen head cavity of the thrust chamber 1, is sprayed out through a liquid oxygen nozzle of a thrust chamber injector after being distributed in a uniform flow manner, and enters a combustion chamber; the gas methane and the liquid oxygen are fully mixed in the combustion chamber, and after being ignited by the torch igniter, high-temperature gas is generated and is fully expanded by the combustion chamber and the extension section of the spray pipe and then is sprayed out at a high speed.
(3) As shown in fig. 1, after the engine receives a shutdown command, the methane bleed-off valve 12 is opened to reduce the engine operating condition, then the methane main valve 2 is closed, the turbine of the methane turbine pump and the turbine of the oxygen turbine pump lose the driving energy and then the rotating speed is rapidly reduced, then the oxygen bleed-off valve 11 is opened to bleed off the liquid oxygen in the pipeline, and then the oxygen main valve 3 is closed; when the methane main valve 2 and the oxygen main valve 3 are closed, the methane path and the oxygen path blowing system of the thrust chamber are respectively opened, so that the propellant is discharged from the thrust chamber as soon as possible, and the engine is shut down in a program mode.
When the engine works under the main working condition: in the thrust chamber, liquid methane reversely flows into an inlet collector at the body part of the thrust chamber and then enters a cooling jacket to cool and protect the body part (combustion chamber) of the thrust chamber so as to prevent the body part from being ablated; meanwhile, liquid methane absorbs heat transferred from the combustion chamber in the regeneration cooling channel to obtain an enthalpy value, and the liquid methane is converted into gaseous methane; the gas methane is converged and flows out from the thrust chamber body outlet collector.
After flowing out of the thrust chamber body collector, the gas methane flows through the methane turbopump and the liquid oxygen turbopump in sequence. In the turbine pump, the gas methane drives the turbine to rotate at high speed, and then flows out from the outlet of the turbine. Due to the coaxial relationship, the turbine also drives the pump to rotate at high speed, so that the liquid oxygen and the liquid methane obtain high pressure at the outlet of the pump. After the work of the turbine is finished, the gas methane flows out from the outlet of the turbine, enters a methane head cavity of the thrust chamber, enters the combustion chamber through a methane nozzle of the injector, is fully mixed and combusted with the atomized liquid oxygen sprayed from the liquid oxygen nozzle, high-temperature gas generated by combustion is sprayed backwards at a high speed through expansion and expansion of the combustion chamber, and the engine generates thrust.
The liquid oxygen and methane supply system is provided with adjusting elements such as a sonic nozzle, an orifice plate and the like, and all the adjusting elements are mutually independent and respectively adjusted. The regulating element is used for effectively compensating the pressure loss of the propellant or the fuel gas and regulating and controlling the flow of the two paths of propellants.
The methane pump front valve 6 and the oxygen pump front valve 7 are ball valves, the methane main valve 2, the oxygen main valve 3, the methane discharge valve 12 and the oxygen discharge valve 11 are all bacteria valves, and the methane pump front valve 6, the oxygen pump front valve 7, the methane main valve 2, the oxygen main valve 3, the methane discharge valve 12 and the oxygen discharge valve 11 adopt a pneumatic control scheme and are controlled by a control electromagnetic valve.
The engine adopts a closed circulation system, namely, in the whole working process, all the propellants are fully combusted and sprayed out through the thrust chamber, so that low-efficiency discharge and waste are avoided, and energy is fully utilized. Therefore, the theoretical specific impulse performance of the engine in the principle scheme of the system is the highest under the same other conditions.
Claims (8)
1. An expansion cycle liquid oxymethane upper engine system, which is characterized in that: comprising a propellant supply system, an ignition system and a thrust chamber (1);
the propellant supply system comprises a methane supply system and a liquid oxygen supply system; the methane supply system is used for pressurizing low-temperature liquid methane from an external liquid methane storage tank and then supplying the low-temperature liquid methane to the thrust chamber (1); the liquid oxygen supply system is used for pressurizing low-temperature liquid oxygen from an external liquid oxygen storage tank and then supplying the low-temperature liquid oxygen to the thrust chamber (1); the ignition system is positioned at the head of the thrust chamber (1), and is used for igniting under the control of the control system, igniting the liquid oxygen and methane entering the thrust chamber (1), and spraying the generated high-temperature fuel gas from a nozzle of the thrust chamber to generate thrust.
2. The expansion cycle liquid oxymethane upper stage engine system according to claim 1, wherein: the propellant supply system comprises a methane main valve (2), an oxygen main valve (3), a methane turbopump (4), an oxygen turbopump (5), a methane pump front valve (6), an oxygen pump front valve (7), an oxygen discharge valve (11) and a methane discharge valve (12);
a pump front pipeline of the methane turbopump (4) is connected with an external liquid methane storage tank through a methane pump front valve (6), and a pump rear pipeline is connected with an inlet of a thrust chamber cooling jacket; a turbine inlet of the methane turbine pump (4) is connected with an outlet of a cooling jacket of the thrust chamber, a turbine outlet of the methane turbine pump (4) is connected with a turbine inlet of the oxygen turbine pump (5), and a turbine outlet of the oxygen turbine pump (5) is connected with a methane head cavity of the thrust chamber through a methane main valve (2); a pump front end pipeline of the oxygen turbine pump (5) is connected with an external liquid oxygen storage tank through an oxygen pump front valve (7), and a pump rear pipeline is connected with a thrust chamber oxygen head cavity through an oxygen main valve (3);
a methane discharge valve (12) is arranged on a pipeline behind a methane turbopump (4) and is used for discharging liquid methane before the engine is started and after the engine is shut down; an oxygen discharge valve (11) is arranged on a pump rear pipeline of the oxygen turbine pump (5) and is used for discharging liquid oxygen before the engine is started and after the engine is shut down.
3. An expansion cycle liquid oxymethane topping engine system as claimed in claim 2 wherein: the propellant supply system also comprises a first orifice plate (13) and a second orifice plate (14), wherein the first orifice plate (13) is arranged on a post-pump pipeline of the oxygen turbine pump (5) and used for regulating the flow of the oxygen path; the second pore plate (14) is arranged on a pump rear pipeline of the methane turbopump (4) and used for adjusting the flow of the methane pipeline.
4. An expansion cycle liquid oxymethane topping engine system as claimed in claim 2 wherein: a first sonic nozzle (8) is arranged on a turbine bypass of the methane turbopump (4) and used for adjusting the flow entering a turbine of the methane turbopump (4).
5. An expansion cycle liquid oxymethane topping engine system as claimed in claim 2 wherein: and a second sonic nozzle (9) is arranged on a turbine bypass of the oxygen turbine pump (5) and used for regulating the flow entering the turbine of the oxygen turbine pump (5).
6. The expansion cycle liquid oxymethane upper stage engine system according to claim 1, wherein: the ignition system comprises a torch igniter (10), an oxygen cylinder and a methane cylinder;
the oxygen cylinder is connected with an oxygen cavity collector of the torch igniter (10) through an oxygen pipeline, an oxygen ignition valve is arranged on the oxygen pipeline, the methane gas cylinder is connected with a methane cavity collector of the torch igniter (10) through a methane pipeline, and a methane ignition valve is arranged on the methane pipeline; the head of the torch igniter (10) is provided with a spark plug for ignition, and the spark plug is controlled by an electric switch to realize ignition of an ignition medium.
7. The expansion cycle liquid oxymethane upper stage engine system according to claim 1, wherein: the upper-level engine system further comprises an oxygen channel blowing system and a methane channel blowing system, when the engine is shut down, the oxygen channel blowing system is used for blowing residual oxygen in the propellant supply system and the thrust chamber, and the methane channel blowing system is used for blowing residual methane in the propellant supply system and the thrust chamber.
8. An implementation method of an expansion cycle liquid oxymethane upper-level engine system is characterized by comprising the following steps:
(1) in the precooling starting stage of the engine, liquid methane is filled to the front of a methane main valve (2), and a liquid methane vaporization product is discharged through a methane discharge valve (12); in a cavity from a pump back pipeline of a methane turbine pump (4) to a methane main valve (2), liquid methane exchanges heat with a system pipeline and a cooling jacket of a thrust chamber (1) to reach a certain balance temperature, certain initial enthalpy is provided for a working medium of a starting turbine, and meanwhile, a liquid oxygen vaporization product is discharged through an oxygen discharge valve (11) before liquid oxygen is filled to an oxygen main valve (3); when the engine meets the conditions of precooling starting temperature and pressure, closing the methane discharge valve (12) and the oxygen discharge valve (11); the flare igniter (10) is ignited, the methane main valve (2) and the oxygen main valve (3) are opened, gas methane with certain enthalpy entering the thrust chamber (1) and liquid oxygen entering the thrust chamber (1) are ignited under the pressure of the storage tank, low-pressure and low-mixing ratio combustion is carried out, the formed high-temperature gas accelerates the temperature of methane in a cooling jacket of the thrust chamber (1) to rise, the energy of turbines of the methane turbine pump and the oxygen turbine pump is further increased, the turbines are accelerated to start, a starting acceleration process is carried out after a period of time, and the engine is switched to a main-stage working condition.
(2) Under the working condition of the main stage, methane in the thrust chamber (1) enters a cooling jacket from a cooling body inlet collector, cools the body of the thrust chamber, absorbs heat simultaneously to be changed into gas methane, and flows out from a body outlet collector to be used as a working medium for driving a methane turbine pump and an oxygen turbine pump; gaseous methane sequentially flows through a turbine of the methane turbopump (4) and a turbine of the oxygen turbopump (5) and is converged into a methane head cavity of the thrust chamber (1), and after uniform flow distribution, the gaseous methane enters a combustion chamber through a methane nozzle of a thrust chamber injector; meanwhile, liquid oxygen is pressurized by an oxygen turbine pump, enters a liquid oxygen head cavity of the thrust chamber (1), is subjected to uniform flow distribution and then enters the combustion chamber through a liquid oxygen nozzle of an injector of the thrust chamber; the gas methane and the liquid oxygen are fully mixed in the combustion chamber, and after being ignited by the torch igniter, high-temperature gas is generated and is fully expanded by the combustion chamber and the extension section of the spray pipe and then is sprayed out at a high speed.
(3) When the engine receives a shutdown instruction, firstly opening a methane discharge valve (12) to reduce the working condition of the engine, then closing a methane main valve (2), rapidly reducing the rotating speed after the turbines of the methane turbine pump and the oxygen turbine pump lose driving energy, then opening an oxygen discharge valve (11), discharging liquid oxygen in a pipeline, and then closing an oxygen main valve (3); when the methane main valve (2) and the oxygen main valve (3) are closed, the methane path and the oxygen path blowing system of the thrust chamber are respectively opened, so that the propellant is discharged from the thrust chamber as soon as possible, and the engine is shut down in a program mode.
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