Rd 191 and 180 comparison. © State Corporation for Space Activities Roscosmos. Some characteristics of the rocket engine
JSC "NPO Energomash"
141400, Russia, Khimki, Moscow region, Burdenko st., 1
open joint-stock company"NPO Energomash named after Academician V.P. Glushko" is the world's leading enterprise in the development of powerful liquid-propellant rocket engines for space launch vehicles. The company was founded on May 15, 1929. NPO Energomash developed about 60 LREs, which were mass-produced and operated and continue to be operated as part of space and combat launch vehicles.
Currently, the main programs of the enterprise are:
- Serial production of modernized RD-171M liquid-propellant rocket engines for the first stage of the Zenit launch vehicle (Sea Launch, Land Launch programs, Federal Space Program)
- Serial production of the RD-180 rocket engine for the first stages of the American Atlas 5 launch vehicle
- Development of the RD-191 rocket engine for the first stages of the new Russian Angara launch vehicle family
- Modernization and architectural supervision of serial production of the RD-107 and RD-108 (14D22 and 14D21) LRE family for the first and second stages of the Soyuz launch vehicle in Samara
- Modernization and architectural supervision of the serial production of the upgraded RD-253 (14D14M) liquid-propellant rocket engine for the first stage of the Proton launch vehicle in Perm
- Modernization and architectural supervision of the RD-120 LPRE for the second stage of the Zenit launch vehicle (Sea Launch, Land Launch, Federal Space Program)
In addition, the company is working on promising areas improvement of LRE:
- Research of the concept of reusable rocket engines
- Study of the concept of liquid-propellant rocket engines with a closed-loop turbine drive
- Design work on engines for a spacecraft using solar energy
- Improving the reliability of LRE
- Research in the field of the use of liquefied natural gas (methane) as a fuel in LRE
- Project of a three-component dual-mode rocket engine (oxygen-kerosene-hydrogen)
- Studies of stress-strain states of components and assemblies of rocket engines
Accumulated by NPO Energomash vast experience in the creation of LRE, ownership unique technologies provides a favorable basis for cooperation with various aerospace organizations and companies around the world.
NPO Energomash is ready to develop a liquid-propellant rocket engine in accordance with technical requirements customer in as soon as possible and at the highest scientific and technical level.
The development of the RD-170 and RD-171 engines for the first stages of the Energia and Zenit launch vehicles, respectively, began in 1976. Their development has become a qualitatively new step in the creation of LRE. The most powerful four-chamber LRE in the world has the highest level of parameters and characteristics for engines of this class, it runs on environmentally friendly fuel components: liquid oxygen and kerosene. The engine for the Energia launch vehicle is designed for reusable use and is certified for 10-fold use. One of the engine specimens was tested on a firing stand up to 20 times. The engine is characterized by high reliability of operation, maintainability and testability and has large stock by resource (at least 5). The thrust vector control of the engine is carried out due to the creation of a unique bellows chamber swing assembly operating in the high-temperature gas flow zone. The engines passed about 900 fire tests with a total operating time of over 100,000 seconds.
The first launch of the Zenit launch vehicle with the RD-171 engine was carried out in April 1985. In 1987 and 1988, the launches of the Energia launch vehicle with the RD-170 engines took place. Since 1999, the operation of RD-171 engines has continued as part of the Zenit 3 SL launch vehicle under the Sea Launch program.
Main parameters of the RD-170/171 engine family
Fuel - oxygen + kerosene
|
Engine modifications |
RD -170 |
RD-171 |
RD-171M |
| Thrust, ground / hollow, tf | 740 / 806 | 740 / 806 | 740 / 806 |
| Specific impulse, terrestrial / void, sec | 309 / 337 | 309 / 337 | 309 / 337 |
| Pressure in the combustion chamber, kgf / cm 2 | 250 | 250 | 250 |
| Weight, dry / flooded, kg | 9750 / 10750 | 9500 / 10500 | 9300 / 10300 |
| Dimensions, height / diameter, mm | 4000 / 3800 | 4150 / 3565 | 4150 / 3565 |
| Development period | 1976-1988 | 1976 – 1986 | 1992 – 1996 2003 - 2004 |
| Purpose | RN "Energy" | RN "Zenith" | RN "Zenith" |
The base engine RD-170/171 was developed in 1976-1986. In 1992-1996 work was underway on a forced version of the RD-171 engine (by 1996, 28 engines had been tested). On 6 engines of an improved design, 5500 seconds were accumulated, and on one engine the operating time was 1590 seconds.
Work on the modernization of the RD-171 engine for use in the Sea Launch program was continued in 2003-2004. Certification of the RD-171M engine was completed on July 5, 2004 - 8 tests with a duration of 1093.6 seconds were carried out on the certification engine, and the last test (in excess of the plan) was at 105% mode. The first commercial engine RD-171M was delivered to Ukraine on March 25, 2004 after a test run of 140 seconds duration.
Serial production of the RD-171M engine is carried out at the NPO ENERGOMASH plant in Khimki.
In early 1996, the project of the RD-180 engine by NPO Energomash was declared the winner of the competition for the development and supply of the first stage engine for the upgraded Atlas launch vehicle of the American company Lockheed Martin. This is a two-chamber engine with afterburning of oxidizing generator gas, with thrust vector control due to the oscillation of each chamber in two planes, with the ability to provide deep throttling of engine thrust in flight. This design is based on well-tested designs of units and elements of RD-170/171 engines. The creation of a powerful engine of the first stage was carried out in a short time, and testing - on a small amount of the material part. Having signed a contract for the development of the engine in the summer of 1996, already in November 1996 the first fire test of the prototype engine was carried out, and in April 1997 the fire test of the standard engine was carried out. In 1997-1998, a series of fire tests of the engine as part of the launch vehicle stage was successfully carried out in the USA. In the spring of 1999, the certification of the engine for use as part of the Atlas 3 launch vehicle was completed. The first launch of the Atlas 3 launch vehicle with the RD-180 engine took place in May 2000. In the summer of 2001, the certification of the engine for use as part of the Atlas 5 launch vehicle was completed. The first flight of the Atlas 5 launch vehicle with the RD-180 engine took place in August 2002.
Main parameters of the RD-180 engine
Liquid propellant rocket engine with afterburning of oxidizing gas
Fuel oxygen + kerosene
Lockheed Martin announced its intention to order at least 101 RD-180 engines for use in the Atlas 3 and Atlas 5 launch vehicles. The marketing and sale of this engine to the customer - Lockheed Martin - is handled by the joint venture RD AMROSS, established by NPO Energomash and Pratt-Whitney (USA). More than 30 commercial engines have already been delivered to the United States, 14 launches of Atlas 3 and Atlas 5 launch vehicles with RD-180 engines in the first stage have been completed.
The development of the RD-191 engine began at the end of 1998. This engine with afterburning of oxidizing gas is designed for the Angara and Baikal family of domestic launch vehicles. The design of this engine is also based on the design of the RD-170/171 engines. The RD-191 engine is a single-chamber LRE with a vertically located TNA. During 1999 was released design documentation, in 2000, autonomous testing of the RD-191 engine units was started, preparation for production was completed. In May 2001, the first finishing engine RD-191 was assembled. The first fire test of the RD-191 engine was carried out in July 2001.
The main parameters of the RD-191 engine
Liquid propellant rocket engine with afterburning of oxidizing gas
Fuel oxygen + kerosene
As of August 1, 2006, more than 35 fire tests of the engine were carried out with a total operating time of 4500 seconds. The maximum time for one test is 400 sec. The test results of the engine confirmed the main parameters of the engine, laid down in terms of reference. Engine testing is carried out in accordance with the experimental development program, which provides for its completion on 10 engine copies with an operating time of more than 15,000 seconds during more than 70 fire tests. The main principle of such a program is a small number of engines and a large operating time on each instance with the maximum number of measurements.
ANALYSIS OF THE EFFECTIVENESS OF NOZZLE EXTENSION FOR ROCKET ENGINE RD-191
Marat Seydagaliev
Russia, Baikonur
Nikolay Ilyushenko
5th year student of the department “Design and testing of aircraft” branch “Voskhod” of MAI,
Russia, Baikonur
Olga Shestopalova
candidate of science, assistant professor of branch “Voskhod”
of the Moscow aviation institute (national research university),
Russia, Baikonur
ANNOTATION
Modern rocket engines have almost reached the limit of fuel energy capabilities, so increasing the efficiency of a rocket engine even by small values is not an easy task. The paper proposes a solution to this problem by using a sliding nozzle nozzle. For calculations, the most efficient and promising single-chamber liquid-propellant rocket engine RD-191 was taken as an example.
ABSTRACT
Modern rocket engines have almost reached the limit of energy fuel capabilities so increasing the efficiency of rocket engine even for small values is a big problem. There is a solution which suggests to use the nozzle extension. As an example for the calculations was taken RD-191 – the most effective and perspective liquid propellant rocket engine by now.
Keywords: launch vehicle (LV), propulsion system (PS), nozzle nozzles, liquid-propellant rocket engine (LRE), jet thrust, specific impulse.
keywords: launch vehicle, nozzle extension, liquid propellant rocket engine, jet thrust, specific impulse.
To date, the most promising launch vehicle of domestic cosmonautics is the Angara family of launch vehicles, which are based on the universal rocket module - 1 (URM-1). The propulsion system of the URM-1 is the RD-191 liquid-propellant rocket engine. This paper evaluates the effectiveness of using a nozzle nozzle for the RD-191 engine. Nozzle nozzle - the retractable part of the rocket engine nozzle, installation in working position which provides an increase in the output area of the nozzle, as a result, increases the efficiency in rarefied layers of the atmosphere or in vacuum.
The following assumptions were made in the calculation:
- the engine is running normally (with constant mass flow);
- the launch vehicle flies in a straight line, at a constant speed;
- losses due to friction and velocity dissipation at the nozzle outlet are not taken into account.
Required for calculation specifications LRE RD-191 are presented in table 1.
Table 1 .
Characteristics of the RD-191 rocket engine
|
Characteristic |
Designation |
Meaning |
|
Thrust (Earth), tf |
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|
Thrust (emptiness), tf |
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Specific impulse (Earth), s |
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|
Specific impulse (void), s |
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|
Pressure in the combustion chamber, kgf / cm in sq. |
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Pressure at the nozzle exit, kgf/cm2 in sq. |
||
|
Temperature in the combustion chamber |
||
|
Nozzle expansion ratio |
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|
Nozzle outlet diameter, mm |
||
|
Diameter of the minimum section of the nozzle, mm |
For calculations, it is proposed to use the jet engine thrust formula under the assumption of one-dimensionality of the gas flow through the nozzle:
where: µ – second mass flow rate; are the pressure, velocity, and cross-sectional area at the nozzle exit, respectively; - pressure environment, (depends on the lift height h).
The flow velocity at the nozzle exit is determined by the relationship known from gas dynamics:
(2)
where: - gas constant of combustion products; - temperature pressure in the combustion chamber, respectively; is the adiabatic index.
The adiabatic index depends on the fuel components used, for a kerosene-oxygen pair; =1.11 .
From expressions (1) and (2) we obtain the final expression for calculating the thrust of a jet engine:
(3)
Obviously, the thrust of the engine changes as it rises to altitude. The reason for this is that the ambient pressure is a continuously changing quantity.
Equation (3) describes the thrust of an engine with a constant geometric expansion ratio. Consider the case in which at each moment of time the calculated mode of operation of the engine () is realized. Then equation (3) will take the form:
(4)
To calculate the average thrust of an engine using a sliding nozzle, it is necessary to determine the geometric characteristics of the nozzle nozzle. Calculations have shown that the optimal radius of the nozzle nozzle, at which the average thrust will be the greatest throughout the entire operation of the engine, exceeds the radius of URM-1 (1.45 m), based on this, we accept the radius of the sliding nozzle equal to 1.20 m, this will allow the use nozzle nozzles in a package design and layout scheme (Angara-A3, Angara-A5, Angara-A5V). Based on the nozzle radius, we determine the pressure at the nozzle exit and calculate the engine thrust according to equation (1).
Below are the results of calculations (Fig. 1) of engine thrust according to equations (3), (4) for three cases:
- engine with fixed nozzle;
- engine with perfectly height-adjustable nozzle;
- engine with a single-stage adjustable nozzle.
Figure 1. Change in engine thrust depending on the flight altitude: 1 - unregulated nozzle, 2 - single-stage adjustable nozzle; 3 - perfectly height-adjustable nozzle
The calculation results showed that the use of a nozzle attachment for the Angara launch vehicles, made in a batch scheme, allows increasing the average thrust of each URM-1 by 9.28 tf, taking into account losses due to friction in the nozzle. When using a sliding nozzle nozzle on light-class launch vehicles made in a tandem scheme (Angara 1.1 and 1.2), the thrust increase will be 17.5 tf due to the absence of a restriction on the radius of the nozzle nozzle. When making structural changes to the RD-191 nozzle (in order to increase the pressure at the nozzle exit), it seems possible to increase the thrust by 24.4 tf for the stack and 35.7 tf for the tandem scheme.
Adjusting the height of the nozzle by using a nozzle nozzle is not a fundamentally new engineering solution, but this solution has not found practical implementation due to the difficulty of providing nozzle cooling. Today, this problem is resolvable due to the emergence of fundamentally new materials that were not available before, having a high swimming temperature, strength, wear resistance, etc. That is why the presented work is relevant and practically realizable.
Bibliography:
1. Alemasov V.E. Theory of rocket engines: textbook. for universities. - M .: Mashinostroenie, 1980.
2. Grechukh L.I. Designing a liquid rocket engine: guidelines to course and diploma design. - M.: Publishing house of OmGTU, 2011. - 69 p.
3. Dobrovolsky M.V. Liquid rocket engines: textbook. for universities. -M.: MSTU named after N.E. Bauman, 2006. - 269 p.
4. Propulsion system. RD-191 - [ Electronic resource]. - Access mode. – URL: http://ecoruspace.me/%D0%A0%D0%94-191.html (Date of access: 04/08/16).
–n. in.
characteristics
Sea level: 196 tf
Sea level: 311.5 s
Known engine modifications:
- RD-191 is used in the first stage of the Korean Naro-1 launch vehicle.
- The RD-193 is intended for use in the Soyuz-2.1v first stage.
- RD-181 export version of the engine RD-193, it is supposed to be installed on the American Antares launch vehicle by Orbital Sciences Corporation as a replacement for the NK-33 engines.
Main characteristics of RD-191:
The developer is the joint-stock company NPO Energomash im. Academician V.P. Glushko "(JSC NPO Energomash"). Engine production time is currently 18 to 24 months; it is planned to reduce this period to 12 months.
History of creation
In July 2010, during scheduled interdepartmental tests, it could not withstand repeated overloads and the RD-191 rocket engine burned out for the first stage of the Angara launch vehicle.
“The engine should have burned out. It's completely normal regular situation, experts had to establish what loads he was able to withstand.
Press center - NPO Energomash.
On August 25, 2015, NPO Energomash began to create an upgraded version of the RD-191 engine - RD-191M - which will be used on the Angara-A5V and Angara-A5P ILVs and will be 10-15% more powerful than its predecessor. The first stage of the pilot project release will be completed in September 2015. Development work is planned to be completed by 2018.
In November 2015, Proton-Perm Motors PJSC announced a tender for the reconstruction of workshops for the production of the RD-191 engine for Angara missiles.
In September 2016, it became known that digital design would be introduced for the RD-191. For this, a project team, a steering committee and a budget. The implementation of the project is planned for three years.
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Notes
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An excerpt characterizing the RD-191
Prince Andrei said that this required a legal education, which he did not have.- Yes, no one has it, so what do you want? This is the circulus viciosus, [the vicious circle] from which one must get out of the effort.
A week later, Prince Andrei was a member of the commission for drafting the military regulations, and, which he did not expect, the head of the department of the commission for compiling wagons. At the request of Speransky, he took the first part of the civil code being compiled and, with the help of the Code Napoleon and Justiniani, [the Code of Napoleon and Justinian,] worked on compiling the department: Rights of persons.
About two years ago, in 1808, returning to St. Petersburg from his trip to the estates, Pierre involuntarily became the head of St. Petersburg Freemasonry. He set up dining and funeral lodges, recruited new members, took care of uniting various lodges and acquiring genuine acts. He gave his money for the construction of temples and replenished, as far as he could, almsgiving, for which most of the members were stingy and sloppy. He almost alone at his own expense supported the house of the poor, arranged by the order in St. Petersburg. Meanwhile, his life went on as before, with the same hobbies and licentiousness. He liked to dine and drink well, and although he considered it immoral and humiliating, he could not refrain from the amusements of bachelor societies in which he participated.
In the wake of his studies and hobbies, Pierre, however, after a year, began to feel how the soil of Freemasonry on which he stood, the more he left from under his feet, the more firmly he tried to become on it. At the same time, he felt that the deeper the soil on which he stood went under his feet, the more involuntarily he was connected with it. When he began Freemasonry, he experienced the feeling of a man trustingly placing his foot on the flat surface of a swamp. Putting his foot down, he fell. In order to fully assure himself of the firmness of the ground on which he stood, he put his other foot on and sank even more, got stuck and already involuntarily walked knee-deep in the swamp.
Iosif Alekseevich was not in Petersburg. (He has recently retired from the affairs of St. Petersburg lodges and lived without a break in Moscow.) All the brothers, members of the lodges, were people familiar to Pierre in life, and it was difficult for him to see in them only brothers in stoneworking, and not Prince B., not Ivan Vasilyevich D., whom he knew in life for the most part as weak and insignificant people. From under the Masonic aprons and signs, he saw on them uniforms and crosses, which they had achieved in life. Often, collecting alms and counting 20-30 rubles written down for the parish, and mostly in debt from ten members, of whom half were as rich as he was, Pierre recalled the Masonic oath that each brother promises to give everything property for a neighbor; and doubts arose in his soul, on which he tried not to dwell.
He divided all the brothers he knew into four categories. In the first category, he ranked brothers who do not take an active part either in the affairs of lodges or in human affairs, but are exclusively occupied with the sacraments of the science of the order, occupied with questions about the triple name of God, or about the three principles of things, sulfur, mercury and salt, or about the meaning square and all the figures of Solomon's temple. Pierre respected this category of Masonic brothers, to which the old brothers mostly belonged, and Joseph Alekseevich himself, according to Pierre, did not share their interests. His heart did not lie to the mystical side of Freemasonry.
In the second category, Pierre included himself and brothers like himself, who are searching, hesitating, who have not yet found a direct and understandable path in Freemasonry, but hoping to find it.
In the third category, he ranked the brothers (there were the largest number of them), who did not see anything in Freemasonry except for the external form and rituals and valued the strict execution of this external form, not caring about its content and meaning. Such were Vilarsky and even the great master of the main lodge.
To the fourth category, finally, was also ranked a large number of brethren, especially those who have lately joined the brotherhood. These were people, according to Pierre's observations, who did not believe in anything, who did not want anything, and who entered Freemasonry only to get closer to young rich and strong brothers in connections and nobility, of whom there were very many in the lodge.
Pierre began to feel dissatisfied with his activities. Freemasonry, at least the Freemasonry he knew here, sometimes seemed to him to be based on appearance alone. He did not even think of doubting Freemasonry itself, but he suspected that Russian Freemasonry had taken the wrong path and deviated from its source. And therefore, at the end of the year, Pierre went abroad to initiate himself into the highest secrets of the order.
In the summer back in 1809, Pierre returned to St. Petersburg. According to the correspondence of our Freemasons with foreign ones, it was known that Bezuhiy managed to gain the trust of many high-ranking officials abroad, penetrated many secrets, was elevated to the highest degree, and was carrying with him a lot for the common good of the masonry business in Russia. Petersburg Freemasons all came to him, currying favor with him, and it seemed to everyone that he was hiding something and preparing something.
A solemn meeting of the lodge of the 2nd degree was appointed, in which Pierre promised to inform what he had to convey to the St. Petersburg brothers from the highest leaders of the order. The meeting was full. After the usual rituals, Pierre got up and began his speech.
“Dear brothers,” he began, blushing and stammering, and holding a written speech in his hand. – It is not enough to observe our sacraments in the quiet of the lodge – you need to act… act. We are in stupor, and we need to act. Pierre took his notebook and began to read.
“In order to spread pure truth and bring about the triumph of virtue,” he read, we must cleanse people of prejudices, spread rules consistent with the spirit of the times, take upon ourselves the education of youth, unite with inseparable ties with the most intelligent people, boldly and together prudently overcome superstition, unbelief and stupidity, to form from people devoted to us, connected with each other by a unity of purpose and having power and strength.
“To achieve this goal, virtue must be given a preponderance over vice, one must strive so that an honest person gains an eternal reward for his virtues in this world. But in these great intentions we are hindered by quite a lot - the current political institutions. What to do in such a state of affairs? Shall we favor revolutions, overthrow everything, expel force by force?... No, we are very far from that. Every violent reform is reprehensible, because it will do nothing to correct evil as long as people remain as they are, and because wisdom has no need for violence.
In July, at the suburban site of Proton-PM PJSC (part of the integrated structure of NPO Energomash JSC), a sheet cutting and painting. The amount of investments in the creation of production amounted to more than 76 million rubles.
The new site produces ground-based products: parts and assembly units of gas turbine power plants of the Ural series, as well as equipment. In the near future, the site will be involved in the production of combustion chambers for rocket engines and other space-related nomenclature.
Earlier, the governor of the Kama region, Maxim Reshetnikov, noted that the production of rocket engines is the top scientific and technological progress and an important factor in the development of the region. According to the head of the region, the Permian rocket and engine building enterprises enjoy great confidence in the country's leadership, and the quality of products is assessed as very high. Everyone understands that Perm enterprises are a guarantee of reliability.
Dmitry Shchenyatsky, Executive Director of PJSC Proton-PM, noted that the creation of a cutting section is the next stage in the organization of a modern full-cycle blank production at the plant's out-of-town site in Novye Lyady. “This is a step forward that will optimize manufacturing process, to use new capacities in the development of promising rocket and space products and the transition to its serial production. AT next year we plan to ensure 100% utilization of the commissioned equipment,” the top manager emphasized.
At the site of sheet cutting and painting with a total area of more than 2 thousand square meters. m housed four units of modern technological equipment: laser cutting machine and waterjet cutting machine for cutting sheet material, shot blasting chamber for preparing metal for coating and painting and drying chamber. In addition, guillotine shears for cutting and chopping metal are installed on the territory of the site, and a warehouse for sheet material is also located here.
The technical characteristics of the laser machine make it possible to cut a contour detail up to 12 mm thick in just one and a half minutes. In turn, the waterjet cutting unit is capable of cutting various materials with a thickness of up to 300 mm with a water jet, making a cut at an angle, providing the necessary accuracy and cleanliness of the machined surface. It does not use harmful oils, liquids and gases, which increases productivity and safety.
New procurement capacities are being created as part of the organization in the Perm Territory of a production complex for serial production of RD-191 and other promising liquid engines. This project has the status of a priority regional investment project and includes the reconstruction and optimization of the production facilities of Proton-PM PJSC with their concentration on the territory of Novye Lyady, the development by the enterprise of the full cycle of production of RD-191 engine units in the Perm Territory and other new technology, creation of high-quality social, educational and housing infrastructure. Overall volume investments will amount to 10.8 billion rubles, while about 250 jobs will be created. The project started in 2018 and runs until 2025.
