Reducing the Aerodynamic Drag of the Mating Sections of the Combustion Chambers of Rocket Engines

Various technology programmes in Europe are concerned with preparing for future propulsion technologies to reduce the costs and increase the life time of components for liquid rocket engine components. One of the key roles to fulfil the future requirements and for realizing reusable and robust engine components is the use of modern and innovative materials. One of the key technologies which concern various engine manufacturers worldwide is the development of fibrereinforced ceramics – CMC's (Ceramic Matrix Composites). The advantages for the developers are obvious – the low specific weight, the high specific strength over a large temperature range, and their good damage tolerance compared to monolithic ceramics make this material class extremely interesting as a construction material. Different kind of composite materials are available and produced by EADS ST, the standard material SICARBON® (C/SiC made by Liquid Polymer Infiltration) and the new developed and qualified composite materials SICTEX® (C/SiC made by Liquid Silicon Infiltration) and CARBOTEX® (C/C made by Rapid Chemical Vapour Infiltration). The composites are based on textile techniques like weaving, braiding, stiching and sewing to produce multiaxial preforms, the SICTEX® material is densificated by the cost effective Liquid Silicon Infiltration (LSI). Over the past years, EADS Space Transportation (formerly DASA) has, together with various partners, worked intensively on developing components for airbreathing and liquid rocket engines. Since this, various prototype developments and hot firing-tests with nozzle extensions for upper and core stage engines and combustion chambers of satellite engines were conducted. MBDA France and EADS-ST have been working on the development of fuel-cooled composite structures like combustion chambers and nozzle extensions for future propulsion applications.

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ACOUSTIC CAVITIES DESIGN PROCEDURES

Revista de Engenharia Térmica ◽

10.5380/reterm.v6i2.61687 ◽

2007 ◽

Vol 6 (2) ◽

pp. 27

Author(s):

A. Santana Jr. ◽

M. S. Silva ◽

P. T. Lacava ◽

L. C. S. Góes

Keyword(s):

Solid Propellant ◽

Rocket Engines ◽

Combustion Chambers ◽

High Frequencies ◽

Design Procedures ◽

Solid Propellant Rocket ◽

Acoustic Cavities ◽

The Stability ◽

Propellant Rocket ◽

Damping Systems

Combustion instability is recognized as one of the major problems frequently faced by engineers during the development of either liquid or solid propellant rocket engines. The performance of the engine can be highly affected by these high frequencies instabilities, possibly leading the rocket to an explosion. The main goal while studying combustion chambers instability, either by means of baffles or acoustic absorbers, is to achieve the stability needed using the simplest possible manner. This paper has the purpose of studying combustion chambers instabilities, as well as the design of acoustic absorbers capable of reducing their eigenfrequencies. Damping systems act on the chamber eigenfrequency, which has to be, therefore, previously known.

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Original Romanian Research for a Rocket Engine with Multiple Combustion Chambers during 1940 - 1944

INCAS BULLETIN ◽

10.13111/2066-8201.2020.12.1.22 ◽

2020 ◽

Vol 12 (1) ◽

pp. 229-241

Author(s):

Nicolae-Florin ZAGANESCU ◽

Constantin-Marcian GHEORGHE ◽

Peter KALMUTCHI

Keyword(s):

Rocket Engine ◽

Mechanical Equipment ◽

Technical Solution ◽

Rocket Engines ◽

Centrifugal Pumps ◽

Combustion Chambers ◽

Bypass Valve ◽

Fuel Tanks ◽

History Of ◽

Points Of View

The paper presents certain points of view regarding the history of Romanian rocket engines, during 1940-1944. Working independently of other scientists, during 1942 – 1944 the Romanian Nicolae Văideanu has invented and designed, independently of other researchers, a liquid fuel missile called UDOVILUL-V [3]. According to the design drawings, this missile was equipped with aerodynamically profiled propelling nozzles and was provided with a special alternator – distributor, the bypass valve adjusting the fuel components dosage in the two combustion chambers, in fuel tanks and pipes, while a special designed gas turbine was driving the centrifugal pumps and other mechanical equipment. Within his main patent the Romanian inventor has included the design of several components [2], [4], [5]. The technical solution of this outstanding design in rocketry development could provide 20kN thrust after 60 sec, enabling a speed of 3200 km/h [10].

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COMBINED CHANNEL PROCESSING TECHNOLOGY BASED ON MULTI-LAYER TEMPLATES

ВЕСТНИК ВОРОНЕЖСКОГО ГОСУДАРСТВЕННОГО ТЕХНИЧЕСКОГО УНИВЕРСИТЕТА ◽

10.36622/vstu.2021.17.1.014 ◽

2021 ◽

pp. 89-96

Author(s):

А.В. Щеднов ◽

В.П. Смоленцев ◽

Н.С. Поташникова

Keyword(s):

Rocket Engine ◽

High Heat ◽

Rocket Engines ◽

Combustion Chambers ◽

Bottom Part ◽

Narrow Channels ◽

Engine Cooling ◽

The Cost ◽

New Generation ◽

Combined Channel

Рассмотрена технология изготовления дополнительных элементов систем охлаждения ракетных двигателей в форме местных углублений, расположенных на имеющихся фрезерованных каналах на наружных поверхностях камер сгорания и реактивного сопла. Такая проблема требует решения в перспективных изделиях с повышенной теплонапряженностью зоны горения топлива. Проведен анализ конструкции и возможностей обработки дополнительных элементов охлаждения в донной части и на боковых поверхностях узких каналов с ограниченным доступом инструмента в зону удаления припуска. Изучены новые конструкции инструмента для комбинированной обработки с использованием шаблонов различной конструкции и обоснована возможность их использования для изготовления углублений в каналах. Предложены новые способы комбинированной локальной обработки углублений с несимметричной геометрией сечения, форма которых обоснована в процессе отработки технологичности конструкции создаваемых двигателей, что ранее считалось неосуществимым или чрезмерно трудоемким. Исследована возможность многоместной обработки локальных углублений для дополнительного охлаждения в каналах на участках с переменным профилем камер сгорания современных и перспективных изделий по многослойным шаблонам. Здесь разработанные комбинированные технологии дают наибольший эффект и способствуют повышению ресурса двигателей новых поколений до уровня, обеспечивающего многократное увеличение количества безотказных пусков космических систем, что значительно снижает затраты на изготовление ракетных двигателей новых поколений The article considers the technology of manufacturing additional elements of rocket engine cooling systems in the form of local recesses located on the existing milled channels on the outer surfaces of the combustion chambers and the jet nozzle. This problem requires solutions in promising products with high heat stress of the fuel combustion zone. We analyzed the design and processing capabilities of additional cooling elements in the bottom part and on the side surfaces of narrow channels with limited tool access to the allowance removal zone. We studied new tool designs for combined processing using templates of various designs and justified the possibility of their use for making recesses in channels. We propose new methods of combined local processing of recesses with an asymmetric cross-section geometry, the shape of which is justified in the process of testing the manufacturability of the design of the created engines, which was previously considered impossible or excessively labor-intensive. We investigated the possibility of multi-site processing of local recesses for additional cooling in channels in areas with a variable profile of the combustion chambers of modern and promising products using multilayer templates. Here, the developed combined technologies give the greatest effect and contribute to increasing the resource of new-generation engines to a level that provides a multiple increase in the number of trouble-free launches of space systems. This significantly reduces the cost of manufacturing new-generation rocket engines

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Study of Hydraulic Characteristics of the Cooling Path of a Model Liquid Rocket Engine Manufactured using Additive Technology of Selective Laser Melting

Herald of the Bauman Moscow State Technical University Series Mechanical Engineering ◽

10.18698/0236-3941-2019-6-41-52 ◽

2019 ◽

pp. 41-52

Author(s):

D.A. Yagodnikov ◽

V.P. Aleksandrenkov ◽

K.E. Kovalev ◽

A.G. Grigoryants ◽

A.A. Drenin

Keyword(s):

Selective Laser Melting ◽

Rocket Engine ◽

Rocket Engines ◽

Hydraulic Characteristics ◽

Combustion Chambers ◽

Laser Melting ◽

Melting Technology ◽

Model Liquid ◽

Cooling Path ◽

Liquid Rocket

The article discusses hydraulic tests of a model combustion chamber of a liquid-propellant rocket engine with a cooling path made using additive selective laser melting technology. The values of the coefficient of hydraulic resistance in the range of Re = 10--2500 are obtained and the influence of the design features of the cooling tract and its manufacturing technology on the hydraulic characteristics is determined. The results of the performed hydraulic tests confirm the possibility of using additive technologies based on selective laser melting technology for the manufacture of fire and power walls of combustion chambers of liquid rocket engines.

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Technology for ﬁ nishing combined processing of mineral-ceramic coatings

10.36652/1813-1336-2020-16-7-318-323 ◽

2020 ◽

pp. 318-323

Author(s):

E.V. Panichev ◽

V.P. Smolentsev ◽

V.V. Ivanov

Keyword(s):

Surface Layer ◽

Protective Coatings ◽

Combustion Products ◽

Ceramic Coatings ◽

Fuel Combustion ◽

Rocket Engines ◽

Combustion Chambers ◽

Temperature Combustion ◽

Liquid Rocket ◽

Processing Zone

Technological methods for manufacturing of cooling elements of modern rocket engines are considered, they are developed taking into account the possibility of reusable use. Significant increase in the thermal load on the walls of combustion chambers of liquid rocket engines required the creation of new ways to protect the surface layer of the hot zone from the effects of the flame in the fuel combustion zone. The possibilities for using of plasma application of metal-ceramic heat-protective coatings for these purposes, which have good erosion resistance and high thermal resistance in conditions of intense exposure to high-temperature combustion products, are revealed. The analysis of the effect of the quality of the coatings surface layer on the performance characteristics of the product is presented. The need for local finishing of the applied coatings is justified, including in the transition areas of the combustion chambers and the jet nozzle, which have limited tool access to the processing zone. The most effective method is the combined alignment of the microprofile with the imposition of electric field. But for its implementation, set of studies is needed to study the mechanism of allowance removing, and to adjust the technological modes. The task of minimizing allowances for finishing combined processing is solved, which allowed to align the thickness of the heat-protective coating along the length of the fuel combustion path, including the cleaning sections, to increase the number of trouble-free engine starts by 1.5...2.0 times and ensure reusable use of product.

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