On the spinning-detonation-like properties of high frequency tangential oscillations in combustion chambers of liquid fuel rocket engines

1972 ◽  
Vol 11 (1) ◽  
pp. 159-161 ◽  
Author(s):  
O. F. Ar'kov ◽  
B. V. Voitsekhovskii ◽  
V. V. Mitrofanov ◽  
M. E. Topchiyan
Keyword(s):  
High Frequency ◽  
Liquid Fuel ◽  
Rocket Engines ◽  
Combustion Chambers ◽  
Spinning Detonation

A Driving Mechanism for High Frequency Combustion Instability in Liquid Fuel Rocket Engines

1964 ◽  
Vol 68 (645) ◽  
pp. 633-637 ◽  
Author(s):  
P. D. McCormack
Keyword(s):  
High Frequency ◽  
Liquid Fuel ◽  
Low Frequency ◽  
Pressure Oscillation ◽  
Experimental Investigations ◽  
Driving Mechanism ◽  
Rocket Engines ◽  
High Frequency Oscillations ◽  
The Subject ◽  
Motor Operation

The problem of combustion pressure oscillation in liquid-fuel rocket motor operation has long been the subject of theoretical and experimental investigations.The low frequency (less than 200 cps) type of oscillation, known as “chugging”, has been thoroughly analysed and the problem solved (see Crocco, 5th Combustion Symposium, p. 164).This Note is concerned with the more complex (and more destructive) high frequency oscillations, covering a range from about 1000 to 6000 cps. Such oscillations can resonate with the acoustical modes of the combustion chamber. Longitudinal, tangential and radial oscillating modes have been observed.

scholarly journals Flame response to high-frequency oscillations in a cryogenic oxygen/hydrogen rocket combustor

2019 ◽  
Author(s):  
N. Fdida ◽  
J. Hardi ◽  
H. Kawashima ◽  
B. Knapp ◽  
M. Oschwald ◽  
...  
Keyword(s):  
High Frequency ◽  
Acoustic Resonance ◽  
High Amplitude ◽  
Operating Conditions ◽  
Test Facility ◽  
Response Analysis ◽  
Rocket Engines ◽  
Acoustic Oscillations ◽  
Spatially Resolved ◽  
Flame Response

Experiments presented in this paper were conducted with the BKH rocket combustor at the European Research and Technology Test Facility P8, located at DLR Lampoldshausen. This combustor is dedicated to study the effects of high magnitude instabilities on oxygen/hydrogen flames, created by forcing high-frequency (HF) acoustic resonance of the combustion chamber. This work addresses the need for highly temporally and spatially resolved visualization data, in operating conditions representative of real rocket engines, to better understand the flame response to high amplitude acoustic oscillations. By combining ONERA and DLR materials and techniques, the optical setup of this experiment has been improved to enhance the existing database with more highly resolved OH* imaging to allow detailed response analysis of the flame. OH* imaging is complemented with simultaneous visible imaging and compared to each other here for their ability to capture flame dynamics.

Advanced Composite Materials for Current and Future Propulsion and Industrial Applications

2006 ◽  
Vol 50 ◽  
pp. 174-181 ◽  
Author(s):  
Steffen Beyer ◽  
Stephan Schmidt ◽  
Franz Maidl ◽  
Rolf Meistring ◽  
Marc Bouchez ◽  
...  
Keyword(s):  
Composite Materials ◽  
Composite Structures ◽  
Chemical Vapour ◽  
Liquid Silicon ◽  
Large Temperature ◽  
Rocket Engines ◽  
Combustion Chambers ◽  
Standard Material ◽  
Liquid Rocket ◽  
Engine Components

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.

Enhanced DMFC Performance via Electro-Hydraulic Pulsing

2004 ◽  
Author(s):  
Comas Haynes ◽  
Scott Leahy ◽  
Leonard Lay ◽  
Larry McCarthy ◽  
David Parekh
Keyword(s):  
Fuel Cell ◽  
Power Output ◽  
High Frequency ◽  
Liquid Fuel ◽  
Direct Methanol Fuel Cells ◽  
Methanol Crossover ◽  
Current Load ◽  
Direct Methanol ◽  
Methanol Fuel Cells ◽  
Choice Option

Direct methanol fuel cells (DMFCs) are an attractive fuel cell choice option, particularly because of the capability to use liquid fuel without need for processing. The phenomenon of methanol crossover, however, substantially reduces cell power output and efficiency. The present work shows the benefits of periodically pulsed fuel supply and current load on the performance of a DMFC. It is determined that the enhanced performance resultant from such electro-hydraulic (EH) pulsing is realized due to temporary, cyclic mitigations of methanol crossover (as well as unstably high voltages given high frequency electronic pulsing).

ACOUSTIC CAVITIES DESIGN PROCEDURES

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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