The Concept of Efficient High Pressure Liquid Oxygen Feed System

2006 ◽  
Author(s):  
Valery Gurov ◽  
Constantine Shestakov ◽  
Evgeny Romasenko
Keyword(s):  
High Pressure ◽  
Liquid Oxygen ◽  
Feed System

Experimental Study on High-Pressure Gas Seals for a Liquid Oxygen Turbopump

1988 ◽  
Vol 31 (1) ◽  
pp. 91-97 ◽  
Author(s):  
Mamoru Oike ◽  
Masataka Nosaka ◽  
Yoshiaki Watanabe ◽  
Masataka Kikuchi ◽  
Kenjiro Kamijo
Keyword(s):  
Experimental Study ◽  
High Pressure ◽  
Liquid Oxygen ◽  
Gas Seals

scholarly journals Hot-fire testing of liquid oxygen/hydrogen single coaxial injector at high-pressure conditions with optical diagnostics

2019 ◽  
Author(s):  
D.I. Suslov ◽  
J.S. Hardi ◽  
B. Knapp ◽  
M. Oschwald
Keyword(s):  
High Pressure ◽  
High Speed ◽  
Optical Diagnostics ◽  
Liquid Oxygen ◽  
Experimental Investigations ◽  
Rocket Engines ◽  
Chamber Length ◽  
Substantial Progress ◽  
Liquid Rocket ◽  
Coaxial Injector

Injector behavior is of utmost importance for the performance and stability of liquid rocket engines (LREs). A major problem is getting a highly efficient homogeneous mixture and effective chemical reaction of fuels at minimum chamber length. Despite substantial progress in numerical simulations, a need for experimental data at representative conditions for development and validation of numerical design tools still exists. Therefore, in the framework of the DLR-project “ProTau,” the authors have performed tests to create an extended data base for numerical tool validation for high-pressure liquid oxygen (LOx) / hydrogen combustion. During the experimental investigations, a windowed DLR subscale thrust chamber model “C” (designated BKC) has been operated over a broad range of conditions at reduced pressures of approximately 0.8 (4 MPa), 1 (5 MPa), and 1.2 (6 MPa) with respect to the thermodynamic critical pressure of oxygen. Liquid oxygen and gaseous hydrogen (GH2) have been injected through a single coaxial injector element at temperatures of ~ 120 and ~ 130 K, respectively. High-speed optical diagnostics have been implemented, including imaging of OH* emission and shadowgraph imaging at frequencies from 8 up to 10 kHz to visualize the flow field.

Development of a novel solids feed system for high pressure gasification

2014 ◽  
Vol 119 ◽  
pp. 32-40 ◽  
Author(s):  
J.M. Craven ◽  
J. Swithenbank ◽  
V.N. Sharifi ◽  
D. Peralta-Solorio ◽  
G. Kelsall ◽  
...  
Keyword(s):  
High Pressure ◽  
Feed System

Injection and Mixing Processes in High-Pressure Liquid Oxygen/Gaseous Hydrogen Rocket Combustors

2000 ◽  
Vol 16 (5) ◽  
pp. 823-828 ◽  
Author(s):  
W. Mayer ◽  
A. Schik ◽  
M. Schaffler ◽  
H. Tamura
Keyword(s):  
High Pressure ◽  
Gaseous Hydrogen ◽  
Liquid Oxygen ◽  
Mixing Processes

scholarly journals Recent Experimental Efforts on High-Pressure Supercritical Injection for Liquid Rockets and Their Implications

2012 ◽  
Vol 2012 ◽  
pp. 1-31 ◽  
Author(s):  
Bruce Chehroudi
Keyword(s):  
High Pressure ◽  
Critical Point ◽  
Space Shuttle ◽  
Specific Impulse ◽  
Liquid Oxygen ◽  
Liquid Jets ◽  
Rocket Engines ◽  
Liquid Rocket Engines ◽  
Liquid Rocket ◽  
Air Force Research Laboratory

Pressure and temperature of the liquid rocket thrust chambers into which propellants are injected have been in an ascending trajectory to gain higher specific impulse. It is quite possible then that the thermodynamic condition into which liquid propellants are injected reaches or surpasses the critical point of one or more of the injected fluids. For example, in cryogenic hydrogen/oxygen liquid rocket engines, such as Space Shuttle Main Engine (SSME) or Vulcain (Ariane 5), the injected liquid oxygen finds itself in a supercritical condition. Very little detailed information was available on the behavior of liquid jets under such a harsh environment nearly two decades ago. The author had the opportunity to be intimately involved in the evolutionary understanding of injection processes at the Air Force Research Laboratory (AFRL), spanning sub- to supercritical conditions during this period. The information included here attempts to present a coherent summary of experimental achievements pertinent to liquid rockets, focusing only on the injection of nonreacting cryogenic liquids into a high-pressure environment surpassing the critical point of at least one of the propellants. Moreover, some implications of the results acquired under such an environment are offered in the context of the liquid rocket combustion instability problem.

A Study on Oxygen Leak-Diffusion Process and Environmental Influence of High-Pressure Liquid of Spherical Tank

2014 ◽  
Vol 1073-1076 ◽  
pp. 1574-1578
Author(s):  
Jia Wei Chen ◽  
Jue Ding ◽  
Pei Fen Weng
Keyword(s):  
High Pressure ◽  
Diffusion Processes ◽  
Environmental Influence ◽  
Assessment Method ◽  
Oxygen Storage ◽  
Liquid Oxygen ◽  
Spherical Tank ◽  
Computational Fluid Dynamics Cfd ◽  
Accident Consequence ◽  
Oxygen Poisoning

Numerical prediction can analyze the cause and process of the accident comprehensively with the application of mathematical models. The computed results are more reliable and intuitive compared with the qualitative analysis results. Therefore, based on the Computational Fluid Dynamics (CFD) and the related theory of safety system science, leak and diffusion processes of high pressure liquid oxygen in spherical tank area, and the subsequent potential oxygen poisoning was analyzed by accident consequence assessment method. The given poisoning area and damage situation provide a reference for the safety analysis of oxygen storage and transportation.

High-Frequency, High-Pressure, Flush Mounted Miniature Liquid Oxygen Fiber-Optic Pressure Sensor

2006 ◽  
Author(s):  
Matthew Palmer ◽  
Matthew Davis ◽  
Robert Fielder ◽  
Clark Boyd ◽  
Marlow Moser ◽  
...  
Keyword(s):  
High Pressure ◽  
Pressure Sensor ◽  
High Frequency ◽  
Fiber Optic ◽  
Liquid Oxygen

Experimental Investigation of Transient Flow Measurement in the Ram-Accelerator High Pressure Pneumatic System

2013 ◽  
Vol 333-335 ◽  
pp. 215-218
Author(s):  
Yang Liu ◽  
Xiao Dong Song ◽  
Xiao Xian Yao ◽  
Kun Li
Keyword(s):  
High Pressure ◽  
Pressure Difference ◽  
Discharge Coefficient ◽  
Flow Characteristic ◽  
Transient Flow ◽  
Least Square ◽  
Inlet Pressure ◽  
Test Bed ◽  
Feed System ◽  
Ram Accelerator

A high-pressure-pneumatic mass flow control test-bed using inert medium was built in order to study the transient flow characteristic of high pressure gas feed system in ram accelerator. The structure of a new type measurement system of transient flow characteristic experiments applied to the test-bed was introduced as also. Measurement tests that high pressure gas-flow ejecting into a tank with exhaust-back-pressure through a high pressure fueling valve were conducted to ascertain the transient discharge coefficient. The results suggest that: The transient discharge coefficient increases with the inlet pressure difference of high pressure fueling valve according to polynomial law. Correlations between inlet pressure difference and transient discharge coefficient was obtained based on the experimental data. The correlation coefficient between the least square fitting curve of the correlations and experimental results reaches 0.994.The system could be used to study the change regularity of pressure and time in the fueling process of high pressure gas.

Development of Advanced Technology and Equipment for Manufacture of Titanium Spherical Vessels

2021 ◽  
pp. 37-43
Author(s):  
I.V. Lomakin ◽  
A.Yu. Ryazantsev ◽  
S.S. Yukhnevich ◽  
A.A. Shirokozhukhova
Keyword(s):  
High Pressure ◽  
Operating Conditions ◽  
Advanced Technology ◽  
Liquid Oxygen ◽  
Production Cycle ◽  
Launch Vehicles ◽  
Design Bureau ◽  
Manufacturing Technologies ◽  
Effective Use ◽  
The Cost

The most promising in the world practice are launch vehicles using titanium spherical vessels in a cryogenic medium at high pressure. The paper deals with an import-substituting technology, which provides a closed production cycle for the manufacture of titanium spherical vessels at the JSC “Chemical Automatics Design Bureau” and analyzes existing manufacturing technologies. We developed an innovative method of shaping and machining hemispheres from hard-to-deform advanced titanium alloys, providing maximum automation and productivity of the process. For hydraulic and cryogenic tests of submersible titanium vessels, bench equipment was developed and introduced into production. For simulating the facility operating conditions in order to reduce the cost and increase the safety of tests, liquid oxygen was replaced with liquid nitrogen and helium was replaced with high-pressure nitrogen. Within the study, we substantiated the area of ??effective use of the import-substituting technology and developed production facilities of a closed cycle for the production of titanium vessels with a capacity of 25 and 130 liters.

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