Mechanical impact tests of some selected polymers in high pressure liquid oxygen environments

2004 ◽  
Vol 28 (1) ◽  
pp. 55-59
Author(s):  
Fu-Yu Hshieh ◽  
David B. Hirsch ◽  
Harold D. Beeson
Keyword(s):  
High Pressure ◽  
Liquid Oxygen ◽  
Mechanical Impact ◽  
Impact Tests

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.

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
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