4127 Measurements of Cryogenic Mass Flow Rate in CEES Rocket Engine

The numerical calculation of three-dimensional unsteady combustion for the combustion chamber of LOX/kerosene high pressure staged combustion rocket engine was carried out. By changing the offset ratio of oxygen mass flow rate in the edge area of the injector face, computational studies were conducted to investigate the effects of non-uniform distribution of oxidizer flow on combustion instability for a liquid-propellant rocket engine. The calculation results show that the offset ratio of oxygen mass flow rate changes the distribution of heat release in the combustion chamber. Within a certain range of offset ratio, the non-uniform distribution degree of oxidizer flow enhances the coupling between the pressure and heat release. As a result, it leads to an increase in the pressure oscillation amplitude in the combustion chamber. However, if the offset ratio is too large, the oxygen-fuel ratio will be too small in some regions, which will reduce coupling between the pressure and heat release and increase the damping of combustion instability.

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Influence of the Blade Number on Inducer Cavitating Behavior

Volume 2: Fora ◽

10.1115/fedsm2009-78405 ◽

2009 ◽

Author(s):

O. Coutier-Delgosha ◽

G. Caignaert ◽

G. Bois ◽

J.-B. Leroux ◽

Patrick Olivier ◽

...

Keyword(s):

Mass Flow Rate ◽

Mass Flow ◽

Flow Rate ◽

Rocket Engine ◽

Cavitation Number ◽

Design Flow ◽

Flow Rates ◽

Blade Number ◽

Radial Forces ◽

Critical Cavitation

Effects of the blade number on the performance of a rocket engine turbopump inducer are investigated in the present paper. For that purpose, two inducers characterized by three blades and five blades respectively were manufactured and tested experimentally. The two inducers were designed on the basis of identical design flow rate, and identical pressure elevation at nominal flow rate. The first part of the study focuses on the steady behavior of the inducers in cavitating conditions: evolutions of performance, torque, mass flow rate, and amplitude of radial forces on the shaft according to the inlet pressure are considered. Several flow rates and rotation speeds are investigated. Significant differences between the inducers are obtained concerning the critical cavitation number, the amplitude of the radial forces, and the organization of cavitation in the machinery. Cavitation instabilities are investigated in the second part of the study. Various flow patterns are detected according to the mass flow rate and the cavitation number.

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Influence of the Blade Number on Inducer Cavitating Behavior

Journal of Fluids Engineering ◽

10.1115/1.4006693 ◽

2012 ◽

Vol 134 (8) ◽

Cited By ~ 5

Author(s):

O. Coutier-Delgosha ◽

G. Caignaert ◽

G. Bois ◽

J.-B. Leroux

Keyword(s):

Mass Flow Rate ◽

Mass Flow ◽

Flow Rate ◽

Rocket Engine ◽

Cavitation Number ◽

Design Flow ◽

Flow Rates ◽

Blade Number ◽

Radial Forces ◽

Critical Cavitation

Effects of the blade number on the performance of a rocket engine turbopump inducer are investigated in the present paper. For that purpose, two inducers characterized by three blades and five blades, respectively, were manufactured and tested experimentally. The two inducers were designed on the basis of identical design flow rate and identical pressure elevation at nominal flow rate. The first part of the study focuses on the steady behavior of the inducers in cavitating conditions: evolutions of performance, torque, mass flow rate, and amplitude of radial forces on the shaft according to the inlet pressure are considered. Several flow rates and rotation speeds are investigated. Significant differences between the inducers are obtained concerning the critical cavitation number, the amplitude of the radial forces, and the organization of cavitation in the machinery. Cavitation instabilities are investigated in the second part of the study. Various flow patterns are detected according to the mass flow rate and the cavitation number.

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