scholarly journals On melting heat transport and nanofluid in a nozzle of liquid rocket engine with entropy generation

2021 ◽  
Author(s):  
Umar Farooq ◽  
Hassan Waqas ◽  
Muhammad Imran ◽  
Metib Alghamdi ◽  
Taseer Muhammad
Keyword(s):  
Heat Transport ◽  
Entropy Generation ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Melting Heat ◽  
Liquid Rocket

scholarly journals On the heat transport mechanism and entropy generation in a nozzle of liquid rocket engine using ferrofluid: A computational framework

2019 ◽  
Vol 6 (4) ◽  
pp. 739-750 ◽  
Author(s):  
Nilankush Acharya ◽  
Kalidas Das ◽  
Prabir Kumar Kundu
Keyword(s):  
Heat Transfer ◽  
Entropy Generation ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Bejan Number ◽  
Computational Framework ◽  
Performance Of Heat Transfer ◽  
Dimensional Shape ◽  
Liquid Rocket ◽  
Heat Transport Mechanism

Abstract An investigation has been carried out to demonstrate the performance of heat transfer and entropy generation in a regenerative cooling channel of a rocket engine. The Nanofluid flow in composition with ferrous nanoparticles has been utilized. Foremost equations are reduced to its non-dimensional shape using similarity renovation and sketched out using variational iterative method (VIM). Impression of the pertinent factors on hydrothermal performance has been brought forwarded via tables and graphs. Favourable comparison originates the basis of our present work. Result communicates that non-dimensional entropy generation amplifies in response to the parameter R and Bejan number intensifies for the parameter N. Significance or application of the present literature is to provide kerosene based ferrofluid as a coolant of rocket engine and how pertinent factors affect the entropy inside the system. Parametric study of this investigation will aid aerospace engineers to design the regenerative equipment in an effective way. Highlights Heat transfer and entropy generation in a nozzle of liquid rocket engine has been studied. Ferrous nanoparticles (CoFe2O4) with kerosene as base fluid have been used. Resulting equations has been solved using VIM. Non-dimensional entropy generation amplifies in response to the parameter R. Influence of ϕ reduces the Nusselt number.

Unsteady Side-Load Evolution in a Liquid Rocket Engine Nozzle

2020 ◽  
Vol 57 (2) ◽  
pp. 391-397
Author(s):  
S. B. Verma ◽  
Oskar Haidn
Keyword(s):  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Side Load ◽  
Liquid Rocket

Rotordynamic analysis of a high thrust liquid rocket engine fuel (Kerosene) turbopump

2013 ◽  
Vol 26 (1) ◽  
pp. 169-175 ◽  
Author(s):  
Seong Min Jeon ◽  
Hyun Duck Kwak ◽  
Suk Hwan Yoon ◽  
Jinhan Kim
Keyword(s):  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Engine Fuel ◽  
Liquid Rocket ◽  
High Thrust

Measurements of Rotordynamic Coefficients of Hybrid Bearings With (a) a Plugged Orifice, and (b) a Worn Land Surface

2002 ◽  
Vol 124 (2) ◽  
pp. 363-368 ◽  
Author(s):  
F. Laurant ◽  
D. W. Childs
Keyword(s):  
Test Data ◽  
Land Surface ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Test Results ◽  
Rotordynamic Coefficients ◽  
Hybrid Bearing ◽  
Liquid Rocket

Test results are presented for the rotordynamic coefficients of a hybrid bearing that is representative of bearings for liquid-rocket-engine turbopump applications. The bearing is tested in the following two degraded conditions: (a) one of five orifices plugged, and (b) a locally enlarged clearance to simulate a worn condition. Test data are presented at 24,600 rpm, with supply pressures of 4.0, 5.5, and 7.0 MPa, and eccentricity ratios from 0.1 to 0.5 in 0.1 increments. Overall, the results suggest that neither a single plugged orifice nor significant wear on the bearing land will “disable” a well-designed hybrid bearing. These results do not speak to multiple plugged orifices and are not an endorsement for operations without filters to prevent plugging orifices.

Characterization of Rotating Cavitation in a High Speed Inducer of Liquid Rocket Engine

2011 ◽  
Vol 320 ◽  
pp. 196-201
Author(s):  
Fei Tang ◽  
Li Jia Wen
Keyword(s):  
High Speed ◽  
High Performance ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Blade Surface ◽  
Cavitation Phenomenon ◽  
Flow Fluctuations ◽  
Blade Cascade ◽  
Liquid Rocket

Rotating cavitation is one of the most important problems in the development of modern high performance rocket pump inducers. In this paper, a numerical simulation of rotating cavitation phenomenon in a 2D blade cascade of liquid rocket engine inducer was carried out using a mixture model based on Rayleigh-Plesset equation. The purpose is to investigate the characterization of rotating cavitation in a high speed inducer. The results show that when sub-synchronous rotating cavitation occurs, the speed for the length of the blade surface cavitation is lower than the speed frequency of rotation shaft with the same direction. The external aspect is that the pressure at the upstream of blades changes synchronous. Thus, the generation of sub-synchronous rotating cavitation is closely related to the changes of flow angel which caused by the flow fluctuations. Hence, elimination of the flow rate redistribution among the flow channel can effectively suppress the occurrence of this phenomenon.

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