Turbo-pump with isolated two stage impellers for future rocket engine (Trial to drive impellers independently)

2008 ◽  
Vol 17 (1) ◽  
pp. 28-34 ◽  
Author(s):  
Toshiaki Kanemoto ◽  
Makoto Shimojyo ◽  
Ryunosuke Kawashima ◽  
Daisuke Tanaka ◽  
Akira Inagaki ◽  
...  
Keyword(s):  
Rocket Engine ◽  
Two Stage ◽  
Turbo Pump

A study into the feasibility of using the oxygen-hydrocarbon engine 11D58M as a basis for development of a high-performance multifunctional gas-generatorless rocket engine with oxygen cooling

2019 ◽  
pp. 67-80
Author(s):  
Boris A. Sokolov ◽  
Nikolay N. Tupitsyn
Keyword(s):  
Film Cooling ◽  
High Performance ◽  
Rocket Engine ◽  
Hydrocarbon Fuel ◽  
Gas Generator ◽  
Automatic Equipment ◽  
The Us ◽  
Upper Stage ◽  
Pump Assembly ◽  
Turbo Pump

The paper presents results of engineering studies and research and development efforts at RSC Energia to analyze and prove the feasibility of using the mass-produced oxygen-hydrocarbon engine 11D58M with 8.5 ton-force thrust as a basis for development of a high-performance multifunctional rocket engine with oxygen cooling and 5 ton-force thrust, which is optimal for upper stages (US), embodying a system that does not include a gas generator. The multi-functionality of the engine implies including in it additional units supporting some functions that are important for US, such as feeding propellant from US tanks to the engine after flying in zero gravity, autonomous control of the engine automatic equipment to support its firing, shutdown, adjustments during burn and emergency protection in case of off-nominal operation, as well as generating torques for controlling the US attitude and stabilizing it during coasting, etc. Replacing conventional engine chamber cooling that uses high-boiling hydrocarbon fuel with the innovative oxygen cooling makes it possible to get rid of the internal film cooling circuits and eliminate their attendant losses of fuel, while the use of the oxygen gasified in the cooling circuit of the chamber to drive the turbo pump assembly permits to design an engine that does not have a gas generator. Key words: Multifunctional rocket engine, oxygen cooling, gas-generatorless design, upper stage.

LRE Fault Detection and Isolation Based on Fuzzy Direction Neural Network

2015 ◽  
Vol 727-728 ◽  
pp. 880-883
Author(s):  
Min Chao Huang ◽  
Bao Yu Xing
Keyword(s):  
Neural Network ◽  
Fault Detection ◽  
Fuzzy Sets ◽  
Fuzzy Set ◽  
Rocket Engine ◽  
Fault Detection And Isolation ◽  
Liquid Rocket Engine ◽  
Direction Vector ◽  
Liquid Rocket ◽  
Turbo Pump

A fuzzy directions neural network used for fault detection and isolation (FDI) of a liquid rocket engine (LRE) is presented in this paper. Neural network utilizes fuzzy sets as engine fault classes. Each fuzzy set is an aggregate of fuzzy direction bodies. A fuzzy direction body is described by a direction vector, an included angle and two radii. FDI simulation of the turbo-pump fed liquid rocket engine demonstrates the strong qualities of the fuzzy direction neural network.

G606 On the Compact Design of Rocket Engine Turbo Pump(2)

2006 ◽  
Vol 2006 (0) ◽  
pp. _G606-1_-_G606-4_
Author(s):  
Hiroyoshi WATANABE ◽  
Yoshiki YOSHIDA
Keyword(s):  
Rocket Engine ◽  
Compact Design ◽  
Turbo Pump

Turbo-Pump Fed Miniature Rocket Engine

2005 ◽  
Author(s):  
C. Scharlemann ◽  
K. Marhold ◽  
Martin Tajmar ◽  
Pierpaolo Miotti ◽  
C. Guraya ◽  
...  
Keyword(s):  
Rocket Engine ◽  
Turbo Pump

scholarly journals Wear Diagnostics of the Thrust Bearing of NK-33 Turbo-Pump Unit on the Basis of Single-Coil Eddy Current Sensors

Sensors ◽  
2021 ◽  
Vol 21 (10) ◽  
pp. 3463
Author(s):  
Viktor Belosludtsev ◽  
Sergey Borovik ◽  
Valeriy Danilchenko ◽  
Yuriy Sekisov
Keyword(s):  
Eddy Current ◽  
Rotational Speed ◽  
Thrust Bearing ◽  
Rocket Engine ◽  
Pump Unit ◽  
Original Solution ◽  
Single Coil ◽  
Current Sensors ◽  
Linear Conductor ◽  
Turbo Pump

The problem of early wear diagnostics of the combined journal-and-thrust bearing of the turbo-pump unit (TPU) of the liquid-propellant rocket engine NK-33 is considered. A feature of the problem is the significant restriction on modifications of the power plant’s design. The original solution based on replacing the standard induction sensors of the turbo-pump rotational speed currently used in TPU by single-coil eddy current sensors (SCECS) with sensitive elements in the form of a segment of a linear conductor is proposed. The SCECS provide the monitoring of the axial displacement of the shaft in the thrust bearing, which characterizes the state of the unit and increases with the bearing wear. The function of the TPU shaft’s rotational speed measuring also remains. The article describes the proposed approach as well as a laboratory prototype of the system for early detection of the TPU thrust bearing’s wear. The results of the prototype research that confirm the feasibility of the proposed approach are analyzed.

A Panel Method for the Hydrodynamic Performance Prediction of a Water-jet and an Inducer

2012 ◽  
Author(s):  
Spyros A. Kinnas ◽  
Shu-Hao Chang ◽  
Alokraj Valsaraj
Keyword(s):  
Performance Prediction ◽  
Present Method ◽  
Rocket Engine ◽  
Water Jet ◽  
Panel Method ◽  
Hydrodynamic Performance ◽  
Jet Pump ◽  
Time Step ◽  
Flow Solver ◽  
Turbo Pump

This paper presents the analyses of the hydrodynamic performance for a marine water-jet propulsor and a rocket engine turbo pump inducer by using a potential flow solver based on a low order panel method. The steady and unsteady fully-wetted and cavitating simulations for the water-jet rotor only problem are investigated and the steady fully-wetted simulation for the inducer is studied in this paper. The convergence studies of rotor averaged cavitating circulation distributions with number of panels on the blade and with different time step sizes are presented in the water-jet case. Finally, the predictions of the hydrodynamic performance for the water-jet pump and the inducer from the present method are validated against existing experimental data or numerical results from RANS solvers.

Failure Analysis of Ball-Bearing of Turbo-Pump Used in Liquid Rocket Engine

2015 ◽  
Vol 830-831 ◽  
pp. 709-712 ◽  
Author(s):  
Venkateswarlu Vartha ◽  
M.S. Arun Kumar ◽  
Saxon Mathew ◽  
Rajan Aneesh ◽  
John Bejoy ◽  
...  
Keyword(s):  
Failure Analysis ◽  
Ball Bearing ◽  
Rocket Engine ◽  
Operating Conditions ◽  
Rolling Contact ◽  
Liquid Rocket Engine ◽  
Bearing Failure ◽  
Deep Groove ◽  
Liquid Rocket ◽  
Turbo Pump

Rolling contact bearings often referred as antifriction bearings are found in many applications where rotating components are involved. Extreme operating conditions, counterfeit or inferior quality bearings, inadequate lubrication, etc often lead to bearing failures. Each rolling contact bearing failure leaves traces of evidences on what caused its failure. Failure analysis of one such bearing is the subject of this paper.One of the engine ground tests was aborted due to the failure of a self-aligning deep groove ball bearing used in turbo-pump of a liquid rocket engine. Series of engine ground tests are conducted as a part of injector acceptance for a liquid rocket engine. The bearing failure occurred in the seventh engine test of one of such series of ground tests. The bearing mentioned here is made of SAE 52100 steel. Post-test hardware inspection revealed that the bearing and the dynamic seals on either side of the bearing are in failed condition. Inner race of bearing was found blackish in appearance with indentation and corrosion marks. Localized black spots were observed in outer race. Bearing balls were found in deformed condition. The paper highlights the failure analysis of the bearing, root cause of the bearing failure and recommendations to avoid such failures.

scholarly journals 1511 Centrifugal Turbo Pump with Two Stage Impellers Driven by Isolated Motor

2005 ◽  
Vol 2005 (0) ◽  
pp. 213
Author(s):  
Toshiaki KANEMOTO ◽  
Makoto SHIMOJO ◽  
Yoshinori EGUCHI
Keyword(s):  
Two Stage ◽  
Turbo Pump
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