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

Automatic Unloading Liquid Rocket Engine Fuel Feed System Booster Pump Radial Thrust Bearings from Axial Force

2021 ◽  
pp. 54-61
Author(s):  
S.F. Timushev ◽  
A.A. Frolov
Keyword(s):  
Axial Force ◽  
High Speed ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Engine Fuel ◽  
Fuel Feed ◽  
Thrust Bearings ◽  
Booster Pump ◽  
Liquid Rocket ◽  
Radial Thrust

Increasing the suction capacity, efficiency and energy parameters of high-speed pumps is an important task in the development of power systems in the aerospace industry, as well as in their application in energy and oil production. With improved cavitation properties, the pumps can operate at a higher shaft speed, and at its given value - with lower cavitation reserves, i.e. at a reduced inlet pressure. When the shaft speed increases, the pump weight and overall dimensions decrease. To increase the anti-cavitation qualities of pumps in the power system, auxiliary (booster) pumping units are used, creating the pressure necessary for the cavitation-free operation of high-pressure and high-speed main pumps of the engine fuel supply system. In accordance with its purpose, the booster pump must provide the required supply pressure of the specified flow rate at the lowest possible liquid pressure at the inlet. At the same time, the efficiency of the booster pump unit should be maximum, and the overall dimensions and weight should be minimal. The last two characteristics predetermine the maximum possible number of revolutions of the pump shaft. Ensuring the operability of the ball-bearing supports of the fuel supply units is one of the most important and complex tasks in the development of modern and promising liquid rocket engines (LRE), especially reusable ones. This task has always been one of the priorities in the fine-tuning the fuel feed units of such engines. The article proposes a method for calculating and controlling the unloading liquid rocket engine booster pump radial thrust bearings from axial force. The method can be applied in the entire range of liquid rocket engine calculations. The further development of this work will be mathematical modeling of the operation of the booster pump automatic axial force unloading.

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

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.

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