In the recent century, rocket engine development has witnessed a vast number of technological advances made in the field. Rocket engines have been very crucial technological equipment for the human race to space. With the change in technology and requirement, the turbopump system has been crucial for the development of the rocket engine. This article provides insight into a technological improvement over the last century and gives a brief note of some of the crucial engines in humankind's history. This research highlights the roadmap to understanding the different categories of turbopump systems within liquid propulsion rocket engines and lays out a comparative study of the different turbopump configurations. This article will help researchers in understanding and appraising the works with their existing results. Further, this article will help newcomers and different researchers in getting an overview of turbopump and the various existing works performed on it and related to this field over the years. 

Development Advances in Liquid Rocket Engines Turbopump: A Review

This article explains how the use of impeller cavitation locking conditions in the presence of a cavitation scale effect provides a means of substantially reducing the number of tests required to obtain the cavitation characteristics for several fixed values of one of the liquid parameters causing the appearance of the cavitation scale effect. By using the method proposed, 4 tests are required in total. Points out that the new method of testing the pump is less laborious since it does not require maintaining constant to a high accuracy for the total test period the parameters of the pumped liquid which determine the cavitation scale effect.

Determination of the cavitation characteristics of vane pumps in the presence of a ''scale effect''

Results of a test program to confirm the prediction of performance and operational characteristics of a prototype twin-spool (integrated low-speed inducer, high-speed pump) hydrogen turbopump at zero net positive suction pressure (NPSP: saturated fluid in the propellant tank) are described. Steady-state and simulated engine transient performance at NPSP values from 20 psi to 0 psi, with hydrogen temperatures of 37°R to 38°R, and with substantial vapor ingestion, are summarized over the operating range of the pump. This member of the low-speed inducer-equipped turbopump family incorporates an inducer forward of the main pump which is driven through a coaxial shaft by a single-stage gas turbine located aft of the main turbine. In previous hydrogen testing, the positive NPSP main turbopump exhibited inadequate pressure rise and flow range at zero NPSP. Testing with the low-speed stage provided a direct evaluation of its addition upon over-all turbopump performance and behavior*

Evaluation of a twin-spool hydrogen turbopump at zero NPSP

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Evaluation of a twin-spool hydrogen turbopump at zero NPSP