Abstract
The article presents a refining method for a two-stage screw centrifugal pump by the joint usage of mathematical optimization software IOSO, meshing complex NUMECA and CFD software ANSYS CFX. The pump main parameters: high-pressure stage rotor speed was 13300 rpm; low-pressure rotor speed was 3617 rpm by gearbox; inlet total pressure was 0.4 MPa; outlet mass flow was 132.6 kg/s at the nominal mode. This article describes the process of simplifying the calculation model for the optimization. The parameters of camber lines of the low-pressure impeller, transition duct, and high-pressure impeller blades for two sections (hub and shroud) were chosen as optimization parameters. The blades of low-pressure impeller, transition duct and high-pressure impeller have changed during optimization. The optimization goal was the increase of the pump efficiency with preservation or slight increase in the pressure head. The efficiency was increased by 3%.
Highlights
Pumps are the integral part of both industrial production and everyday human life [1]
Simplified models were calculated with the Mass Flow boundary condition, since changing the geometry of the lowpressure impeller (LPI), transferring passage (TP), and especially of the HPI can lead to a displacement of the pump characteristics
Checking the optimal model with KID and volute outlet duct (VOD) pump parts revealed a slight increase in efficiency by 0.2% with decrease in pressure head by 1.5%
Summary
Pumps are the integral part of both industrial production and everyday human life [1]. A special place is occupied by the screw centrifugal pumps as the devices for supplying liquid components to the rocket engine chamber. In this case, the turbo-pump unit requires both high performance and high reliability of operation. The turbo-pump unit requires both high performance and high reliability of operation It is known [2] that more than 70% of crashes of liquid propellant rocket engine occurred due to the breakdown in the turbo-pump units. Used turbo-pump units for liquid propellant rocket engines (LPRE) were designed in the 1960-1970. After validating the simulation results, these CFD models can be used to study the effect of the pump parameters on its performance. This can be achieved by changing the geometry of LPI, TP and HPI blades
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