Design Procedure of Centrifugal Compressors (original) (raw)
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DESIGN AND NUMERICAL ANALYSIS OF A CENTRIFUGAL COMPRESSOR.
2020
Centrifugal compressors are used widely in various range of aero-engine applications both small and medium-sized. And its performance affects the working state of the engine. So in this thesis I am going to briefly explain how the performance affects the working state using three different solutions. The first is the normal numerical solution using compal, in this solution, working conditions were added to get performance curves which I will discuss later in this thesis. The second solution is the blade to blade solution and the third solution is the computational fluid dynamics (CFD) solution. Computational Fluid Dynamics is usually used in centrifugal compressor design. Computational fluid dynamics provides extensive optimization chances for the compressor design instead of designing the centrifugal compressor. The design process is still an important part of the compressor developments. The wide range of design subjects represents a very not so easy design world for centrifugal compressor designers. So, a few basic information for centrifugal design is still quite important. The impeller is the most useful part of the centrifugal stage. Designing a very efficiency centrifugal impeller with a wide operation range can ensure overall design success. With these three solution how briefly explain how they affect the working state of the centrifugal compressor. Keywords: Centrifugal compressor; Mass flow; Pressure ratio; CFD; Overall performance. Blade to Blade; Compal solution.
A Review on Centrifugal Compressor Design Methods
The use of turbochargers has increased in response to strengthened automotive exhaust emission and fuel consumption regulations for global environmental protection. Most centrifugal compressors are required to operate over a broad range of flow rates and to provide a high pressure ratio with high efficiency. The internal flow of a centrifugal compressor is very problematic with 3-dimensional and unsteady flow phenomena, and the analysis of flow phenomena and expansion of the operational range are difficult problems. Review is done for gathering the efficient method for designing and analyzing the centrifugal compressor. In order to meet these demands the application of variable geometry techniques is often considered and applied.
Some Aerodynamic Considerations in the Design of Centrifugal Compressor Impellers
Abstract: A simple one dimensional approach to determine the size of the centrifugal impeller for maximum through flow has been indicated. This design procedure does not mean that the centrifugal impeller could be finally decided on the results obtained from this article. It must be borne in mind that this only deals with some aspects of the design and in itself is not a complete one by which the impeller could have its final shape and size. The major idea of introducing this paper is to highlight the importance of some of the parameters that go towards influencing the design of the centrifugal impeller.
Aerodynamic and geometric optimization for the design of centrifugal compressors
International Journal of Heat and Fluid Flow, 1985
Maximizing efficiency is the main goal in centrifugal compressor design. Thus a computer code has been developed to optimize geometric and fluid dynamic variables with respect to several design constraints. Computations are performed with an adiabatic one-dimensional approach using state-of-the-art loss and slip correlations. The optimization takes into account mechanical stress limits. Results with different loss and slip correlations are compared with the available experimental data. Changes in optimum efficiency and specific speed due to variations of mass flow rate and pressure ratio are also presented and discussed together with the trends of the optimum geometric features.
Numerical Simulation of a Centrifugal Compressor
In this paper, the tip clearance effects on flow field of a low speed centrifugal compressor without and with partial shroud (PS) fitted on to the rotor blade tip at three values of tip clearance, viz. = 2.2%, 5.1% and 7.9% of rotor blade height at the exit at three flow coefficients, namely, = 0.18, 0.28, and 0.34, was studied. Based on the theory of computational fluid dynamics (CFD), performance curves and parameter distributions of the compressor were obtained from the 3-D numerical simulation by using ANSYS CFX 15.0. The centrifugal compressor in aerodynamic requirement is that edge velocities along the impeller channel passage surfaces like hub, shroud, pressure and suction surfaces vary smoothly without sudden decelerations, which cause flow separation leading to losses. Using the periodic boundaries and defined flow conditions at inflow / exit flow and blade rotations, the turbulent viscous flow between blade channels are computed. The efficiency related parameters using average quantities, besides flow pattern in terms of velocities, streamlines and pressure distribution on blade surfaces are graphically interpreted. An attempt is also made to study the influence of pressure loads on structural deformations in the chosen blade profile. This paper highlights aero-mechanical features of centrifugal impeller obtained from several numerical simulations, which are expected to provide a sound basis for further investigations.
An Investigation on the Performance Characteristics of a Centrifugal Compressor
The design and off-design performance characteristics of single stage centrifugal compressor consisting of 12 vanes impeller interfacing with 11 vanes diffuser have been studied experimentally and numerically. The impeller has been designed and developed with radial exit, 30o inlet blade angle (with tangent), 77 mm diameter and the discharge volute considering constant mean flow velocity. The performance of the compressor at varying capacity (60 to 120 % of design) by controlling the discharge valve and with the variation of rotating speed (15000 to 35000 rpm) by regulating speed of the coupled gas turbine has been conducted at the recently developed test rig. The numerical simulation has been done by adopting viscous Reynolds Average Navier-Stokes (RANS) equations with and without Coriolis Force & Centrifugal Force in rotating reference frame (impeller) and stationary reference frame (casing) respectively utilizing CFD software Fluent 14. The flow around a single vane of impeller interfacing with single vane of diffuser, the rotational periodicity and sliding mesh at the interfacing zone between rotating impeller and stationery diffuser are considered. Non dimensional performance curves derived from experimental and numerical results are presented and compared. The numerical results are found to match very closely with the experimented data near the design point and deviation is observed at the both side of the designed operating point. Non-uniform pressure profiles towards the impeller exit and strong cross flow from blade to blade are detected at low flow operating conditions. Total pressure, static pressure and velocity distributions at design and off design operation obtained from the CFD results are analysed and presented here.
Energies, 2021
Turbomachinery with double counter-rotating impellers offers more degrees of freedom in the choice of design and control parameters compared to conventional machines. For these innovative machines, the literature review shows that more publications concerning axial type turbomachines are available than centrifugal ones. This work deals with a design and experimental performance analysis, applied to two counter-rotating impellers of a centrifugal compressor “CRCC”. CRCC was designed with a specifically developed tool based on mean-line approach coupled with optimization algorithms and a stream-curvature through-flow method to satisfy the design criteria. This paper presents an experimental validation of the CRCC design tool and its performances against the baseline “SR”, composed of one centrifugal impeller and a volute for which experimental data are available. CRCC numeric simulations are also validated by experimental data. For a fair comparison between CRCC and SR, the same volut...
유체기계 연구개발 발표회 논문집, 2015
The prediction and design of the aerodynamic performance of a compressor are crucial requirements to properly evaluate the aerodynamic performance and characteristics during preliminary design of a centrifugal compressor because it is not clear to figure out the internal flow property of a compressor including complicated three dimensional turbulent flow. In this study the industrial centrifugal compressor was calculated for variations of mass flow and blade Mach number with 2 cases of different number of diffuser vanes. One of the major cause of the impeller loss is the pressure drop when the operating mass flow rate closes to choking flow coefficient. Momentum transfer and loss characteristics of the impeller are important to understand impeller characteristics. The method was suggested to estimate the impeller performance characteristics.
Parametric Study on Impeller Exit Blade Width Variation on Centrifugal Compressor Performance
2017
The work addresses an imperious issue of enhancing centrifugal flow compressor performance by modifying the impeller blade design. Recent advancements have reported in enhancement of centrifugal compressor performance by the impeller with extended shroud by 10%. Present work extends to explore the significance geometric and design parametric variation of varying exit blade width and its implications on the compressor performance. Numerical simulations were carried out for the selected cases of extended shroud by 10% along with the width at exit blade width increased by 5% and 10%. The numerical predictions were validated with the compressor theory and matched reasonably well. Results indicates higher static pressure rise with reduced losses and increased efficiency with exit blade width variation. The stagnation pressure distribution increases at exit of diffuser due to rotating vaneless diffuser. The presence of rotating vaneless diffuser yields smooth entry flow profiles, thereby ...