Effect of Exit Pressure Pulsation on the Performance and Stability Limit of a Turbocharger Centrifugal Compressor

2016 ◽  
Author(s):  
Maria Esperanza Barrera-Medrano ◽  
Peter Newton ◽  
Ricardo Martinez-Botas ◽  
Srithar Rajoo ◽  
Isao Tomita ◽  
...  
Keyword(s):  
Centrifugal Compressor ◽  
Flow Instability ◽  
Combustion Engine ◽  
Stability Limit ◽  
Intermittent Flow ◽  
Limited Information ◽  
Surge Margin ◽  
Compressor Surge ◽  
Compressor Inlet ◽  
The Stability

It is well known that compressor surge imposes a significant limit on the flow range of a turbocharged internal combustion engine. The centrifugal compressor is commonly placed upstream of the inlet manifold and hence, it is exposed to the intermittent flow regime of the inlet valves. Surge phenomena has been well studied over the past decades, there still remains limited information with regards to the unsteady impact caused by the inlet valves. This study presents an experimental evaluation of such a situation. Engine representative pulses are created by a downstream system comprising a large volume, two rotating valves, a throttle valve and the corresponding pipe network. Different pulsation levels are characterized by means of their frequency and the corresponding amplitude at the compressor inlet. The stability limit of the system under study is evaluated with reference to the parameter B proposed by Greitzer [7–9]. B describes the dynamics of the compression system in terms of volume, area, equivalent length and compressor tip speed as well as the Helmholtz frequency of the system. For a given compressor, as B goes beyond a critical value, the system will exhibit surge as the result of the flow instability progression. The reduced frequency analysis shows that the scroll-diffuser operates in an unsteady regime, while the impeller is nearly quasi-steady. In the vicinity of the surge point, under a pulsating flow, the instantaneous operation of the compressor showed significant excursions into the unstable side of the surge line. Furthermore, it has been found that the presence of a volume in the system has the greatest effect on the surge margin of the compressor under the unsteady conditions.

Effect of Exit Pressure Pulsation on the Performance and Stability Limit of a Turbocharger Centrifugal Compressor

2016 ◽  
Vol 139 (5) ◽  
Author(s):  
Maria Esperanza Barrera-Medrano ◽  
Peter Newton ◽  
Ricardo Martinez-Botas ◽  
Srithar Rajoo ◽  
Isao Tomita ◽  
...  
Keyword(s):  
Centrifugal Compressor ◽  
Flow Instability ◽  
Combustion Engine ◽  
Axial Flow ◽  
Stability Limit ◽  
Rotating Stall ◽  
Intermittent Flow ◽  
Limited Information ◽  
Compression System ◽  
Axial Flow Compressors

It is well known that compressor surge imposes a significant limit on the flow range of a turbocharged internal combustion engine. The centrifugal compressor is commonly placed upstream of the inlet manifold, and hence, it is exposed to the intermittent flow regime of the inlet valves. Surge phenomena have been well studied over the past decades, and there still remains limited information with regard to the unsteady impact caused by the inlet valves. This study presents an experimental evaluation of such a situation. Engine representative pulses are created by a downstream system comprising a large volume, two rotating valves, a throttle valve, and the corresponding pipe network. Different pulsation levels are characterized by means of their frequency and the corresponding amplitude at the compressor inlet. The stability limit of the system under study is evaluated with reference to the parameter B proposed by Greitzer (1976, “Surge and Rotating Stall in Axial Flow Compressors—Part II: Experimental Results and Comparison With Theory,” ASME J. Eng. Power, 98(2), pp. 199–211; 1976, “Surge and Rotating Stall in Axial Flow Compressors—Part I: Theoretical Compression System Model,” ASME J. Eng. Power, 98(2), pp. 190–198). B describes the dynamics of the compression system in terms of volume, area, equivalent length, and compressor tip speed as well as the Helmholtz frequency of the system. For a given compressor, as B goes beyond a critical value, the system will exhibit surge as the result of the flow instability progression. The reduced frequency analysis shows that the scroll diffuser operates in an unsteady regime, while the impeller is nearly quasi-steady. In the vicinity of the surge point, under a pulsating flow, the instantaneous operation of the compressor showed significant excursions into the unstable side of the surge line. Furthermore, it has been found that the presence of a volume in the system has the greatest effect on the surge margin of the compressor under the unsteady conditions.

On the Effect of Engine Pulsations on the Performance of a Turbocharger Centrifugal Compressor

2019 ◽  
Vol 141 (8) ◽  
Author(s):  
Maria Esperanza Barrera-Medrano ◽  
Ricardo Martinez-Botas ◽  
Isao Tomita ◽  
Seiichi Ibaraki
Keyword(s):  
Centrifugal Compressor ◽  
Flow Instability ◽  
Combustion Engine ◽  
Stability Limit ◽  
Pulse Frequency ◽  
Pulse Parameter ◽  
Surge Margin ◽  
Valve Motion ◽  
Storage Volume ◽  
Inlet Manifold

In an internal combustion engine, the centrifugal compressor is placed upstream of the inlet manifold and therefore, it is exposed an unsteady flow regime caused by the inlet valves of the cylinder arrangement. This valve motion sets a pulsating state at the compressor exit, having greater influence when the operation is near the surge margin of the compressor. This paper presents the experimental results of the evaluation of the surge dynamics on a compressor with induced downstream pulsating flow. Different pulsation levels are achieved by the variation of three different parameters on the induced pulse: pulse frequency, amplitude, and system storage volume (plenum). Each pulse parameter was evaluated independently in order to assess its effect on the compressor stability limit. The main effect on the surge margin of the compressor was found to be due to the presence of a storage volume in the system for all cases (steady/pulsating condition) and at all frequencies. It was found that the magnitude of the pulse frequency determines the hysteresis behavior of the system that leads to a phase difference between the convected terms and the acoustic dominated terms, and therefore this affects the onset of flow instability, surge, in the compression system under study.

Enhancement of Centrifugal Compressor Operating Range by Control of Inlet Recirculation With Inlet Fins

2016 ◽  
Vol 138 (10) ◽  
Author(s):  
Hideaki Tamaki ◽  
Masaru Unno ◽  
Ryuuta Tanaka ◽  
Satoshi Yamaguchi ◽  
Yohei Ishizu
Keyword(s):  
Centrifugal Compressor ◽  
Stability Limit ◽  
Great Promise ◽  
Low Speed ◽  
Operating Range ◽  
Surge Margin ◽  
Compressor Inlet ◽  
Qualitative Effect ◽  
Computational Fluid Dynamics Cfd ◽  
The Stability

The operating points of a turbocharger compressor tend to approach or cross its surge line while an engine is accelerating, particularly under low-engine speed conditions, hence the need for an acceptable surge margin under low compressor-speed conditions. A method shifting the stability limit on a compressor low-speed line toward a lower flow rate is expected and inlet recirculation is often observed in a centrifugal compressor with a vaneless diffuser near a surge and under a low compressor-speed condition. First, examples of inlet recirculation were introduced in this paper, whereupon the effect of inlet recirculation on compressor characteristic was discussed by 1D consideration and the potential shown for growth of inlet recirculation to destabilize compressor operations. Accordingly, this study focused on suppressing the effect of inlet recirculation on compressor characteristics using small fins mounted in a compressor-inlet pipe, and examining whether they enhance the compressor operating range under low-speed conditions. Small fins are known as inlet fins in this paper. According to test results, they showed great promise in enhancing the compressor operating range during inlet recirculation. Besides, attempts were also made to investigate the qualitative effect of inlet fins on flow fields using computational fluid dynamics (CFD) and the disadvantages of inlet fins were also discussed.

Enhancement of Centrifugal Compressor Operating Range by Control of Inlet Recirculation With Inlet Fins

2015 ◽  
Author(s):  
Hideaki Tamaki ◽  
Masaru Unno ◽  
Ryuuta Tanaka ◽  
Satoshi Yamaguchi ◽  
Yohei Ishizu
Keyword(s):  
Centrifugal Compressor ◽  
Stability Limit ◽  
Great Promise ◽  
Low Speed ◽  
Operating Range ◽  
Surge Margin ◽  
Compressor Inlet ◽  
Qualitative Effect ◽  
The Stability ◽  
Operating Points

The operating points of a turbocharger compressor tend to approach or cross its surge line while an engine is accelerating, particularly under low-engine speed conditions, hence the need for an acceptable surge margin under low compressor-speed conditions. A method shifting the stability limit on a compressor low-speed line toward a lower flow rate is expected and inlet recirculation is often observed in a centrifugal compressor with a vaneless diffuser near a surge and under a low compressor-speed condition. First, examples of inlet recirculation were introduced in this paper, whereupon the effect of inlet recirculation on compressor characteristic was discussed by 1-D consideration and the potential shown for growth of inlet recirculation to destabilize compressor operations. Accordingly, this study focused on suppressing the effect of inlet recirculation on compressor characteristics using small fins mounted in a compressor-inlet pipe, and examining whether they enhance the compressor operating range under low-speed conditions. Small fins are known as inlet fins in this paper. According to test results, they showed great promise in enhancing the compressor operating range during inlet recirculation. Besides, attempts were also made to investigate the qualitative effect of inlet fins on flow fields using CFD and the disadvantages of inlet fins were also discussed.

Aerodynamics of a Centrifugal Compressor With a Double Sided Impeller

2011 ◽  
Author(s):  
Vai-Man Lei
Keyword(s):  
Centrifugal Compressor ◽  
Stability Limit ◽  
Low Flow ◽  
Recirculation Flow ◽  
Flow Capacity ◽  
Operation Modes ◽  
Compressor Inlet ◽  
Parallel Mode ◽  
The Stability ◽  
Ported Shroud

A double sided impeller, which consists of two impellers arranged in a back-to-back configuration with the backdisks eliminated, enables a single centrifugal compressor to have flow capacity similar to two compressors working in parallel but with a smaller packaging size. It reduces inertia of the rotating group and helps improve transient response. The smaller impeller diameter also enhances turbine performance by improving the compressor-turbine matching. These attributes are very attractive for automotive turbocharging applications. As a consequence of a common compressor inlet and diffuser, the two compressor sides interact and two operation modes exist. In the parallel mode, the two compressor sides work under comparable condition and the overall compressor behaves similar to a conventional compressor. As flow rate is reduced below a transition value, the system operates in a single-compressor mode with one compressor side flowing significantly more. The compressor side that flows more operates away from the stability limit and the side with low flow remains stable because of heavy recirculation flow with a ported shroud. Characteristics of the two operation modes are elucidated with test and CFD data.

A New Inlet Distortion and Pressure Loss Based Design of an Intake System for Stationary Gas Turbines

2013 ◽  
Author(s):  
Jose Rodriguez ◽  
Stephan Klumpp ◽  
Thomas Biesinger ◽  
James O’Brien ◽  
Tobias Danninger
Keyword(s):  
Gas Turbines ◽  
Inlet System ◽  
Inlet Distortion ◽  
Surge Margin ◽  
Compressor Surge ◽  
Compressor Inlet ◽  
The Face ◽  
Flow Quality ◽  
Inlet Manifold ◽  
Distortion Parameters

This paper presents a new design for a Compressor Inlet Manifold (CIM) for a land-based power generation Gas Turbine (turbine). The CIM is the component of the Inlet System (IS) that is directly connected to the turbine via the Compressor Inlet Case (CIC). The design philosophy is to use low fidelity but fast and automated CFD (Computational Fluid Dynamics) for design iterations and then confirm the design with detailed higher accuracy CFD before proceeding to engine tests. New design features include contouring the wall to minimize areas of flow separation and associated unsteadiness and losses, and improvement of the flow quality into the compressor. The CIM in a land-based turbine acts as a nozzle whereas the inlet of an aircraft acts as a diffuser. The flow also enters the CIM at 90 deg to the engine axis. This leads to a pair of counter rotating vortices at the compressor inlet. Three main sources of flow distortions at the face of the compressor are identified: flow separations at outer walls of the IS and CIM struts and the counter rotating vortices. The higher accuracy CFD analysis including the complete IS, CIM and the first compressor stage, simulates the effect of these distortions on the compressor front stage at design conditions. A range of inlet distortion parameters are used to evaluate the inlet design. The well known DC60 based criterion derived from aircraft engines and other less known but published parameters are able to give an indication of how the compressor surge margin of stationary gas turbines is affected.

Stability Analysis of Chatter System on Ultrasonic Honing

2013 ◽  
Vol 712-715 ◽  
pp. 1241-1247
Author(s):  
Yun Peng Shao ◽  
Xi Jing Zhu ◽  
Meng Liu ◽  
Zhen Liu
Keyword(s):  
Combustion Engine ◽  
Damping Ratio ◽  
Stability Limit ◽  
Cylinder Liner ◽  
Spindle Speed ◽  
Machining System ◽  
Motion Speed ◽  
The Stability ◽  
Stiffness And Damping

The chatter caused by the inner factors of the machining system in the ultrasonic honing process would seriously affect the surface quality of combustion engine. A dynamical model of ultrasonic honing chatter system was established, which involved with ultrasonic honing mechanism and dynamic honing depth, the relationship between the limit honing width and honing speed was deduced based on the theory of regenerative chatter; the simulation was carried out to obtain the effect of different parameters including stiffness coefficient, damping ratio, spindle speed and reciprocation motion speed on the stability limit curve of the chatter system. It can be concluded that the ultrasonic honing chatter system have better stability with low spindle speed, high stiffness and damping ratio, which providing foundation to eliminate ultrasonic honing system chatter in the precision machining of cylinder liner.

The Operational Stability of a Centrifugal Compressor and Its Dependence on the Characteristics of the Subcomponents

1994 ◽  
Vol 116 (2) ◽  
pp. 250-259 ◽  
Author(s):  
R. Hunziker ◽  
G. Gyarmathy
Keyword(s):  
Flow Rate ◽  
Centrifugal Compressor ◽  
Pressure Field ◽  
Dynamic Instability ◽  
Pressure Rise ◽  
Stability Limit ◽  
Maximum Pressure ◽  
Pressure Measurements ◽  
The Stability ◽  
Inlet Angle

A centrifugal compressor was tested with three different diffusers with circular-arc vanes. The vane inlet angle was varied from 15 to 30 deg. Detailed static wall pressure measurements show that the pressure field in the diffuser inlet is very sensitive to flow rate. The stability limit regularly occurred at the flow rate giving the maximum pressure rise for the overall stage. Mild surge arises as a dynamic instability of the compression system. The analysis of the pressure rise characteristic of each individual subcomponent (impeller, diffuser inlet, diffuser channel,...) reveals their contribution to the overall pressure rise. The diffuser channels play an inherently destabilizing role while the impeller and the diffuser inlet are typically stabilizing. The stability limit was mainly determined by a change in the characteristic of the diffuser inlet. Further, the stability limit was found to be independent of the development of inducer-tip recirculation.

Centrifugal Compressor Inlet Guide Vanes for Increased Surge Margin

1991 ◽  
Vol 113 (4) ◽  
pp. 696-702 ◽  
Author(s):  
C. Rodgers
Keyword(s):  
Centrifugal Compressor ◽  
High Speed ◽  
System Stability ◽  
Negative Slope ◽  
Vaned Diffuser ◽  
Guide Vanes ◽  
Inlet Guide Vanes ◽  
Surge Margin ◽  
Compressor Inlet ◽  
Surge Line

This paper describes the results of compressor rig testing with a moderately high specific speed, high inducer Mack number, single-stage centrifugal compressor, with a vaned diffuser, and adjustable inlet guide vanes (IGVs). The results showed that the high-speed surge margin was considerably extended by the regulation of the IGVs, even though the vaned diffuser was apparently operating stalled. Simplified one-dimensional analysis of the impeller and diffuser performances indicated that at inducer tip Mach numbers approaching and exceeding unity, the high-speed surge line was triggered by inducer stall. Also, IGV regulation increased impeller stability. This permitted the diffuser to operate stalled, providing the net compression system stability remained on a negative slope.

Assessment of Steady and Unsteady Model Predictions for a Subsonic Centrifugal Compressor Stage

2012 ◽  
Author(s):  
Y. Bousquet ◽  
X. Carbonneau ◽  
I. Trebinjac
Keyword(s):  
Centrifugal Compressor ◽  
Industrial Development ◽  
Pressure Ratio ◽  
Stability Limit ◽  
Compressor Stage ◽  
Common Procedure ◽  
Centrifugal Compressor Stage ◽  
Steady Simulation ◽  
The Stability ◽  
High Level

The most common procedure to obtain the performance of a centrifugal compressor in an industrial development process is based on the use of a steady RANS model with the mixing-plane approach. However some phenomena such as the flow interaction between the impeller and the diffuser can be the source of unsteady effects which can affect the steady model prediction. This paper investigates the ability of a steady simulation to predict the overall performance and the flow structures in a subsonic centrifugal compressor stage by comparison with time-dependent results. Simulations are performed considering three operating points: peak efficiency, close to the stability limit and close to the blockage. The results show that the steady model is accurate enough to predict the stage static-to-total pressure ratio. However, in location where high level of fluctuation is expected, the steady model shows some weakness to predict the time-averaged quantities of the flow structure.

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