Performance Improvement of Low Pressure Turbine Blade by Using Synthetic Jets

Liu, Xiaomin; Wang, Xing

doi:10.1080/19942060.2011.11015385

Cited by 9 publications

(4 citation statements)

References 9 publications

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“…They also demonstrated computational efficiency obtained using the methodology. Further studies of similar interest have been presented by Aziz et al (2008), Wasewar and Sarathi (2008) and Liu and Wang (2011). The work presented in this article utilizes the same ILES approach using high resolution methods to study the flow of a transverse sonic hydrogen jet injected into the free-stream turbulent supersonic (Mach number 2.5) flow of air.…”

Section: Introductionmentioning

confidence: 99%

Dynamics of Sonic Hydrogen Jet Injection and Mixing Inside Scramjet Combustor

Rana

Thornber

Drikakis

2013

Engineering Applications of Computational Fluid Mechanics

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This paper presents the application of a Finite Volume Godunov-type implicit large eddy simulation method to study fuel injection into the combustion chamber of HyShot-II scramjet engine without chemical reaction/combustion in order to understand the fuel injection and air-fuel (hydrogen) mixing. The study is carried out in two parts; part one presents analysis of 2D HyShot-II geometry (without fuel injection) incorporating high temperature gas formulation which is validated against the NASA Thermally-Perfect-Gas code in order to obtain the combustion chamber inlet conditions. These combustor initial conditions are then utilized in part two for 3D combustion chamber simulations with hydrogen injection but cold flow where a digital filter based turbulent inflow boundary condition has been utilized. The purpose of the study is to understand the flow physics, hydrogen jet penetration and air & fuel mixing inside the HyShot-II combustor which is vital at the design stages. Various flow features are investigated such as the Mach number, velocity, pressure distributions, temperature, turbulent kinetic energy, Reynolds stresses and the effect of counter rotating vortices on mixing. The results of full geometry simulations are compared with computational results from the German Aerospace Centre, DLR, whereas due to unavailability of any data for hydrogen cold flow the validity of the results is based upon a similar validation case presented earlier (Rana et al., 2011b).

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Section: Introductionmentioning

confidence: 99%

Dynamics of Sonic Hydrogen Jet Injection and Mixing Inside Scramjet Combustor

Rana

Thornber

Drikakis

2013

Engineering Applications of Computational Fluid Mechanics

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“…Yao and Sandham (2002) Arcas and Redekopp (2004), who evaluated the instability threshold for the comparison of the vortex pattern. The idea of oscillating blowing at zero-net massflow stems from flow control studies in low pressure turbines exploiting synthetic jets in order to overcome suction side separation (Liu and Wang, 2011). However, flow suction from the base region is unacceptable in a high pressure turbine.…”

Section: Introductionmentioning

confidence: 99%

Pulsating Coolant Ejection Effects Downstream of Supersonic Trailing Edge

Bernardini¹,

Salvadori²,

Martelli³

et al. 2013

Engineering Applications of Computational Fluid Mechanics

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ABSTRACT:Trailing edge blowing is used in a great variety of applications. In particular, high-pressure turbines bleed about 3% of the engine core massflow through a rear slot of the inlet guide vanes. At transonic conditions the coolant flow alters substantially the base region characteristics, and therefore the wake and shocks. Certain pulsating coolant frequencies give rise to exotic vortical shedding structures, not observed when the coolant is continuous. A detailed analysis of the flow field near the trailing edge region has been performed using the in-house HybFlow code. Blunt and circular trailing edges, exposed to continuous blowing (at different rates) were compared by using steady simulations. Both shock intensity and wake loss are discussed in this paper considering pulsating coolant ejection at various frequencies and blowing ratios.

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“…A brief review of flow control literature is provided by Gad-el (2000), Williams . In recent years, the synthetic jet and pulsed jet (Qiu et al, 2012;Liu and Wang, 2011) are becoming more and more important in active flow control, particularly for the plasma actuators due to the absence of any moving parts and their fast time response characteristics. The dielectric barrier discharge (DBD) actuator is the most popular plasma actuator.…”

Section: Introductionmentioning

confidence: 99%

Effects of Parameters on Continuously Working Plasma Synthetic Jet

Gan

2014

Engineering Applications of Computational Fluid Mechanics

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ABSTRACT:If the actuator of the plasma synthetic jet (PSJ) operates continuously under a high frequency, the performance of the actuator will become worse than it is in single pulse test. This is because the air in the cavity cannot fully recover to the original state before the next cycle starts. Therefore, the characteristics of the plasma synthetic jet during continuous operation, rather than during a single pulse, need to be studied carefully. In this paper, simulated flow fields of the continuously working PSJ are analyzed. It is found that the time-averaged results of the PSJ are self-similar, however, the instantaneous results are only self-similar when y is less than y 0.5 . Moreover, the effects of the dominant parameters, such as the maximum temperature, cavity shape and the operating frequency, on the performance of the PSJ actuator under stable operating condition are discussed. The maximum temperature is the most important parameter for the PSJ actuator. Actuator performance improves when the maximum temperature increases. In contrast, the frequency has little influence on performance, and the PSJ actuator is shown to perform well under a wide range of frequencies. This is more beneficial for active flow control compared with the synthetic jet actuator driven by the piezoelectric patch. The shape and the volume of the cavity can also influence the performance of the actuator. As the volume of the cavity becomes smaller, the duration of the spurt period is reduced.

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Performance Improvement of Low Pressure Turbine Blade by Using Synthetic Jets

Cited by 9 publications

References 9 publications

Dynamics of Sonic Hydrogen Jet Injection and Mixing Inside Scramjet Combustor

Dynamics of Sonic Hydrogen Jet Injection and Mixing Inside Scramjet Combustor

Pulsating Coolant Ejection Effects Downstream of Supersonic Trailing Edge

Effects of Parameters on Continuously Working Plasma Synthetic Jet

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