Pulsating Coolant Ejection Effects Downstream of Supersonic Trailing Edge

Bernardini, Chiara; Salvadori, Simone; Martelli, Francesco; Paniagua, Guillermo; Saracoglu, Bayindir H.

doi:10.1080/19942060.2013.11015468

Cited by 4 publications

(5 citation statements)

References 17 publications

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“…Towards a more efficient use of this flow actuation, the modulation of the base bleed flow by means of intermittent trailing edge injection instead of a constant mass flow can be considered. This topic was numerically and experimentally covered in the low supersonic regime [15][16][17], with interesting results. While part of the published numerical data suggests that employing intermittent base bleed actuation would not offer significant gains when compared to constant actuation [16], empirical results indicate the contrary.…”

Section: Introductionmentioning

confidence: 99%

“…This topic was numerically and experimentally covered in the low supersonic regime [15][16][17], with interesting results. While part of the published numerical data suggests that employing intermittent base bleed actuation would not offer significant gains when compared to constant actuation [16], empirical results indicate the contrary. It has been shown that forcing base bleed to actuate by pulses may enhance blade cooling and reduce associated losses, as the modulation of the trailing edge flow could alter the impingement of the trailing edge shock wave on the suction side of downstream blades [17].…”

Section: Introductionmentioning

confidence: 99%

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Efficiency of Pulsating Base Bleeding to Control Trailing Edge Flow Configurations

et al. 2022

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As high-pressure-turbines operate at extreme temperature conditions, base bleed can be applied at the trailing edge of the airfoils, enhancing the thermal protection along the trailing edge surface, but also disrupting the trailing edge flow and altering the overall aerodynamic pressure losses. The current work explores the potential use of base bleed as a flow control tool to modulate the flow between turbine blade rows. Through the numerical analysis of a symmetric airfoil immersed in a subsonic flow, the effects that trailing edge ejection has on the base region properties and the downstream flow are evaluated. In particular, previous research constrained to steady blowing is now extended to consider an unsteady pulsating base bleed injection. Three injection frequencies are investigated, covering a wide range of base bleed intensities. The results presented herein demonstrate that pulsating bleed flow is more efficient than its steady counterpart in terms of reducing pressure losses and controlling the primary frequency of the downstream oscillations for the same mass flow injection.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Efficiency of Pulsating Base Bleeding to Control Trailing Edge Flow Configurations

et al. 2022

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“…The results show that the coolant can change the shock system and modify the vortex shedding frequency. Bernardini et al (2013) study the effect of trailing edge pulsating coolant ejection under supersonic flow. They conclude that the change in the value of the coolant, not the absolute value, affects the shape of the vortex.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study on the Biomimetic Trailing Edge of a Turbine Blade Under a Wide Range of Outlet Mach Numbers

et al. 2021

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This study was carried out to investigate the loss mechanism of a blade with a harbor seal whisker structure on the trailing edge under different Mach numbers. The loss of high-pressure turbine blades with four different trailing edge geometries, including a prototype, an elliptical trailing edge (ETE), a sinusoidal trailing edge (STE), and a biomimetic trailing edge (BTE) at Mach numbers of 0.38–1.21 is studied. The delayed detached-eddy simulation method is used to predict the detailed flow of the four cascades. The result shows that, when the Mach number is less than 0.9, the BTE can effectively reduce the energy loss coefficient compared with the other three cases. As the Mach number increases, the three-dimensional characteristics of the wake behind the BTE weaken. The energy loss coefficient of the blade with the BTE is close to that of the blade with the ETE and STE when the Mach number is greater than 0.9. Besides this, by controlling the wake, the BTE can effectively suppress the dynamic movement of shock waves in the cascade at high Mach numbers.

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“…For example, both shock intensity and wake loss are discussed considering pulsating coolant ejection at various frequencies and blowing ratios. To this end, blunt and circular trailing edges, exposed to continuous blowing (at different rates), were compared by using steady simulations (Bernardini et al, 2013).…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic analysis of nonuniform trailing edge blowing

Wang

Thomas

2018

AEAT

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Purpose Numerical and experimental results for different oncoming base-flow conditions indicate that nonuniform trailing edge blowing (NTEB) can expand the performance range of compressors and reduce the thrust on the rotor, while the efficiency of the compressor can be improved by more than 2 per cent. Design/methodology/approach Relevant aerodynamic parameters, such as total pressure, ratio of efficiency and axial thrust, are calculated and analyzed under conditions with and without NTEB. Measurements are performed downstream of two adjacent stator blades, at seven equidistantly spaced reference locations. The experimental measurement of the interstage flow field used a dynamic four-hole probe with phase lock technique. Findings An axial low-speed single-stage compressor was established with flow field measurement system and nonuniform blowing system. NTEB was studied by means of numerical simulations and experiments, and it is found that the efficiency of the tested compressor can be improved by more than 2 per cent. Originality/value Unlike most of the previous research studies which mainly focused on the rotor/stator interaction and trailing edge uniform blowing, the research results summarized in the current paper on the stator/rotor interaction used inlet guide vanes for steady and unsteady calculations. An active control of the interstage flow field in a low-speed compressor was used to widen the working range and improve the performance of the compressor.

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Pulsating Coolant Ejection Effects Downstream of Supersonic Trailing Edge

Cited by 4 publications

References 17 publications

Efficiency of Pulsating Base Bleeding to Control Trailing Edge Flow Configurations

Efficiency of Pulsating Base Bleeding to Control Trailing Edge Flow Configurations

Numerical Study on the Biomimetic Trailing Edge of a Turbine Blade Under a Wide Range of Outlet Mach Numbers

Aerodynamic analysis of nonuniform trailing edge blowing

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