An Experimental Study of Heat Transfer and Film Cooling on Low Aspect Ratio Turbine Nozzles

Takeishi, Kenichiro; Matsuura, M.; Aoki, S.; Satō, Tomohiko

doi:10.1115/1.2927684

Cited by 99 publications

(14 citation statements)

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“…Equation [8] Where, = uncertainty Equation [9] Equation [10] Equation [11] Combining equation [2][3][4][5] Hence, the total uncertainty (Instrument accuracy + uncertainty due to unsteadiness of total pressure) can be given as, …”

Section: Applying Kline and Mcclintock's [24] Methodsmentioning

confidence: 99%

“…In the coming years, studies were conducted by Sjolander [6], Langston [7] and many more, which were finally summarized by Sieverding [8] in his comprehensive review paper. These were further followed by Sharma and Butler [9], Goldstein and Spores [10], Takeishi et al [11]. Blanco et al [14] also looked into the effects of a backward and forward facing step with and without leakage flow and found that the forward facing step produced stronger endwall flows compared to the backward facing step.…”

Section: Secondary Flow Physicsmentioning

confidence: 99%

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Aerodynamic Performance of a Transonic Turbine Blade Passage in Presence of Upstream Slot and Mateface Gap With Endwall Contouring

Jain

Roy

et al. 2014

Volume 2C: Turbomachinery

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The present study investigates mixed out aerodynamic loss coefficient measurements for a high turning, contoured endwall passage under transonic operating conditions in presence of upstream purge slot and mateface gap. The upstream purge slot represents the gap between stator-rotor interface and the mateface gap simulates the assembly feature between adjacent airfoils in an actual high pressure turbine stage. While the performance of the mateface and upstream slot has been studied for lower Mach number, no studies exist in literature for transonic flow conditions. Experiments were performed at the Virginia Tech's linear, transonic blow down cascade facility. Measurements were carried out at design conditions (isentropic exit Mach number of 0.87, design incidence) without and with coolant blowing. Upstream leakage flow of 1.0% coolant to mainstream mass flow ratio (MFR) was considered with the presence of mateface gap. There was no coolant blowing through the mateface gap itself. Cascade exit pressure measurements were carried out using a 5-hole probe traverse at a plane 1.0Cax downstream of the trailing edge for a planar geometry and two contoured endwalls. Spanwise measurements were performed to complete the entire 2D loss plane from endwall to midspan, which were used to plot pitchwise averaged losses for different span locations and loss contours for the passage. Results reveal significant reduction in aerodynamic losses using the contoured endwalls due to the modification of flow physics compared to a non contoured planar endwall.iii

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Section: Applying Kline and Mcclintock's [24] Methodsmentioning

confidence: 99%

Section: Secondary Flow Physicsmentioning

confidence: 99%

Aerodynamic Performance of a Transonic Turbine Blade Passage in Presence of Upstream Slot and Mateface Gap With Endwall Contouring

Jain

Roy

et al. 2014

Volume 2C: Turbomachinery

View full text Add to dashboard Cite

show abstract

“…These vortices are shown in Figure 3.3, which illustrates the secondary flow model of Takeishi et al (1990). There are many secondary flow models, but they do not all agree on the existence of the smaller corner vortices (Goldstein and Spores (1988)) and the path that the suction leg of the horseshoe vortex follows.…”

Section: Passage Vorticesmentioning

confidence: 99%

“…3.1 Structure of supersonic trailing edge shock system (Denton and Xu (1989)). 18 3.2 Schematic illustration of the development of secondary flow in a rotor blade passage (Lakshminarayana (1996) Takeishi et al (1990) …”

Section: Acknowledgmentsmentioning

confidence: 99%

Effect of Inlet Temperature Non-Uniformity on High-Pressure Turbine Performance

Smith

Chang

Tavoularis

2010

Volume 7: Turbomachinery, Parts A, B, and C

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The temperature of the flow entering a high-pressure turbine stage is inherently non-uniform, as it is produced by several discrete, azimuthally-distributed combustors. In general, however, industrial simulations assume inlet temperature uniformity to simplify the preparation process and reduce computation time In the VI configuration, the hot streaks produced higher time-averaged heat load on the vanes and lower heat load on the blades. As the hot streaks in the VI case passed over the stator vanes, they also spread spanwise due to the actions of the casing passage vortices and the radial pressure gradient; this resulted in a stream entering the rotor with relatively low temperature variations. The hot streaks in the MP case were convected undisturbed past the relatively cool vane section. Relatively high time-averaged enthalpy values were found to occur on the pressure side of the blades in the MP configuration. The non-uniformity of the time-averaged enthalpy on the blade surfaces was lower in the VI configuration. The flow exiting the rotor section was much less non-uniform in the VI case, but differences in calculated efficiency were not significant. i for Claudine and Henri ii

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“…Opt 2 leads to more crossflow to the hub than the baseline design, and thus it suppresses the secondary flow vortices in the hub side. Based on experimental (24) and LES results (25) , it has been reported that the secondary flow vortices originate in horseshoe vortices caused by the flow interference between the blade leading edge and end walls, which then leads to total pressure loss. Based on these reports, blade shapes were examined as follows.…”

Section: Journal Of Computational Science and Technologymentioning

confidence: 99%

Multi-Objective Design Optimization for a Steam Turbine Stator Blade Using LES and GA

Shimoyama

Yoshimizu

Jeong

et al. 2011

JCST

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Multi-objective design optimization for a steam turbine stator blade was implemented using three-dimensional large eddy simulation (LES) and a genetic algorithm (GA). The GA used here was assisted by the Kriging response surface model for global and efficient optimization. The aim of the optimization described here was to reduce overall pressure loss and local pressure loss due to end walls simultaneously. The optimization results revealed the blade design candidates that overcame the baseline design in terms of overall loss and local loss, and the trade-off relation between them. In addition, these results provided a specific design concept and corresponding flow mechanism to realize a highly efficient stator blade.

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An Experimental Study of Heat Transfer and Film Cooling on Low Aspect Ratio Turbine Nozzles

Cited by 99 publications

References 0 publications

Aerodynamic Performance of a Transonic Turbine Blade Passage in Presence of Upstream Slot and Mateface Gap With Endwall Contouring

Aerodynamic Performance of a Transonic Turbine Blade Passage in Presence of Upstream Slot and Mateface Gap With Endwall Contouring

Effect of Inlet Temperature Non-Uniformity on High-Pressure Turbine Performance

Multi-Objective Design Optimization for a Steam Turbine Stator Blade Using LES and GA

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