Design of the Purdue Experimental Turbine Aerothermal Laboratory for Optical and Surface Aero-Thermal Measurements

Paniagua, Guillermo; Cuadrado, David G.; Saavedra, Jorge; Andreoli, Valeria; Meyer, T. O.; Meyer, Scott; Lawrence, D.

doi:10.1115/gt2016-58101

Cited by 5 publications

(3 citation statements)

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“…The PETAL facilities allow to use optical measurement techniques such as high frequency particle image velocimetry (PIV) and Schlieren flow visualization, that will be combined with pressure and heat flux measurements to provide an extended dataset of the experimental analysis. An extended description of the PETAL facilities can be consulted on [29].…”

Section: Experimental Methodology and Model Descriptionmentioning

confidence: 99%

Coanda Flow Characterization on Base Bleed Configurations Using Global Stability Analysis

Martínez-Cava

Valero

Vicente

et al. 2019

AIAA Scitech 2019 Forum

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Base pressure control is often employed on drag reduction design, but the interaction of the jet with the base region flow topology can generate undesired or uncontrolled flow configurations. The ejected flow can drive pressure bifurcations at the trailing edge, that without a correct optimization can affect the aerodynamic performance of the system. The purpose of this work is to fully understand the physical mechanisms related with the use of injected base bleed employing global stability analysis and adjoint methodologies. Moreover, the results of the sensitivity analysis are used to identify the regions more receptive to passive and active flow control methodologies. This work has a particular relevance in turbine research, where coolant flow is ejected at the trailing edge to ensure an adequate thermal protection of the blade and the downstream turbine stages.

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Section: Experimental Methodology and Model Descriptionmentioning

confidence: 99%

Coanda Flow Characterization on Base Bleed Configurations Using Global Stability Analysis

Martínez-Cava

Valero

Vicente

et al. 2019

AIAA Scitech 2019 Forum

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“…12 Stagger control mechanism set to 620 deg Flow Periodicity. The flow behavior and the validity of the experimental data are heavily influenced by the spanwise flow characteristics upstream and downstream of the test section [14,32]. The inlet boundary layer suction maintains relatively uniform 2D pressure and velocity distributions across all six passages.…”

Section: Mechanical Designmentioning

confidence: 99%

Continuous Closed-Loop Transonic Linear Cascade for Aerothermal Performance Studies in Microturbomachinery

Yakirevich

Miezner

Leizeronok

et al. 2017

Journal of Engineering for Gas Turbines and Power

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The present work summarizes the design process of a new continuous closed-loop hot transonic linear cascade. The facility features fully modular design which is intended to serve as a test bench for axial microturbomachinery components in independently varying Mach and Reynolds numbers ranges of 0-1.3 and 2 Â 10 4 -6 Â 10 5 , respectively. Moreover, for preserving heat transfer characteristics of the hot gas section, the gas to solid temperature ratio (up to 2) is retained. This operational environment has not been sufficiently addressed in prior art, although it is critical for the future development of ultra-efficient high power or thrust devices. In order to alleviate the dimension specific challenges associated with microturbomachinery, the facility is designed in a highly versatile manner and can easily accommodate different geometric configurations (pitch, 620 deg stagger angle, and 620 deg incidence angle), absence of any alterations to the test section. Owing to the quick swap design, the vane geometry can be easily replaced without manufacturing or re-assembly of other components. Flow periodicity is achieved by the inlet boundary layer suction and independently adjustable tailboard mechanisms. Enabling test-aided design capability for microgas turbine manufacturers, aerothermal performance of various advanced geometries can be assessed in engine relevant environments.

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“…The objective of this paper is to demonstrate a methodology for designing a turbine stage from a 1D mean-line analysis directly to a full 3D optimized design of the stator, rotor, and channel. This manuscript uses design requirements from the Purdue Experimental Turbine Aerothermal Lab (PETAL) [ 17 ] as a starting point for the 1D design.…”

Section: Introductionmentioning

confidence: 99%

Turbine Passage Design Methodology to Minimize Entropy Production—A Two-Step Optimization Strategy

Juangphanich

Maesschalck

Paniagua

2019

Entropy

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Rapid aerodynamic design and optimization is essential for the development of future turbomachinery. The objective of this work is to demonstrate a methodology from 1D mean-line-design to a full 3D aerodynamic optimization of the turbine stage using a parameterization strategy that requires few parameters. The methodology is tested by designing a highly loaded and efficient turbine for the Purdue Experimental Turbine Aerothermal Laboratory. This manuscript describes the entire design process including the 2D/3D parameterization strategy in detail. The objective of the design is to maximize the entropy definition of efficiency while simultaneously maximizing the stage loading. Optimal design trends are highlighted for both the stator and rotor for several turbine characteristics in terms of pitch-to-chord ratio as well as the blades metal and stagger angles. Additionally, a correction term is proposed for the Horlock efficiency equation to maximize the accuracy based on the measured blade kinetic losses. Finally, the design and performance of optimal profiles along the Pareto front are summarized, featuring the highest aerodynamic performance and stage loading.Researchers have used Bezier curves [3] or a combination of splines and b-splines to design airfoil geometries. B-splines have been proven to be a successful tool in reducing turbomachinery loss when coupled to an optimizer. However, they have limitations. Shelton et al. [4] stated that it was difficult to induce large changes to the stagger, trailing edge wedge and leading edge angle using b-splines. They instead used b-splines as a tool to fine-tune the design of the blade. Ghaly and Mengistu [5] used Non-Uniform Rational B-Splines (NURBS) to optimize an existing turbine airfoil design in 2D-NURBS are similar to B-splines except their control points each have a weight. Their parameterization showed that NURBS required fewer points to parameterize a compressor airfoil [6], as opposed to a turbine blade [7] due to the increased curvature of the suction side. Shelton et al.[3] optimized a turbine blade under transonic conditions incorporating a stacking and sweep law. They similarly observed that it was difficult to make large changes to the stagger, wedge angle, and suction side surface angles in their parameterization using b-splines. Hasenjäger et al.[8] adopted b-splines to optimize a low aspect ratio stator blade in 3D and encountered difficulties as well, attempting to limit the number of control points needed to represent the blade surface using spline-like strategies.Bezier curves have been applied in a wide variety of turbomachinery applications because they offer designers the prospect of using less parameters while controlling the curvature by removing the need to parameterize the knot vector [9,10]. Goel et al. [11] used this type of curves to define 2D turbine airfoils using 10 and 8 parameters for the suction and pressure side respectively. Pierret and Van den Braembussche [12] employed a series of Bezier curves to model the suction and pressu...

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Design of the Purdue Experimental Turbine Aerothermal Laboratory for Optical and Surface Aero-Thermal Measurements

Cited by 5 publications

References 0 publications

Coanda Flow Characterization on Base Bleed Configurations Using Global Stability Analysis

Coanda Flow Characterization on Base Bleed Configurations Using Global Stability Analysis

Continuous Closed-Loop Transonic Linear Cascade for Aerothermal Performance Studies in Microturbomachinery

Turbine Passage Design Methodology to Minimize Entropy Production—A Two-Step Optimization Strategy

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