Scaling Three-Dimensional Low-Pressure Turbine Blades for Low-Speed Testing

2016 ◽  
Vol 138 (11) ◽  
Author(s):  
Matteo Giovannini ◽  
Michele Marconcini ◽  
Filippo Rubechini ◽  
Andrea Arnone ◽  
Francesco Bertini
Keyword(s):  
Turbine Blade ◽  
High Speed ◽  
Large Scale ◽  
General Procedure ◽  
Turbine Blades ◽  
Three Dimensional ◽  
Low Pressure ◽  
Low Speed ◽  
Scaling Procedure ◽  
Inlet Conditions

The present activity was carried out in the framework of the Clean Sky European Research Project ITURB (optimal high-lift turbine blade aeromechanical design), aimed at designing and validating a turbine blade for a geared open-rotor engine. A cold-flow, large-scale, low-speed (LS) rig was built in order to investigate and validate new design criteria, providing reliable and detailed results while containing costs. This paper presents the design of an LS stage and describes a general procedure that allows to scale three-dimensional (3D) blades for LS testing. The design of the stator row was aimed at matching the test-rig inlet conditions and at providing the proper inlet flow field to the blade row. The rotor row was redesigned in order to match the performance of the high-speed (HS) configuration, compensating for both the compressibility effects and different turbine flow paths. The proposed scaling procedure is based on the matching of the 3D blade loading distribution between the real engine environment and the LS facility one, which leads to a comparable behavior of the boundary layer and hence to comparable profile losses. To this end, the datum blade is parameterized, and a neural-network-based methodology is exploited to guide an optimization process based on 3D Reynolds-averaged Navier–Stokes (RANS) computations. The LS stage performance was investigated over a range of Reynolds numbers characteristic of modern low-pressure turbines (LPTs) by using a multi-equation, transition-sensitive, turbulence model. Some comparisons with experimental data available within the project finally proved the effectiveness of the proposed scaling procedure.

Scaling 3D Low-Pressure Turbine Blades for Low-Speed Testing

2015 ◽  
Author(s):  
Matteo Giovannini ◽  
Michele Marconcini ◽  
Filippo Rubechini ◽  
Andrea Arnone ◽  
Francesco Bertini
Keyword(s):  
Turbine Blade ◽  
High Speed ◽  
Large Scale ◽  
Mechanical Design ◽  
General Procedure ◽  
Turbine Blades ◽  
Low Pressure ◽  
Low Speed ◽  
Open Rotor ◽  
Inlet Conditions

The present activity was carried out in the framework of the Clean Sky European research project ITURB (“Optimal High-Lift Turbine Blade Aero-Mechanical Design”), aimed at designing and validating a turbine blade for a geared open rotor engine. A cold-flow, large-scale, low-speed (LS) rig was built in order to investigate and validate new design criteria, providing reliable and detailed results while containing costs. This paper presents the design of a LS stage, and describes a general procedure that allows to scale 3D blades for low-speed testing. The design of the stator row was aimed at matching the test-rig inlet conditions and at providing the proper inlet flow field to the blade row. The rotor row was redesigned in order to match the performance of the high-speed one, compensating for both the compressibility effects and different turbine flow paths. The proposed scaling procedure is based on the matching of the 3D blade loading distribution between the real engine environment and the LS facility one, which leads to a comparable behavior of the boundary layer and hence to comparable profile losses. To this end, the datum blade is parameterized, and a neural-network-based methodology is exploited to guide an optimization process based on 3D RANS computations. The LS stage performance were investigated over a range of Reynolds numbers characteristic of modern low-pressure turbines by using a multi-equation, transition-sensitive, turbulence model.

scholarly journals The Design and Testing of a Radial Flow Turbine for Aerodynamic Research

1991 ◽  
Author(s):  
I. Huntsman ◽  
H. P. Hodson ◽  
S. H. Hill
Keyword(s):  
High Speed ◽  
Large Scale ◽  
Three Dimensional ◽  
Surface Flow ◽  
Stream Line ◽  
Flow Visualisation ◽  
Gas Generator ◽  
Low Speed ◽  
Scaling Parameters ◽  
Design And Testing

This paper describes the design of a high-speed radial inflow turbine for use as part of a gas-generator, and the design of a large-scale (1.2 m tip dia.) low-speed model of the high-speed turbine. Stream-line curvature throughflow, two-dimensional blade-to-blade and fully three-dimensional inviscid and viscous calculation methods have been used extensively in the analysis of the designs. The use of appropriate scaling parameters and their impact on turbine performance is discussed. A simple model shows, for example, how to model the blade lean in the inducer which serves to balance the effect of meridional curvature at inlet to the rotor and can be used to unload the rotor tip. A brief description of the low speed experimental facility is followed by a presentation and discussion of experimental results. These include surface flow visualisation patterns on both the rotor and stator blades and blade row exit traverses.

scholarly journals Performances and Stall Delays of Three Dimensional Wind Turbine Blade Plate-Models with Helicopter-Like Propeller Blade Tips

2017 ◽  
Vol 11 (10) ◽  
pp. 189 ◽  
Author(s):  
Sutrisno Sutrisno ◽  
Deendarlianto Deendarlianto ◽  
Indarto Indarto ◽  
Sigit Iswahyudi ◽  
Muhammad Agung Bramantya ◽  
...  
Keyword(s):  
Wind Turbine ◽  
Turbine Blade ◽  
High Speed ◽  
Turbine Blades ◽  
Three Dimensional ◽  
Laminar Flows ◽  
Wind Turbine Blade ◽  
Mathematical Form ◽  
Wind Turbine Blades ◽  
Blade Tips

The research on three dimensional (3-D) wind turbine blades has been introduced (Sutrisno, Prajitno, Purnomo, & B.W. Setyawan, 2016). In the current experiment, the 3-D wind turbine blades would be fitted with helicopter-like blade tips and additional fins to the blade hubs to demonstrate some laminarizing features. It was found that additional helicopter-like blade tip to the turbine blade creates strong laminar flows over the surface of the blade tips. Supplementary, finned hub, fitted to the blade body, creates rolled-up vortex flows, weakens the blade stall growth development, especially for blades at high-speed wind. A proposed mathematical form of modified lifting line model has been developed to pursue further 3-d blade development study of 3-d wind turbine blade. Rolled up vortex effects, developed by finned of the base hub, has been acknowledged could demolish the turbulent region, as well as laminarize the stall domain to intensify the induced wind turbine blade lift.

Transient Thermal and Structural Analysis of the Liquid Rocket Turbopump Turbine

2005 ◽  
Author(s):  
S. H. Yoon ◽  
S. M. Jeon ◽  
J. Kim
Keyword(s):  
Heat Transfer ◽  
Structural Analysis ◽  
Turbine Blade ◽  
High Speed ◽  
Turbine Blades ◽  
Three Dimensional ◽  
Liquid Oxygen ◽  
Cfd Analysis ◽  
Hot Gas ◽  
Liquid Rocket

A turbopump unit is a key component of the liquid rocket engine assembly. Generally operated by an impulse-type turbine with supersonic hot gas for a gas generator cycle engine, it pressurizes liquid oxygen and fuel to attain high specific impulse. The turbine is exposed to hot gas while rotating at a high speed and experiences severe thermal and mechanical loads during the operation. Its structural integrity must be assured through thermal and structural analyses of the turbine. To investigate non-steady heat transfer characteristics from the hot gas to the turbine blade, the heat transfer of supersonic hot gas flow to the complicated turbine blade geometry is solved through a three-dimensional CFD analysis. The distribution of gas temperature, pressure and velocity on the blade surface are obtained by the CFD analysis with appropriate convection heat transfer coefficients to be used for the structural analysis of the turbine rotor. The thermal stress due to material expansion and mechanical stress due to centrifugal loads are considered in the analysis. The three-dimensional transient stress distributions of the turbine blades, shroud, and disk are obtained by a finite element analysis. Finally, the overall results are examined to evaluate the strength safety of the turbine.

Three-Dimensional Flow in a Low-Pressure Turbine Cascade at Its Design Condition

1987 ◽  
Vol 109 (2) ◽  
pp. 177-185 ◽  
Author(s):  
H. P. Hodson ◽  
R. G. Dominy
Keyword(s):  
High Speed ◽  
Turbine Blades ◽  
Three Dimensional ◽  
Low Pressure ◽  
Surface Flow ◽  
Turbine Cascade ◽  
Suction Surface ◽  
Three Dimensional Flow ◽  
Low Pressure Turbine ◽  
Dimensional Flow

This paper describes an experimental study of the three-dimensional flow within a high-speed linear cascade of low-pressure turbine blades. Data were obtained using pneumatic probes and a surface flow visualization technique. It is found that in general, the flow may be described using concepts derived from previous studies of high-pressure turbines. In detail, however, there are differences. These include the existence of a significant trailing shed vortex and the interaction of the endwall fluid with the suction surface flow. At an aspect ratio of 1.8, the primary and secondary losses are of equal magnitude.

The Design and Testing of a Radial Flow Turbine for Aerodynamic Research

1992 ◽  
Vol 114 (2) ◽  
pp. 411-418 ◽  
Author(s):  
I. Huntsman ◽  
H. P. Hodson ◽  
S. H. Hill
Keyword(s):  
High Speed ◽  
Large Scale ◽  
Three Dimensional ◽  
Surface Flow ◽  
Gas Generator ◽  
Low Speed ◽  
Streamline Curvature ◽  
Blade Row ◽  
Scaling Parameters ◽  
Design And Testing

This paper describes the design of a high-speed radial inflow turbine for use as part of a gas generator, and the design of a large-scale (1.2 m tip diameter) low-speed model of the high-speed turbine. Streamline curvature throughflow, two-dimensional blade-to-blade, and fully three-dimensional inviscid and viscous calculation methods have been used extensively in the analysis of the designs. The use of appropriate scaling parameters and their impact on turbine performance is discussed. A simple model shows, for example, how to model the blade lean in the inducer, which serves to balance the effect of meridional curvature at inlet to the rotor and can be used to unload the rotor tip. A brief description of the low-speed experimental facility is followed by a presentation and discussion of experimental results. These include surface flow visualization patterns on both the rotor and stator blades and blade row exit traverses.

scholarly journals Prevention of Mountain Disasters and Maintenance of Residential Area through Real-Time Terrain Rendering

2021 ◽  
Vol 13 (5) ◽  
pp. 2950
Author(s):  
Su-Kyung Sung ◽  
Eun-Seok Lee ◽  
Byeong-Seok Shin
Keyword(s):  
Real Time ◽  
Graphics Processing Units ◽  
High Speed ◽  
Large Scale ◽  
Civil Engineering ◽  
Three Dimensional ◽  
Sampled Data ◽  
Residential Areas ◽  
Terrain Rendering ◽  
Mountain Disasters

Climate change increases the frequency of localized heavy rains and typhoons. As a result, mountain disasters, such as landslides and earthworks, continue to occur, causing damage to roads and residential areas downstream. Moreover, large-scale civil engineering works, including dam construction, cause rapid changes in the terrain, which harm the stability of residential areas. Disasters, such as landslides and earthenware, occur extensively, and there are limitations in the field of investigation; thus, there are many studies being conducted to model terrain geometrically and to observe changes in terrain according to external factors. However, conventional topography methods are expressed in a way that can only be interpreted by people with specialized knowledge. Therefore, there is a lack of consideration for three-dimensional visualization that helps non-experts understand. We need a way to express changes in terrain in real time and to make it intuitive for non-experts to understand. In conventional height-based terrain modeling and simulation, there is a problem in which some of the sampled data are irregularly distorted and do not show the exact terrain shape. The proposed method utilizes a hierarchical vertex cohesion map to correct inaccurately modeled terrain caused by uniform height sampling, and to compensate for geometric errors using Hausdorff distances, while not considering only the elevation difference of the terrain. The mesh reconstruction, which triangulates the three-vertex placed at each location and makes it the smallest unit of 3D model data, can be done at high speed on graphics processing units (GPUs). Our experiments confirm that it is possible to express changes in terrain accurately and quickly compared with existing methods. These functions can improve the sustainability of residential spaces by predicting the damage caused by mountainous disasters or civil engineering works around the city and make it easy for non-experts to understand.

Design of an Intermediate Turbine Duct Downstream of a High Pressure Turbine

2016 ◽  
Author(s):  
Chaoshan Hou ◽  
Hu Wu
Keyword(s):  
High Pressure ◽  
Three Dimensional ◽  
Low Pressure ◽  
Aerodynamic Load ◽  
Duct Flow ◽  
Original Design ◽  
High Pressure Turbine ◽  
Intermediate Turbine Duct ◽  
Low Pressure Turbine ◽  
Inlet Conditions

The flow leaving the high pressure turbine should be guided to the low pressure turbine by an annular diffuser, which is called as the intermediate turbine duct. Flow separation, which would result in secondary flow and cause great flow loss, is easily induced by the negative pressure gradient inside the duct. And such non-uniform flow field would also affect the inlet conditions of the low pressure turbine, resulting in efficiency reduction of low pressure turbine. Highly efficient intermediate turbine duct cannot be designed without considering the effects of the rotating row of the high pressure turbine. A typical turbine model is simulated by commercial computational fluid dynamics method. This model is used to validate the accuracy and reliability of the selected numerical method by comparing the numerical results with the experimental results. An intermediate turbine duct with eight struts has been designed initially downstream of an existing high pressure turbine. On the basis of the original design, the main purpose of this paper is to reduce the net aerodynamic load on the strut surface and thus minimize the overall duct loss. Full three-dimensional inverse method is applied to the redesign of the struts. It is revealed that the duct with new struts after inverse design has an improved performance as compared with the original one.

Design and Analysis of Wind Turbine Blades: Winglet, Tubercle, and Slotted

2013 ◽  
Author(s):  
Alka Gupta ◽  
Abdulrahman Alsultan ◽  
R. S. Amano ◽  
Sourabh Kumar ◽  
Andrew D. Welsh
Keyword(s):  
Power Generation ◽  
Wind Turbine ◽  
Turbine Blade ◽  
Alternative Energy ◽  
Turbine Blades ◽  
Three Dimensional ◽  
Wind Turbine Blade ◽  
Wind Turbine Blades ◽  
Wind Speeds ◽  
Governing Factor

Energy is the heart of today’s civilization and the demand seems to be increasing with our growing population. Alternative energy solutions are the future of energy, whereas the fossil-based fuels are finite and deemed to become extinct. The design of the wind turbine blade is the main governing factor that affects power generation from the wind turbine. Different airfoils, angle of twist and blade dimensions are the parameters that control the efficiency of the wind turbine. This study is aimed at investigating the aerodynamic performance of the wind turbine blade. In the present paper, we discuss innovative blade designs using the NACA 4412 airfoil, comparing them with a straight swept blade. The wake region was measured in the lab with a straight blade. All the results with different designs of blades were compared for their performance. A complete three-dimensional computational analysis was carried out to compare the power generation in each case for different wind speeds. It was found from the numerical analysis that the slotted blade yielded the most power generation among the other blade designs.

Flow Characteristics in a Three-Dimensional Rectangular Channel With a Pair of Ribs Placed Symmetrically at the Channel Walls

2000 ◽  
Author(s):  
M. Singh ◽  
P. K. Panigrahi ◽  
G. Biswas
Keyword(s):  
Heat Transfer ◽  
Large Scale ◽  
Numerical Study ◽  
Rectangular Channel ◽  
Turbine Blades ◽  
Three Dimensional ◽  
Flow Characteristics ◽  
Navier Stokes ◽  
Complex Flow ◽  
Energy Equations

Abstract A numerical study of rib augmented cooling of turbine blades is reported in this paper. The time-dependent velocity field around a pair of symmetrically placed ribs on the walls of a three-dimensional rectangular channel was studied by use of a modified version of Marker-And-Cell algorithm to solve the unsteady incompressible Navier-Stokes and energy equations. The flow structures are presented with the help of instantaneous velocity vector and vorticity fields, FFT and time averaged and rms values of components of velocity. The spanwise averaged Nusselt number is found to increase at the locations of reattachment. The numerical results are compared with available numerical and experimental results. The presence of ribs leads to complex flow fields with regions of flow separation before and after the ribs. Each interruption in the flow field due to the surface mounted rib enables the velocity distribution to be more homogeneous and a new boundary layer starts developing downstream of the rib. The heat transfer is primarily enhanced due to the decrease in the thermal resistance owing to the thinner boundary layers on the interrupted surfaces. Another reason for heat transfer enhancement can be attributed to the mixing induced by large-scale structures present downstream of the separation point.

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