Design Method for Turbomachine Blades With Finite Thickness by the Circulation Method

1997 ◽  
Vol 119 (3) ◽  
pp. 539-543 ◽  
Author(s):  
J. Jiang ◽  
T. Dang
Keyword(s):  
Inverse Method ◽  
Design Method ◽  
Guide Vane ◽  
Finite Thickness ◽  
Three Dimensional ◽  
Inlet Guide Vane ◽  
Impulse Turbine ◽  
Blade Thickness ◽  
Flow Limit ◽  
Design Calculations

This paper presents a procedure to extend a recently developed three-dimensional inverse method for infinitely thin blades to handle blades with finite thickness. In this inverse method, the prescribed quantities are the blade pressure loading and the blade thickness distributions, and the calculated quantity is the blade mean camber line. The method is formulated in the fully inverse mode whereby the blade shape is determined iteratively using the flow-tangency condition along the blade surfaces. Design calculations are presented for an inlet guide vane, an impulse turbine blade, and a compressor blade in the two-dimensional inviscid- and incompressible-flow limit. Consistency checks are carried out for these design calculations using a panel analysis method and the analytical solution for the Gostelow profile.

scholarly journals Design Method for Turbomachine Blades With Finite Thickness by the Circulation Method

1994 ◽  
Author(s):  
Jun Jiang ◽  
Thong Dang
Keyword(s):  
Inverse Method ◽  
Incompressible Flows ◽  
Design Method ◽  
Guide Vane ◽  
Finite Thickness ◽  
Three Dimensional ◽  
Inlet Guide Vane ◽  
Impulse Turbine ◽  
Blade Thickness ◽  
Design Calculations

This paper presents a procedure to extend a well-developed fully three-dimensional inverse method for infinitely-thin blades to handle blades with finite thickness. In this inverse method, the prescribed quantities are the blade pressure loading and the blade thickness distributions, and the calculated quantity is the blade geometry. The method is formulated in the fully inverse mode whereby the blade shape is determined iteratively using the flow-tangency condition along the blade surfaces. This technique is demonstrated here in the first instance for the design of cascaded blades in inviscid and incompressible flows. Design calculations are presented for an inlet guide vane, an impulse turbine blade, and a compressor blade. Consistency checks are carried out for these design calculations using a panel analysis method and the analytical solution for the Gostelow profile.

scholarly journals An improved inverse method for multirow blades of turbomachinery

2020 ◽  
Vol 234 (22) ◽  
pp. 4433-4443
Author(s):  
Li Aiting ◽  
Zhu Yangli ◽  
Li Wen ◽  
Wang Xing ◽  
Qin Wei ◽  
...  
Keyword(s):  
Flow Structure ◽  
Inverse Method ◽  
Design Method ◽  
Spline Interpolation ◽  
Thickness Distribution ◽  
Three Dimensional ◽  
Internal Flow ◽  
Navier Stokes ◽  
Virtual Displacement ◽  
Blade Thickness

A three-dimensional viscous inverse design method is improved and extended to multirow blades environment. The inverse method takes load distribution as optimization objective and is implemented into the time-marching finite-volume Reynolds-averaged Navier–Stokes solver. The camber line of rotor blade is updated by virtual displacement, which is calculated by characteristic compatibility relations according to the difference between target and actual load so as to control the location and intensity of shock wave, and realize the optimization of flow structure and reduction flow separation. The inlet and outlet geometry angles of stator blade are adjusted in real time according to the inlet and outlet flow angles. Thus, it is computationally ensured that the blade row interactions are accounted and optimization process is carried out under the design condition. To preserve the robustness of calculation, the maximum virtual displacement is limited by Y+ <10 and the camber line is smoothed via cubic B-spline interpolation. The complete blade profile is then generated by adding the prescribed blade thickness distribution to the camber line. The effectiveness of the method is demonstrated in the optimization of Stage35 compressor stage. Numerical results showed that this inverse method can effectively improve the internal flow structure and optimize the matching between blade rows, and this method is robust, efficient, and flexible.

scholarly journals Effect of the Reynolds Number and Clearance Flow on the Aerodynamic Characteristics of a New Variable Inlet Guide Vane

Aerospace ◽  
2021 ◽  
Vol 8 (7) ◽  
pp. 172
Author(s):  
Hengtao Shi
Keyword(s):  
Reynolds Number ◽  
Guide Vane ◽  
Three Dimensional ◽  
High Growth ◽  
Aerodynamic Characteristics ◽  
Inlet Guide Vane ◽  
Separation Region ◽  
Clearance Flow ◽  
New Type ◽  
Variable Inlet Guide Vane

Recently, a new type of low-loss variable inlet guide vane (VIGV) was proposed for improving a compressor’s performance under off-design conditions. To provide more information for applications, this work investigated the effect of the Reynolds number and clearance flow on the aerodynamic characteristics of this new type of VIGV. The performance and flow field of two representative airfoils with different chord Reynolds numbers were studied with the widely used commercial software ANSYS CFX after validation was completed. Calculations indicate that, with the decrease in the Reynolds number Rec, the airfoil loss coefficient ω and deviation δ first increase slightly and then entered a high growth rate in a low range of Rec. Afterwards, a detailed boundary-layer analysis was conducted to reveal the flow mechanism for the airfoil performance degradation with a low Reynolds number. For the design point, it is the appearance and extension of the separation region on the rear portion; for the maximum incidence point, it is the increase in the length and height of the separation region on the former portion. The three-dimensional VIGV research confirms the Reynolds number effect on airfoils. Furthermore, the clearance leakage flow forms a strong stream-wise vortex by injection into the mainflow, resulting in a high total-pressure loss and under-turning in the endwall region, which shows the potential benefits of seal treatment.

The Effect of the Thickness and Angle of the Inlet and Outlet Guide Vane on the Performance of Axial-Flow Pump

2016 ◽  
Author(s):  
Sang-Won Kim ◽  
Youn-Jea Kim
Keyword(s):  
Numerical Analysis ◽  
Numerical Study ◽  
Guide Vane ◽  
Axial Flow ◽  
Inlet Guide Vane ◽  
Guide Vanes ◽  
Pump Performance ◽  
Blade Thickness ◽  
Axial Flow Pump ◽  
Flow Pump

An axial-flow pump has a relatively high discharge flow rate and specific speed at a relatively low head and it consists of an inlet guide vane, impeller, and outlet guide vane. The interaction of the flow through the inlet guide vane, impeller, and outlet guide vane of the axial-flow pump has a significant effect on its performance. Of those components, the guide vanes especially can improve the head and efficiency of the pump by transforming the kinetic energy of the rotating flow, which has a tangential velocity component, into pressure energy. Accordingly, the geometric configurations of the guide vanes such as blade thickness and angle are crucial design factors for determining the performance of the axial-flow pump. As the reliability of Computational Fluid Dynamics (CFD) has been elevated together with the advance in computer technology, numerical analysis using CFD has recently become an alternative to empirical experiment due to its high reliability to measure the flow field. Thus, in this study, 1,200mm axial-flow pump having an inlet guide vane and impeller with 4 blades and an outlet guide vane with 6 blades was numerically investigated. Numerical study was conducted using the commercial CFD code, ANSYS CFX ver. 16.1, in order to elucidate the effect of the thickness and angle of the guide vanes on the performance of 1,200mm axial-flow pump. The stage condition, which averages the fluxes between interfaces and is accordingly appropriate for the evaluation of pump performance, was adopted as the interface condition between the guide vanes and the impeller. The rotational periodicity condition was used in order to enable a simplified geometry to be used since the guide vanes feature multiple identical regions. The shear stress transport (SST) k-ω model, predicting the turbulence within the flow in good agreement, was also employed in the CFD calculation. With regard to the numerical simulation results, the characteristics of the pressure distribution were discussed in detail. The pump performance, which will determine how well an axial-flow pump will work in terms of its efficiency and head, was also discussed in detail, leading to the conclusion on the optimal blade thickness and angle for the improvement of the performance. In addition, the total pressure loss coefficient was considered in order to investigate the loss within the flow paths depending on the thickness and angle variations. The results presented in this study may give guidelines to the numerical analysis of the axial-flow pump and the investigation of the performance for further optimal design of the axial-flow pump.

Wall Boundary Layer Development Near the Tip Region of an IGV of an Axial Flow Compressor

1984 ◽  
Vol 106 (2) ◽  
pp. 337-345
Author(s):  
B. Lakshminarayana ◽  
N. Sitaram
Keyword(s):  
Boundary Layer ◽  
Guide Vane ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Axial Flow ◽  
Inlet Guide Vane ◽  
Wall Boundary Layer ◽  
Wall Boundary ◽  
Boundary Layer Development ◽  
Flow Compressor

The annulus wall boundary layer inside the blade passage of the inlet guide vane (IGV) passage of a low-speed axial compressor stage was measured with a miniature five-hole probe. The three-dimensional velocity and pressure fields were measured at various axial and tangential locations. Limiting streamline angles and static pressures were also measured on the casing of the IGV passage. Strong secondary vorticity was developed. The data were analyzed and correlated with the existing velocity profile correlations. The end wall losses were also derived from these data.

IGV-Rotor Interaction Analysis in a Transonic Compressor Using the Navier-Stokes Equations

1996 ◽  
Author(s):  
Andrea Arnone ◽  
Roberto Pacciani
Keyword(s):  
Stokes Equations ◽  
Interaction Analysis ◽  
Guide Vane ◽  
Three Dimensional ◽  
Navier Stokes ◽  
Inlet Guide Vane ◽  
Operating Characteristics ◽  
Navier Stokes Equations ◽  
Transonic Compressor ◽  
Mass Flow Rates

A recently developed, time-accurate multigrid viscous solver has been extended to handle quasi-three-dimensional effects and applied to the first stage of a modern transonic compressor. Interest is focused on the inlet guide vane (IGV):rotor interaction where strong sources of unsteadiness are to be expected. Several calculations have been performed to predict the stage operating characteristics. Flow structures at various mass flow rates, from choke to near stall, are presented and discussed. Comparisons between unsteady and steady pitch-averaged results are also included in order to obtain indications about the capabilities of steady, multi-row analyses.

Investigation of Nonaxisymmetric Endwall Contouring and Three-Dimensional Airfoil Design in a 1.5 Stage Axial Turbine—Part II: Experimental Validation

2015 ◽  
Vol 137 (8) ◽  
Author(s):  
Jens Niewoehner ◽  
Thorsten Poehler ◽  
Peter Jeschke ◽  
Yavuz Guendogdu
Keyword(s):  
Experimental Validation ◽  
Guide Vane ◽  
Radial Profile ◽  
Three Dimensional ◽  
Mechanical Efficiency ◽  
Fast Response ◽  
Numerical Results ◽  
Inlet Guide Vane ◽  
Computational Fluid Dynamics Cfd ◽  
Yaw Angle

This paper is the second part of a two-part paper reporting on the increase in efficiency of a 1.5 stage axial test rig turbine with the use of nonaxisymmetric endwalls and 3D airfoil design. Contoured endwalls were developed for the inlet guide vane separately, as well as in combination with a bowed radial profile stacking. In addition, a contour endwall was applied to the hub of the unshrouded rotor. In Part I, the design of the profiled endwalls and 3D airfoils is presented, as well as a detailed analysis of the steady and unsteady computational fluid dynamics (CFD) results. Part II reports on the experimental validation of the numerical results. A distinct increase in mechanical efficiency for both new configurations in good agreement with the numerical results is observed. Additionally, performance map measurements demonstrate that the new designs are also beneficial under off-design conditions. Five- and three-hole-probes as well as fast-response total pressure probes are used to investigate the new designs. The main effect is the homogenization of the yaw angle behind the first stator.

Design of a Modern Test-Facility for LPT/OGV Flows

2003 ◽  
Author(s):  
Johan Hja¨rne ◽  
Jonas Larsson ◽  
Lennart Lo¨fdahl
Keyword(s):  
Test Section ◽  
Design Method ◽  
Guide Vane ◽  
Three Dimensional ◽  
Flow Characteristics ◽  
Design Procedure ◽  
Test Facility ◽  
Settling Chamber ◽  
Inlet Section ◽  
Analytical Approaches

This paper presents a complete design process of a modern test-facility for the investigation of low pressure turbine/outlet guide vane (LPT/OGV) flows. The design is based on modern CFD techniques combined with classical analytical approaches and experimental expertise. The paper describes the design procedure of the diffuser, the settling chamber, the contraction, the inlet section with boundary layer bleeds and the test-section. In the contraction part of the paper a new design method is developed using both separation and relaminarization theory. Finally, full viscous three-dimensional CFD calculations are performed of the test-facility, from the contraction to the test-section, making it possible to assess the flow characteristics of the test-facility before it is even constructed.

Turbine Blade Duty Re-Design by Controlling Lean and Sweep Using an Innovative Iterative Inverse Design Method

2006 ◽  
Author(s):  
Jose´ C. Pa´scoa ◽  
Anto´nio C. Mendes
Keyword(s):  
Gas Turbines ◽  
Inverse Method ◽  
Design Method ◽  
Three Dimensions ◽  
Weak Part ◽  
Blade Thickness ◽  
Long Time ◽  
Time Marching ◽  
Time Lagged ◽  
Inverse Design Method

Inverse methods able to work in the transonic regime have for a long time been the weak part in the inverse method universe, albeit most of current gas turbines work in this regime. The present iterative inverse method is based on a Finite Volume time-marching scheme that is able to accurately compute the flowfield inside turbomachinery passages. In our design method we prescribe the acrodynamic load and blade thickness. Imposition of these variables precludes any existence and uniqueness problems and enables us to incorporate information regarding thermal and mechanical stresses in the first design stages. The method herein presented starts with an analysis of the flow in an initial geometry that is afterward adjusted by a modification in camber line. A new time-lagged formulation for the camber line generator will be presented. In order to design in three-dimensions a flexible stacking line generator will be introduced, as a mean to independently control sweep and lean for the blades. The results presented illustrate how an annular turbine cascade can be re-designed, with the present method, for better blade performance.

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