Application of an Inverse Design Method to Meet a Target Pressure in Axial-Flow Compressors

2011 ◽  
Author(s):  
Ali Madadi ◽  
Mohammad Jafar Kermani ◽  
Mahdi Nili-Ahmadabadi
Keyword(s):  
Flow Field ◽  
Pressure Distribution ◽  
Axial Flow ◽  
Inverse Design ◽  
Design Algorithm ◽  
Axial Flow Compressor ◽  
Differential Movement ◽  
Target Pressure ◽  
Flow Compressor ◽  
Blade Geometry

Numerous methods have been developed to design axial-flow compressor blades. These methods are generally categorized into inverse or direct approaches. In the inverse design methods, a distribution of an aerodynamic parameter such as pressure or velocity on the blade surfaces is given, and the target blade geometry that can provide the corresponding distribution is to be determined. In the present work, a novel inverse design algorithm called Ball Spine Algorithm (BSA) is developed to design an axial-flow compressor on the blade to blade surface. In the BSA, the blade surfaces are considered as a set of virtual balls that move freely along the specified directions, called ‘spines’. At first, initial blade geometry is guessed and the blade-to-blade flow field is analyzed by an in-house inviscid flow solver based on the Roe scheme. Comparing the computed pressure distribution (CPD) on the blade surfaces with the target pressure distribution (TPD), gives a guideline in a differential movement for the balls to obtain a modified geometry. For the flow field analysis on the modified geometry, new grids are generated by a combined algebraic-elliptic code. The sequence is repeated until the target pressure is reached. For validation, the approach is applied on an arbitrary blade profile.

Inverse Design of Axial-Flow Compressor Blades Using Elastic Surface Algorithm in Subsonic and Transonic Flow Regimes With Separation

2016 ◽  
Author(s):  
M. H. Noorsalehi ◽  
M. Nili-Ahamadabadi ◽  
E. Shirani ◽  
M. Safari
Keyword(s):  
Pressure Distribution ◽  
Transonic Flow ◽  
Design Method ◽  
Axial Flow ◽  
Flow Regimes ◽  
Inverse Design ◽  
Elastic Surface ◽  
Axial Flow Compressor ◽  
Inverse Design Method ◽  
Flow Compressor

In this study, a new inverse design method called Elastic Surface Algorithm (ESA) is developed and enhanced for axial-flow compressor blade design in subsonic and transonic flow regimes with separation. ESA is a physically based iterative inverse design method that uses a 2D flow analysis code to estimate the pressure distribution on the solid structure, i.e. airfoil, and a 2D solid beam finite element code to calculate the deflections due to the difference between the calculated and target pressure distributions. In order to enhance the ESA, the wall shear stress distribution, besides pressure distribution, is applied to deflect the shape of the airfoil. The enhanced method is validated through the inverse design of the rotor blade of the first stage of an axial-flow compressor in transonic viscous flow regime. In addition, some design examples are presented to prove the effectiveness and robustness of the method. The results of this study show that the enhanced Elastic Surface Algorithm is an effective inverse design method in flow regimes with separation and normal shock.

Effects of Endwall Profiling on Axial Flow Compressor Stage

2009 ◽  
Author(s):  
Jialing Lu ◽  
Wuli Chu ◽  
Yanhui Wu
Keyword(s):  
Flow Field ◽  
Engineering Design ◽  
Axial Flow ◽  
Design Tool ◽  
Operating Conditions ◽  
Compressor Stage ◽  
Corner Separation ◽  
Axial Flow Compressor ◽  
Flow Compressor ◽  
Stage Efficiency

In recent years endwall profiling has been well validated as a major new engineering design tool for the reduction of secondary loss in turbines. However, its application on compressors have been rarely performed and reported. This paper documents the findings of the analysis for diminishing compressor stator corner separation using endwall profiling; In the study, novel profiled endwalls were designed and numerically studied on a subsonic axial-flow compressor stage. The compressor stator endwalls were profiled on both axial and azimuthal directions. The results showed, the stator corner separation was significantly suppressed under all the operating conditions by implementing this profiled endwall. Significant improvements on stage pressure ratios and stage efficiency were observed. Detailed flow field changes, as well as endwall profiling methods are provided in the paper, so that the results of this research can be referenced to other compressor designs.

Unsteady flow field under surge and rotating stall in a three-stage axial flow compressor

2011 ◽  
Vol 20 (1) ◽  
pp. 6-12 ◽  
Author(s):  
Takayuki Hara ◽  
Daisuke Morita ◽  
Yutaka Ohta ◽  
Eisuke Outa
Keyword(s):  
Flow Field ◽  
Unsteady Flow ◽  
Axial Flow ◽  
Rotating Stall ◽  
Axial Flow Compressor ◽  
Flow Compressor

C16 Effect of Rotor-Stator Gap on Internal Flow Field in an Axial Flow Compressor near Stall

2008 ◽  
Vol 2008.61 (0) ◽  
pp. 85-86
Author(s):  
Noritaka NAKAMURA ◽  
Takahiro MORIKAWA ◽  
Yasuhiro SHIBAMOTO ◽  
Ken-ichiro IWAKIRI ◽  
Satoshi GUNJISHIMA ◽  
...  
Keyword(s):  
Flow Field ◽  
Axial Flow ◽  
Internal Flow ◽  
Axial Flow Compressor ◽  
Flow Compressor

scholarly journals Experimental Investigation of the Flow Field in a Multistage Axial Flow Compressor

1996 ◽  
Vol 2 (4) ◽  
pp. 247-258 ◽  
Author(s):  
B. Lakshminarayana ◽  
N. Suryavamshi ◽  
J. Prato ◽  
R. Moritz
Keyword(s):  
Flow Field ◽  
Secondary Flow ◽  
Axial Flow ◽  
Suction Side ◽  
Mean Velocity ◽  
Axial Flow Compressor ◽  
Total Temperature ◽  
Single Sensor ◽  
Flow Compressor ◽  
Thermocouple Probe

The nature of the flow field in a three stage axial flow compressor, including a detailed survey at the exit of an embedded stator as well as the overall performance of the compressor is presented and interpreted in this paper. The measurements include area traverse of a miniature five hole probe (1.07 mm dia) downstream of stator 2, radial traverses of a miniature five hole probe at the inlet, downstream of stator 3 and at the exit of the compressor at various circumferential locations, area traverse of a low response thermocouple probe downstream of stator 2, radial traverses of a single sensor hot-wire probe at the inlet, and casing static pressure measurements at various circumferential and axial locations across the compressor at the peak efficiency operating point. Mean velocity, pressure and total temperature contours as well as secondary flow contours at the exit of the stator 2 are reported and interpreted. Secondary flow contours show the migration of fluid particles toward the core of the low pressure regions located near the suction side casing endwall corner.

Effect of hub clearance of cantilever stator on aerodynamic performance and flow field of a transonic axial-flow compressor

2021 ◽  
pp. 095441002199370
Author(s):  
Botao Zhang ◽  
Bo Liu ◽  
Xiaochen Mao ◽  
Hejian Wang
Keyword(s):  
Flow Field ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Aerodynamic Performance ◽  
Tip Clearance ◽  
Leakage Flow ◽  
Stall Margin ◽  
Axial Flow Compressor ◽  
Stator Blade ◽  
Flow Compressor

To investigate the effect of hub clearance of cantilever stator on the aerodynamic performance and the flow field of the transonic axial-flow compressor, the performance of single-stage compressors with the shrouded stator and cantilever stator was studied numerically. It is found that the hub corner separation on the stator blade suction surface (SS) was modified by introducing the hub leakage flow. The separation vortex on the SS of the stator blade root at about 10% axial chord length caused by the interaction of the shock wave and boundary layer was also controlled. Compared with the tip clearance size of the rotor blade, the stator hub clearance size (HCS) has a much less effect on the overall aerodynamic performance of the compressor, and there is no obvious effect on the flow field in the upstream blade row. With the increase of HCS, the leakage loss and the blockage degree in the flow field near the stator hub are increased and further make the adiabatic efficiency and the total pressure ratio of the compressor gradually decrease. Meanwhile, the stall margin of the compressor was changed slightly, but the response of the stall margin to the change of the HCS is nonlinear and insensitive. The stator hub leakage flow (HLF) can not only change the flow field near the hub but also redistribute the flow law within the range of the entire blade span. It will contribute to further understand the mechanism of the HLF and provide supports for the design of the cantilever stator of transonic compressors.

scholarly journals Steady and Unsteady Three Dimensional Flow Field Downstream of an Embedded Stator in a Multistage Axial Flow Compressor: Part 3 — Deterministic Stress and Heat-Flux Distribution and Average-Passage Equation System

1998 ◽  
Author(s):  
N. Suryavamshi ◽  
B. Lakshminarayana ◽  
J. Prato
Keyword(s):  
Heat Flux ◽  
Flow Field ◽  
Three Dimensional ◽  
Tangential Velocity ◽  
Axial Flow ◽  
Equation System ◽  
Radial Component ◽  
Shear Stresses ◽  
Axial Flow Compressor ◽  
Flow Compressor

The results from the area traverse measurements of the unsteady velocity and total temperature downstream of the second stator of a three stage axial flow compressor have been correlated to derive various deterministic stress and heat-flux terms. These terms are consistent with those arising from the average-passage equation system of Adamczyk (1985). The deterministic periodic stress and heat-flux terms were found to be larger than the aperiodic terms for both the normal and shear components. Consequently the terms involving the aperiodic components in the average-passage equations could be neglected for stator exit and rotor inlet flow modeling. The deterministic periodic normal and shear stresses were seen to be most significant in the stator wakes away from the endwall regions. The most significant shear stress correlation was between the axial and tangential velocity components. Since the correlations involving the radial component were small, it is postulated that the dominant mechanism for mixing (in the radial direction) is due to the steady deterministic radial velocity. All three components of deterministic heat-flux were found to be significant in this flow field especially in the wakes. The dominant terms in the average-passage equation system away from the endwalls were due to the tangential gradient compared to the radial gradient terms and both the terms were found to be of equal importance in the hub and casing endwall regions.

Effect of Turbulence Model on the Prediction of Performance and Span-Wise Mixing in High-Speed Highly-Loaded Multi-Stage Axial-Flow Compressor

2019 ◽  
Author(s):  
Takashi Goto ◽  
Tetsuya Oshio ◽  
Naoki Tani ◽  
Mizuho Aotsuka ◽  
Guillaume Pallot ◽  
...  
Keyword(s):  
Flow Field ◽  
Turbulence Model ◽  
High Speed ◽  
Axial Flow ◽  
Weno Scheme ◽  
Axial Flow Compressor ◽  
Multi Stage ◽  
Radial Profiles ◽  
Flow Compressor ◽  
Highly Loaded

Abstract Despite significant advancements in computational power and various numerical modeling in past decades, flow simulation of a multi-stage axial-flow compressor is still one of the most active areas of research, for it is the critical component in engine performance and operability, and there are so many elements that need to be looked into to predicting correct matching of the stages and accurate flow distribution inside the machine. Modeling unsteadiness, both deterministic and random types, and real geometries are among the most important features to be considered in such prediction. The authors have conducted in their previous studies a series of unsteady RANS (URANS) simulations of a 6.5-stage high-speed highly-loaded axial-flow compressor, and explored many unsteady effects as well as effects of real geometries such as Variable Stator Vane (VSV) clearance and inter-stage seal leakage flow on the compressor performance. However, all the analyses failed to predict correct stage matching, total pressure and temperature radial profiles, or mass-flow with adequate accuracies. In the present study, an Improved Delayed Detached Eddy Simulation (IDDES) with SST k-omega model is applied to the simulation of the same compressor configuration at aerodynamic design point. Fifth-order WENO scheme is employed for improved spatial accuracy to suppress significant increase in mesh size. Total number of mesh points are over 400 million for 1/10th sector model. Computations are ensemble averaged for 20 sector passage. Computed overall performance and flow field are compared with the compressor rig test data. The predictions of inter-stage total temperature radial profiles are noticeably improved over the URANS with the same mesh, discretization scheme and eddy turbulence model. Good comparison with the rig data indicates the current simulation is properly capturing the span-wise mixing phenomena. Unsteady flow field are compared between IDDES and URANS to locate the cause for the enhanced mixing. It is shown that components of Reynolds stress responsible for radial diffusion and anisotropic features are intensified in the tip leakage vortex at the rotor exit for the IDDES.

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