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A special issue of Machines (ISSN 2075-1702). This special issue belongs to the section "Turbomachinery".

Deadline for manuscript submissions: closed (15 January 2024) | Viewed by 23089

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Prof. Dr. Jingyin Li

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Guest Editor

National Engineering Research Center of Fluid Machinery and Compressors, Department of Fluid Machinery, School of Energy and Power Engineering, Xi’an Jiaotong University, Xi’an 710049, China
Interests: numerical simulation and experimental measurement for supersonic flows around cascades and axial flow compressors; optimization and design of turbomachines; droplet impact processes and gas-droplet two-phase flows in fluid machinery; optimization and flow control of wind turbines

Dr. Lei Tan

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Guest Editor

State Key Laboratory of Hydroscience and Engineering, Department of Energy and Power Engineering, Tsinghua University, Beijing 100084, China
Interests: the design and optimization of pumps, turbo-machinery; two-phase flows and cavitation; basic research on fluid machinery; vibration and noise of pumps
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

Turbomachinery plays a very important role in industry and daily life, and its consumption of energy accounts for a large portion of the whole energy production worldwide. Therefore, aerodynamic design and optimization of turbomachinery is always a hot and challenging research topic, ranging from theoretic and basic scientific research to the optimal design and application of turbomachines. This Special Issue will provide an international forum for professionals, academics, and researchers to developments, including but not limited to theoretical studies, computational algorithm developments, and the design and application of high-efficiency and stable-operation turbomachinery.

This Special Issue will accept contributions describing innovative research and developments in “Aerodynamic Design and Optimization for Turbomachinery”. The Special Issue will cover a wide range of disciplines, test platforms, numerical simulation, acoustics analysis, multiphysical coupling and multidisciplinary design. It particularly welcomes those emerging methodologies and techniques which bridge theoretical studies and applications in turbomachinery design and optimization.

The proposed Special Issue particularly fits the following scopes of MDPI’s Machines journal:

All aspects of turbomachinery design and optimization methods;
New turbomachinery design method/theory/modified empirical formula;
Turbomachinery aerodynamic performance test platform and experimental research;
Advances in fluid dynamics of turbomachinery and high-precision numerical simulation methods;
Application of multi/many objectives optimization algorithm in turbomachinery optimization;
Design optimization methods and CFD analysis of turbomachinery components;
Multidisciplinary design of turbomachinery (e.g., efficiency, acoustics, strength, and vibration);
Two-phase flow and multi-phase flow in turbomachinery;
Vortex dynamics and boundary layers in turbomachinery;
The prediction of stall and surge condition, and flow range extension method of turbomachinery.

Prof. Dr. Jingyin Li
Dr. Lei Tan
Guest Editors

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Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Machines is an international peer-reviewed open access monthly journal published by MDPI.

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Keywords

turbomachinery design and optimization
aerodynamic performance test platform
acoustics analysis
turbulence and vortex structure analysis
turbulence and boundary layers test
high-precision numerical simulation method
multiphysical coupling and multidisciplinary design
machine learning and evolutionary algorithms application

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Published Papers (12 papers)

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Research

14 pages, 5674 KiB

Open AccessArticle

Research on the Influence of Disc–Drum Connection Bolt Preloading Rotor Assembly Modal Characteristics and Diagnosis Technology

by Haijun Wang, Pu Xue, Yonghong Zhang, Liang Jiang and Shengxu Wang

Machines 2024, 12(1), 83; https://doi.org/10.3390/machines12010083 - 22 Jan 2024

Viewed by 1388

Abstract

The drum rotor of an aero-engine is connected by one or multiple mounting edges through bolts, and their dynamics are significantly influenced by the preload state of the bolts. Long working hours in challenging environments can result in the deterioration of bolt pre-tightening during assembly or service, which impacts the rotor’s dynamic stability and overall performance. Currently, there are no available methods for detecting the dynamic characteristics of the drum connection components. This paper analyzes the impact of the natural characteristics of the drum composite structure of a high-pressure aero-engine turbine based on the refined finite element method when the preloading state changes. Two conditions of deviation and uneven stiffness distribution were applied to the connected components of the drum. The analysis focused on the impact of the pre-tightening state on its natural frequency. After analyzing the feasibility of identifying the pre-tightening state, two methods are proposed. These methods focus on changes in natural frequency and mode shape, specifically the sensitive natural frequency change method and the mode step change method. The methods proposed in this paper can serve as a reference for evaluating the quality of assembling complex disc–drum structures with multiple bolt connections. Full article

(This article belongs to the Special Issue Aerodynamic Design and Optimization for Turbomachinery)

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15 pages, 4602 KiB

Open AccessArticle

Influence of Upstream Sweeping Wake Number on the Unsteady Flow Mechanism in an Integrated Aggressive Intermediate Turbine Duct

by Xiaoqing Ouyang, Zhijun Lei, Hanliu Deng, Hongrui Liu, Xingen Lu, Gang Xu and Junqiang Zhu

Machines 2023, 11(7), 728; https://doi.org/10.3390/machines11070728 - 10 Jul 2023

Viewed by 956

Abstract

This paper focuses on the dynamic internal flow in the integrated aggressive intermediate turbine duct (AITD) with different HPT wake numbers, using CFX Solver with dynamic Reynolds-averaged Navier–Stokes equations (RANS), the shear stress transmission κ-ω turbulence model (SST) and the γ-θ transition model. The HPT wakes are simulated using sweeping rods, with the number of rods ranging from 14 to 56 and a reduced frequency of 1.07. The increasing wake number reduces the radial pressure gradient in the integrated AITD, and then decelerates the radial migration and dissipation of wake vortices, so that some residual wakes can reach the integrated low-pressure turbine guide vane (LPT-GV) to enhance the suppression of flow separation to a certain extent. On the other hand, the increase in wake number can also weaken the skewness and stretching of the wake, thereby increasing the duration of flow separation suppression. When there are too many wakes, the mixing between adjacent wakes accelerates the dispersion of wake vortices, leading to increased total pressure loss and an enhanced turbulence intensity. This enhanced turbulence intensity promotes bypass transition on the suction surface of the LPT-GV in advance, thereby completely eliminating flow separation on the LPT-GV in the entire spatiotemporal domain, which is beneficial for reducing separation loss, but also increasing turbulent viscous loss. When N ≤ 28, the gross loss of the integrated AITD studied in this paper reaches a minimum value (around 0.22), as the benefits brought by the wake suppression of flow separation can offset the wake dissipation loss and the turbulent viscous loss caused by the wake-induced transition. Considering that wake loss is inherently present, using sweeping wakes to inhibit the flow separation on the integrated LPT-GV can bring certain aerodynamic benefits when the wake number is less than 28. Full article

(This article belongs to the Special Issue Aerodynamic Design and Optimization for Turbomachinery)

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24 pages, 6208 KiB

Open AccessArticle

Design of Radial-Inflow Turbines for Low-Temperature Organic Rankine Cycle

by Jiangnan Zhang and Yi Tang

Machines 2023, 11(7), 725; https://doi.org/10.3390/machines11070725 - 9 Jul 2023

Viewed by 1524

Abstract

This study presents the development of a design method that has been extended to the design of radial-inflow turbines operating in organic Rankine cycles (ORC). Both the conventional design method and the circulation method available in the literature have been reviewed. The two main limitations of the current circulation method that make it not suitable for the ORC turbine design are the lack of real gas capability and 3D blades with high stresses. Using the circulation method, the flow field is decomposed into a potential part and a rotational part. The mean velocity field and the periodic velocity field are solved separately. To model the thermodynamic properties of the real gas, NIST REFPROP or CoolProp are used. The blade geometry is then solved iteratively by assuming that the velocity vector is parallel to the blade surface. The blade boundary condition is modified to force the blade camber to be radial-fibred, which is helpful to reduce the centrifugal bending stress on the blade. All the formulations are derived step by step, and the numerical treatments, including grid generation, numerical differentiation, computational scheme, and convergence, are discussed in detail. This method is validated by designing a R245fa ORC turbine rotor. The performance of the rotor design is predicted by CFD and FEA simulations, and it is compared to the results using other methodologies in the literature. Full article

(This article belongs to the Special Issue Aerodynamic Design and Optimization for Turbomachinery)

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22 pages, 9850 KiB

Open AccessArticle

Design Optimization of 1.5-Stage Transonic Compressor Based on BPNN Surrogate Model and NSGA-II

by Xinlong Li, Yun Jin, Shuaipeng Liu, Shaojuan Geng, Xiaoyu Zhang and Hongwu Zhang

Machines 2023, 11(6), 631; https://doi.org/10.3390/machines11060631 - 6 Jun 2023

Cited by 2 | Viewed by 1263

Abstract

To achieve multi-objective aerodynamics design optimization for a 1.5-stage transonic compressor, a design platform incorporating blade parameterization methods, a BPNN surrogate model, and the NSGA-II optimization method was developed. The stagger angle distribution of three blade rows was selected as the optimization variable, with isentropic efficiency at the new design condition and stall margin set as the goal functions. Results demonstrated that, without altering the blade profile shape and endwall contour, the flow rate at design condition increased by 7.1%, stall margin increased by 1.8%, isentropic efficiency decreased by 0.0087, and total pressure ratio experienced a slight increase. The flow field at different conditions before and after optimization was compared and analyzed. The analysis indicated that the tangential velocity of rotor outlet becomes the determining factor for the compressor’s work capacity. The relative Mach number at the rotor inlet emerged as the key parameter affecting shock wave intensity and shock wave/boundary layer interaction, which directly influenced the efficiency of the rotor passage. At near stall condition, the stator vane root’s stagger angle is crucial for the compressor’s performance. Full article

(This article belongs to the Special Issue Aerodynamic Design and Optimization for Turbomachinery)

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14 pages, 790 KiB

Open AccessArticle

Leading-Edge Erosion and Floating Particles: Stagnation Point Simulation in Particle-Laden Turbulent Flow via Lagrangian Particle Tracking

by Reza Hassanian and Morris Riedel

Machines 2023, 11(5), 566; https://doi.org/10.3390/machines11050566 - 19 May 2023

Cited by 5 | Viewed by 2120

Abstract

Since the stagnation point is subject to straining motion, this 3D experiment is an effort to simulate the stagnation plane, which applies to studying the particle erosion in rotary machine blades, such as wind turbines, gas turbines, and compressors. Wind turbine blade erosion, caused by particles such as sand, ice, insects, raindrops, and snowflakes, can significantly impact turbine efficiency, as with other rotary machines. Previous research has indicated that flow geometry and gravity can influence particle dynamics statistics. The current study’s laboratory experiment simulates the airfoil’s stagnation plane to investigate how floating particles cause erosion. The experiment involves seeding tracers and inertial particles in a strained turbulent flow with specific turbulent intensity, strain rate, and the presence of gravity. It is conducted on initially homogeneous turbulence undergoing a sudden axisymmetric expansion. The flow was generated in

100 < R e_{λ} < 160

. The Lagrangian particle tracking technique based on the 4-frame best estimate method was employed to measure the velocity field. The obtained results are with two different mean strain rates and Reynolds–Taylor microscales in the presence of gravity, which has not been considered in most numerical studies in a particle-laden turbulent flow. It provides a transparent window to investigate how particles of different sizes with distinct strain rates flow and their relationship to the turbulence intensity affects the erosion. Two most important issues are observed in the presence of gravity: Increasing the turbulence intensity from

R e_{λ} = 100

to 160 led to a 10–23% increase in the erosion ratio, depending on the particle type and the flow strain rate. Likewise, a doubled mean strain rate of the flow (caused by deformation/shear flow) resulted in a 3–10% increase in erosion, depending on the particle type and Reynolds number. Moreover, the influence of gravity could potentially play a significant role in this observation. Full article

(This article belongs to the Special Issue Aerodynamic Design and Optimization for Turbomachinery)

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15 pages, 6575 KiB

Open AccessArticle

Optimization Design and Pressure Fluctuation Suppression Based on Orthogonal Method for a Centrifugal Compressor

by Huanxin Zhao, Lei Tan, Dangguo Yang, Bing Liu, Honggang Fan and Hongshuai Li

Machines 2023, 11(5), 559; https://doi.org/10.3390/machines11050559 - 16 May 2023

Cited by 1 | Viewed by 1534

Abstract

An air compressor is the core component of the air supply system of a hydrogen fuel cell, which demands high efficiency and reliable stability in a wide operation region. In this work, a centrifugal air compressor for a hydrogen fuel cell is first designed and then measured experimentally. Furthermore, a test rig for assessing the aerodynamic performance of the centrifugal air compressor is established, which includes a pipeline, gas flowmeter, flow regulating valve, pressure transmitter, centrifugal compressor, controller, DC power supply and computer. Then, the orthogonal method is employed to conduct the aerodynamic performance optimization. Four optimization parameters—including blade number, blade angle at the inlet, blade angle at the outlet and wrap angle—are set with three levels. Nine compressor individuals are designed according to the orthogonal method, and then numerical simulation is implemented to confirm the aerodynamic performance and flow pattern. Results show that the blade number has the greatest influence on the compressor’s performance, and the blade angle at inlet is also very important. The optimal performance of the compressor improves compared to that of the baseline compressor; the efficiencies of the baseline compressor and optimal compressor are 81.3% and 83.8%, respectively, improving by 2.5%. The frequency domain of pressure fluctuation in the centrifugal compressor is related to the stator-rotor interaction. The peak value of pressure fluctuation amplitude occurs at the rotation frequency of 833 Hz and its harmonic frequency. In comparison with the baseline compressor, the pressure fluctuation amplitude of the optimal compressor is obviously reduced, especially near the volute tongue. Full article

(This article belongs to the Special Issue Aerodynamic Design and Optimization for Turbomachinery)

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18 pages, 8649 KiB

Open AccessArticle

Performance Investigation of a Large Turning Blade for Marine Gas Turbine Based on Experimental and Numerical Methods

by Mengyao Qi, Xiaodong Ren, Xuesong Li, Yaobin Xiao and Yuhong Li

Machines 2023, 11(3), 346; https://doi.org/10.3390/machines11030346 - 3 Mar 2023

Cited by 2 | Viewed by 1657

Abstract

Replacing the last-stage stator and the outlet guide vane of the low-pressure compressor of the marine gas turbine with a large turning blade can reduce the number of compressor blades and reduce the size and weight of marine gas turbines. At present, there are few studies on similar profiles, and it is necessary to verify the feasibility of this type of compressor profile with a large turning angle. The performance of this profile is investigated by combining experimental measurement with numerical simulation calculation. The analysis of the experimental and numerical results reveals that this profile has a large flow turning angle, a wide operating range, and low overall total pressure losses. The loss of the profile only suddenly increases at some large positive angles of attack due to the large separation of the suction surface. The results show that this profile can compress air and increase the turning ability at a low loss, and can play the role of both the original last-stage stator and the outlet guide vane. This research provides a reference for the design and analysis of marine gas turbines and guidance for the application of the blade to gas turbines in other fields. Full article

(This article belongs to the Special Issue Aerodynamic Design and Optimization for Turbomachinery)

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17 pages, 10181 KiB

Open AccessArticle

Vortex Structure Topology Analysis of the Transonic Rotor 37 Based on Large Eddy Simulation

by Kunhang Li, Pengbo Tang, Fanjie Meng, Penghua Guo and Jingyin Li

Machines 2023, 11(3), 334; https://doi.org/10.3390/machines11030334 - 28 Feb 2023

Viewed by 1817

Abstract

Highly three–dimensional and complex flow structures are closely related to the aerodynamic losses occurring in the transonic axial–flow compressor. The large eddy simulation (LES) approach was adopted to study the aerodynamic performance of the NASA rotor 37 for the cases at the design, the near stall (NS), and the near choke (NC) flow rate. The internal flow vortex topology was analyzed by the Q–criterion method, the omega (Ω) vortex identification method, and the Liutex identification method. It was observed that the Q–criterion method was vulnerable to being influenced by the flow with high–shear deformation rate, especially near the end–wall regions. The Ω method was adopted to recognize the three–dimensional vortex structure with a higher precision than that of the Q–criterion method. Meanwhile, the Liutex vortex identification method showed a good performance in vortex identification, and the corresponding contribution of Liutex components in the vortex topology was analyzed. The results show that the high–vortex fields around the separation line and reattachment line had high vortex components in the x–axis, the tip clearance vortices presented a high–vortex component in the y–axis, and the suction side corner vortex possessed high–vortex components in the y– and z–axes. Full article

(This article belongs to the Special Issue Aerodynamic Design and Optimization for Turbomachinery)

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21 pages, 6738 KiB

Open AccessArticle

Flow Capacity Optimization of a Squirrel Cage Fan with a New Rounded Rectangle Volute under Size Limitation

by Jin Xiong, Jie Tang, Penghua Guo and Jingyin Li

Machines 2023, 11(2), 283; https://doi.org/10.3390/machines11020283 - 13 Feb 2023

Cited by 4 | Viewed by 2666

Abstract

Squirrel cage fans (SCFs) are widely used in a variety of household appliances. Due to the restriction on installation size, the design of high-efficiency SCFs with high flow capacities is an important topic. In this study, we proposed a novel rounded rectangle volute profile (RRVP) for the design of compact high-flow SCFs. At first, we used computational fluid dynamics (CFD) to simulate the aerodynamic performances of three SCFs having the same impeller but different volutes, which were the common logarithmic-spiral volute profile, the cutting volute profile, and the RRVP volute at the maximum flow rate working condition. The CFD simulations indicate that the fan with RRVP volute has the highest flow rate at the maximum flow rate working condition. Then, we proposed a parameterization method for the RRVP with 16 control variables. The multiobjective evolutionary algorithm based on decomposition (MOEA/D) and Kriging model was used to optimize the aerodynamic shape of the compact SCF with an RRVP volute. Twenty-three control variables were used in the multiobjective optimization process, including the optimization of the blade angles and the impeller position. Optimization results show that the maximum volumetric flow rate of the optimal SCF with an RRVP volute increases from 147.1 cubic feet per minute (CFM) to 191.1 CFM, and the fan efficiency also increases from 32.21% to 33.5%, compared with the original SCF with the common logarithmic-spiral volute. Two main factors were found to increase the flow capacity and efficiency of the optimal SCF under strict size constrains. First, the RRVP became smooth and large, which reduced the flow loss and increased the flow cross-section; second, the eccentrically mounted impeller of the optimal fan enlarged the flow section near the outlet of the volute. Full article

(This article belongs to the Special Issue Aerodynamic Design and Optimization for Turbomachinery)

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18 pages, 9044 KiB

Open AccessArticle

Aerodynamic Optimization and Mechanism Investigation on Performance Improvements in a Transonic Compressor Cascade

by Fanjie Meng, Chaoxuan Gong, Kunhang Li, Jin Xiong, Jingyin Li and Penghua Guo

Machines 2023, 11(2), 244; https://doi.org/10.3390/machines11020244 - 7 Feb 2023

Cited by 2 | Viewed by 1870

Abstract

In this paper, a transonic compressor cascade was optimized to improve its aerodynamic performance. A new blade parameterization method with 16 control variables was first proposed to fit the shapes of the suction and the pressure side, as well as the leading edge. Then, the Kriging surrogate-model-based genetic algorithm (GA) was used to optimize the performance of the transonic cascade. The optimization algorithm is effective in reducing the total pressure loss while extending the working range of the cascade. The results show that the total pressure loss coefficient could be reduced by 11% at the best airflow angle and the working range could be extended by 6.9% for the optimized cascade in two-dimensional simulations. Similar improvement results could also be obtained in the simulations of their linear cascade cases. Detailed analyses show that the relative maximum thickness positions of the optimized blades move forward by about 10% to the leading edge, and the radii of curvature of the front half of the suction and pressure surfaces increase, compared with the initial blade. This makes the front half of the optimized blades look more closely like a wedge. Consequently, the passage shock strength is reduced and the shock changes from the passage normal shock to oblique shock. The weakened shock strength leads to the disappearance of the flow separation caused by the shock boundary layer interaction on the suction surfaces of the optimized blades, and results in a narrowed wake width at the outlet section. Full article

(This article belongs to the Special Issue Aerodynamic Design and Optimization for Turbomachinery)

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17 pages, 7096 KiB

Open AccessArticle

Optimization Design of Aspect Ratio and Solidity of a Heavy-Duty Gas Turbine Transonic Compressor Rotor

by Shuaipeng Liu, Shaojuan Geng, Xinlong Li, Yun Jin and Hongwu Zhang

Machines 2023, 11(1), 82; https://doi.org/10.3390/machines11010082 - 9 Jan 2023

Cited by 6 | Viewed by 2410

Abstract

To investigate the influence of blade aspect ratio and solidity on the performance of heavy-duty gas turbine transonic compressors, a multi-objective optimization design platform was built by adopting the blade parameterization method based on the superposition of thickness distribution on the suction surface, the Kriging surrogate model, and the NSGA-II optimization method. The spanwise distribution of solidity and number of blades were the optimization variables. The multi-objective optimization was carried out with isentropic efficiency and stall margin as the objective parameters for the inlet stage transonic rotor of an F-class heavy-duty gas turbine compressor. The results show that the isentropic efficiency and stall margin at design condition with a constant mass flow rate can be improved by 0.96% and 18.7%, respectively, and the total pressure ratio can also increase. The analysis shows that, for regions where the shock wave–boundary layer interaction is obvious, increasing the solidity can reduce the shock wave loss, the shock wave–boundary layer interaction loss, and the end wall loss, and reducing the aspect ratio can reduce the blade boundary layer loss. The spanwise distributions of solidity and aspect ratio determine the stall margin by affecting the radial matching of the load of each blade section. Tip solidity near the tip region needs to be determined according to the pressure field established by the bulk of the flow. Full article

(This article belongs to the Special Issue Aerodynamic Design and Optimization for Turbomachinery)

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22 pages, 9665 KiB

Open AccessArticle

Influence of Position of Intake Struts on Unsteady Load and Vibration of First-Stage Rotor

by Wei Peng, Xiaodong Ren, Xuesong Li, Chunwei Gu, Hong Wu and Xiaobin Que

Machines 2022, 10(11), 1096; https://doi.org/10.3390/machines10111096 - 18 Nov 2022

Cited by 1 | Viewed by 2035

Abstract

To investigate the influence law and mechanism of the relative circumferential position of intake struts on the unsteady load and vibration of the first stage rotor, the first 1.5-stage of a heavy-duty gas turbine compressor with intake struts was numerically simulated. The analysis of the flow field and vibration of the rotor blade reveals that the circumferential position of intake struts has little effect on aerodynamic performance but obviously changes the unsteady load and vibration level of the rotor blade. When strut and inlet guide vane wakes coincide, they are strengthened, resulting in the overall enhancement of the unsteady load and vibration on the rotor blade. The circumferential position of struts changes the combined effect of strut wakes and the first stage stator potential flow on the rotor blade, which has an obvious influence on the unsteady load and vibration in the middle chord length but has little influence on the unsteady load near the leading and trailing edges. Research results provide reference and guidance for the installation of struts. Full article

(This article belongs to the Special Issue Aerodynamic Design and Optimization for Turbomachinery)

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