Author: Gregory Paul Herrick
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages :
Book Description
The quest to accurately capture flow phenomena with length-scales both short and long and to accurately represent complex flow phenomena within disparately sized geometry inspires a need for an efficient, high-fidelity, multi-block structured computational fluid dynamics (CFD) parallel computational scheme. This research presents and demonstrates a more efficient computational method by which to perform multi-block structured CFD parallel computational simulations, thus facilitating higher-fidelity solutions of complicated geometries (due to the inclusion of grids for "small" flow areas which are often merely modeled) and their associated flows. This computational framework offers greater flexibility and user-control in allocating the resource balance between process count and wallclock computation time. The principal modifications implemented in this revision consist of a "multiple grid-block per processing core" software infrastructure and an analytic computation of viscous flux Jacobians. The development of this scheme is largely motivated by the desire to simulate axial compressor stall inception with more complete gridding of the flow passages (including rotor tip clearance regions) than has been previously done while maintaining high computational efficiency (i.e., minimal consumption of computational resources), and thus this paradigm shall be demonstrated with an examination of instability in a transonic axial compressor. However, the paradigm presented herein facilitates CFD simulation of myriad previously impractical geometries and flows and is not limited to detailed analyses of axial compressor flows. While the simulations presented herein were technically possible under the previous structure of the subject software, they were much less computationally efficient and thus not pragmatically feasible; the previous research using this software to perform three-dimensional, full-annulus, time-accurate, unsteady, full-stage (with sliding-interface) simulations of rotating stall inception in axial compressors utilized tip clearance periodic models, while the scheme here is demonstrated by a simulation of axial compressor stall inception utilizing gridded rotor tip clearance regions. As will be discussed, much previous research --- experimental, theoretical, and computational --- has suggested that understanding clearance flow behavior is critical to understanding stall inception, and previous computational research efforts which have used tip clearance models have begged the question, "What about the clearance flows?". This research begins to address that question.
Facilitating Higher-fidelity Simulations of Axial Compressor Instability and Other Turbomachinery Flow Conditions
Author: Gregory Paul Herrick
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages :
Book Description
The quest to accurately capture flow phenomena with length-scales both short and long and to accurately represent complex flow phenomena within disparately sized geometry inspires a need for an efficient, high-fidelity, multi-block structured computational fluid dynamics (CFD) parallel computational scheme. This research presents and demonstrates a more efficient computational method by which to perform multi-block structured CFD parallel computational simulations, thus facilitating higher-fidelity solutions of complicated geometries (due to the inclusion of grids for "small" flow areas which are often merely modeled) and their associated flows. This computational framework offers greater flexibility and user-control in allocating the resource balance between process count and wallclock computation time. The principal modifications implemented in this revision consist of a "multiple grid-block per processing core" software infrastructure and an analytic computation of viscous flux Jacobians. The development of this scheme is largely motivated by the desire to simulate axial compressor stall inception with more complete gridding of the flow passages (including rotor tip clearance regions) than has been previously done while maintaining high computational efficiency (i.e., minimal consumption of computational resources), and thus this paradigm shall be demonstrated with an examination of instability in a transonic axial compressor. However, the paradigm presented herein facilitates CFD simulation of myriad previously impractical geometries and flows and is not limited to detailed analyses of axial compressor flows. While the simulations presented herein were technically possible under the previous structure of the subject software, they were much less computationally efficient and thus not pragmatically feasible; the previous research using this software to perform three-dimensional, full-annulus, time-accurate, unsteady, full-stage (with sliding-interface) simulations of rotating stall inception in axial compressors utilized tip clearance periodic models, while the scheme here is demonstrated by a simulation of axial compressor stall inception utilizing gridded rotor tip clearance regions. As will be discussed, much previous research --- experimental, theoretical, and computational --- has suggested that understanding clearance flow behavior is critical to understanding stall inception, and previous computational research efforts which have used tip clearance models have begged the question, "What about the clearance flows?". This research begins to address that question.
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages :
Book Description
The quest to accurately capture flow phenomena with length-scales both short and long and to accurately represent complex flow phenomena within disparately sized geometry inspires a need for an efficient, high-fidelity, multi-block structured computational fluid dynamics (CFD) parallel computational scheme. This research presents and demonstrates a more efficient computational method by which to perform multi-block structured CFD parallel computational simulations, thus facilitating higher-fidelity solutions of complicated geometries (due to the inclusion of grids for "small" flow areas which are often merely modeled) and their associated flows. This computational framework offers greater flexibility and user-control in allocating the resource balance between process count and wallclock computation time. The principal modifications implemented in this revision consist of a "multiple grid-block per processing core" software infrastructure and an analytic computation of viscous flux Jacobians. The development of this scheme is largely motivated by the desire to simulate axial compressor stall inception with more complete gridding of the flow passages (including rotor tip clearance regions) than has been previously done while maintaining high computational efficiency (i.e., minimal consumption of computational resources), and thus this paradigm shall be demonstrated with an examination of instability in a transonic axial compressor. However, the paradigm presented herein facilitates CFD simulation of myriad previously impractical geometries and flows and is not limited to detailed analyses of axial compressor flows. While the simulations presented herein were technically possible under the previous structure of the subject software, they were much less computationally efficient and thus not pragmatically feasible; the previous research using this software to perform three-dimensional, full-annulus, time-accurate, unsteady, full-stage (with sliding-interface) simulations of rotating stall inception in axial compressors utilized tip clearance periodic models, while the scheme here is demonstrated by a simulation of axial compressor stall inception utilizing gridded rotor tip clearance regions. As will be discussed, much previous research --- experimental, theoretical, and computational --- has suggested that understanding clearance flow behavior is critical to understanding stall inception, and previous computational research efforts which have used tip clearance models have begged the question, "What about the clearance flows?". This research begins to address that question.
FACILITATING HIGHER-FIDELITY SIMULATIONS OF AXIAL COMPRESSOR INSTABILITY AND OTHER TURBOMACHINERY FLOW CONDITIONS.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
The quest to accurately capture flow phenomena with length-scales both short and long and to accurately represent complex flow phenomena within disparately sized geometry inspires a need for an efficient, high-fidelity, multi-block structured computational fluid dynamics (CFD) parallel computational scheme. This research presents and demonstrates a more efficient computational method by which to perform multi-block structured CFD parallel computational simulations, thus facilitating higher-fidelity solutions of complicated geometries (due to the inclusion of grids for "small" flow areas which are often merely modeled) and their associated flows. This computational framework offers greater flexibility and user-control in allocating the resource balance between process count and wallclock computation time. The principal modifications implemented in this revision consist of a "multiple grid-block per processing core" software infrastructure and an analytic computation of viscous flux Jacobians. The development of this scheme is largely motivated by the desire to simulate axial compressor stall inception with more complete gridding of the flow passages (including rotor tip clearance regions) than has been previously done while maintaining high computational efficiency (i.e., minimal consumption of computational resources), and thus this paradigm shall be demonstrated with an examination of instability in a transonic axial compressor. However, the paradigm presented herein facilitates CFD simulation of myriad previously impractical geometries and flows and is not limited to detailed analyses of axial compressor flows. While the simulations presented herein were technically possible under the previous structure of the subject software, they were much less computationally efficient and thus not pragmatically feasible; the previous research using this software to perform three-dimensional, full-annulus, time-accurate, unsteady, full-stage (with sliding-interface) simulation.
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
The quest to accurately capture flow phenomena with length-scales both short and long and to accurately represent complex flow phenomena within disparately sized geometry inspires a need for an efficient, high-fidelity, multi-block structured computational fluid dynamics (CFD) parallel computational scheme. This research presents and demonstrates a more efficient computational method by which to perform multi-block structured CFD parallel computational simulations, thus facilitating higher-fidelity solutions of complicated geometries (due to the inclusion of grids for "small" flow areas which are often merely modeled) and their associated flows. This computational framework offers greater flexibility and user-control in allocating the resource balance between process count and wallclock computation time. The principal modifications implemented in this revision consist of a "multiple grid-block per processing core" software infrastructure and an analytic computation of viscous flux Jacobians. The development of this scheme is largely motivated by the desire to simulate axial compressor stall inception with more complete gridding of the flow passages (including rotor tip clearance regions) than has been previously done while maintaining high computational efficiency (i.e., minimal consumption of computational resources), and thus this paradigm shall be demonstrated with an examination of instability in a transonic axial compressor. However, the paradigm presented herein facilitates CFD simulation of myriad previously impractical geometries and flows and is not limited to detailed analyses of axial compressor flows. While the simulations presented herein were technically possible under the previous structure of the subject software, they were much less computationally efficient and thus not pragmatically feasible; the previous research using this software to perform three-dimensional, full-annulus, time-accurate, unsteady, full-stage (with sliding-interface) simulation.
Dissertation Abstracts International
Author:
Publisher:
ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 868
Book Description
Publisher:
ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 868
Book Description
Fluid Mechanics, Acoustics, and Design of Turbomachinery
Author: B. Lakshminarayana
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 910
Book Description
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 910
Book Description
Thermodynamics and Fluid Mechanics of Turbomachinery
Worked Examples in Turbomachinery
Author: S. L. Dixon
Publisher: Elsevier
ISBN: 1483187713
Category : Technology & Engineering
Languages : en
Pages : 117
Book Description
Worked Examples in Turbomachinery (Fluid Mechanics and Thermodynamics) is a publication designed to supplement the materials in Fluid Mechanics, Thermodynamics of Turbomachinery, Second Edition. The title provides detailed solution for the unanswered problems from the main textbook. The text first covers dimensional analysis, and then proceeds to tackling thermodynamics. Next, the selection discusses two-dimensional cascades. The text also talks about axial flow turbines and compressors, along with the three-dimensional flow in axial turbo machines. Chapter 7 covers centrifugal compressor and pumps, while Chapter 8 tackles radial flow turbines. The book will be of great use to students of mechanical engineering, particularly those who have access to the main textbook.
Publisher: Elsevier
ISBN: 1483187713
Category : Technology & Engineering
Languages : en
Pages : 117
Book Description
Worked Examples in Turbomachinery (Fluid Mechanics and Thermodynamics) is a publication designed to supplement the materials in Fluid Mechanics, Thermodynamics of Turbomachinery, Second Edition. The title provides detailed solution for the unanswered problems from the main textbook. The text first covers dimensional analysis, and then proceeds to tackling thermodynamics. Next, the selection discusses two-dimensional cascades. The text also talks about axial flow turbines and compressors, along with the three-dimensional flow in axial turbo machines. Chapter 7 covers centrifugal compressor and pumps, while Chapter 8 tackles radial flow turbines. The book will be of great use to students of mechanical engineering, particularly those who have access to the main textbook.
Turbomachinery Fluid Dynamics and Heat Transfer
Author: Hah
Publisher: Routledge
ISBN: 1351406639
Category : Technology & Engineering
Languages : en
Pages : 464
Book Description
This festschrift in honor of Professor Budugur Lakshminarayana's 60th birthday-based on the proceedings of a symposium on Turbomachinery Fluid Dynamics and Heat Transfer held recently at The Pennsylvania State University, University Park-provides authoritative and conclusive research results as well as new insights into complex flow features found in the turbomachinery used for propulsion, power, and industrial applications. Explaining in detail compressors, heat transfer fields in turbines, computational fluid dynamics, and unsteady flows, Turbomachinery Fluid Dynamics and Heat Transfer covers: Mixing mechanisms, annulus wall boundary layers, and the flow field in transonic turbocompressors The numerical implementation of turbulence models in a computer code Secondary flows, film cooling, and thermal turbulence modeling The visualization method of modeling using liquid crystals Innovative techniques in the computational modeling of compressor and turbine flows measurement in unsteady flows as well as axial flows and compressor noise generation And much more Generously illustrated and containing key bibliographic citations, Turbomachinery Fluid Dynamics and Heat Transfer is an indispensable resource for mechanical, design, aerospace, marine, manufacturing, materials, industrial, and reliability engineers; and upper-level undergraduate and graduate students in these disciplines.
Publisher: Routledge
ISBN: 1351406639
Category : Technology & Engineering
Languages : en
Pages : 464
Book Description
This festschrift in honor of Professor Budugur Lakshminarayana's 60th birthday-based on the proceedings of a symposium on Turbomachinery Fluid Dynamics and Heat Transfer held recently at The Pennsylvania State University, University Park-provides authoritative and conclusive research results as well as new insights into complex flow features found in the turbomachinery used for propulsion, power, and industrial applications. Explaining in detail compressors, heat transfer fields in turbines, computational fluid dynamics, and unsteady flows, Turbomachinery Fluid Dynamics and Heat Transfer covers: Mixing mechanisms, annulus wall boundary layers, and the flow field in transonic turbocompressors The numerical implementation of turbulence models in a computer code Secondary flows, film cooling, and thermal turbulence modeling The visualization method of modeling using liquid crystals Innovative techniques in the computational modeling of compressor and turbine flows measurement in unsteady flows as well as axial flows and compressor noise generation And much more Generously illustrated and containing key bibliographic citations, Turbomachinery Fluid Dynamics and Heat Transfer is an indispensable resource for mechanical, design, aerospace, marine, manufacturing, materials, industrial, and reliability engineers; and upper-level undergraduate and graduate students in these disciplines.
Incorporation of High-fidelity Flow Field Information Into Preliminary Design of Multi-stage Axial Compressors
Author: Alexander Timo Jörger
Publisher:
ISBN:
Category :
Languages : en
Pages : 210
Book Description
This thesis establishes an axisymmetric methodology that incorporates pre-performed high-fidelity CFD into the performance estimation of multi-stage axial compressors during preliminary design. Its key differentiator is that radial non-uniformity, inferred from three-dimensional CFD and represented using orthonormal basis functions, replaces empirical correlations of blockage, loss, and deviation as well as simplified models of flow features, such as boundary-layer growth, spanwise mixing, and endwall-corner separation. The methodology includes the effects of changes in radial non-uniformity and in blade geometry on the axisymmetric flow field. The approach can supersede current throughflow methods, increasing the fidelity of preliminary design. The primary impact of the methodology is a new capability for power gas turbine compressors to rapidly assess off-design matching at different spanwise locations along the blade height, enabling early-design choices, such as the annulus-area scheduling, based on the fidelity of CFD. Over a range of off-design conditions from near stall to near choke, the massflow capacity of a four-stage compressor was estimated within 1.2% and its efficiency within 1.5 percentage points compared to CFD at equal loading. The estimation of quasi-one-dimensional performance and the characterization of the flow close to the endwalls are improved relative to estimations of a legacy streamline curvature method since radial non-uniformity is inferred from high-fidelity flow field information. The methodology is demonstrated to be suitable for incorporation into compressor design systems.
Publisher:
ISBN:
Category :
Languages : en
Pages : 210
Book Description
This thesis establishes an axisymmetric methodology that incorporates pre-performed high-fidelity CFD into the performance estimation of multi-stage axial compressors during preliminary design. Its key differentiator is that radial non-uniformity, inferred from three-dimensional CFD and represented using orthonormal basis functions, replaces empirical correlations of blockage, loss, and deviation as well as simplified models of flow features, such as boundary-layer growth, spanwise mixing, and endwall-corner separation. The methodology includes the effects of changes in radial non-uniformity and in blade geometry on the axisymmetric flow field. The approach can supersede current throughflow methods, increasing the fidelity of preliminary design. The primary impact of the methodology is a new capability for power gas turbine compressors to rapidly assess off-design matching at different spanwise locations along the blade height, enabling early-design choices, such as the annulus-area scheduling, based on the fidelity of CFD. Over a range of off-design conditions from near stall to near choke, the massflow capacity of a four-stage compressor was estimated within 1.2% and its efficiency within 1.5 percentage points compared to CFD at equal loading. The estimation of quasi-one-dimensional performance and the characterization of the flow close to the endwalls are improved relative to estimations of a legacy streamline curvature method since radial non-uniformity is inferred from high-fidelity flow field information. The methodology is demonstrated to be suitable for incorporation into compressor design systems.
Transonic Flow Problems in Turbomachinery
Author: Thomas Charles Adamson
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 696
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 696
Book Description