Fundamentals of Turbomachines Erick Dick

1987

The state of the art in axial turbomachinery has advanced to the point where further impuovements will have to come from a better understanding and eventual control of the unsteady flow phenomena which occur in turbomachines. These unsteady flows have a significant influence on efficiency, aerodynamic stability of the compression system, aeroelastic stability, forced response, and noise generation. Over the past fifteen years, a number of workshops and symposia have been held to discuss various turbomachinery unsteady flow and aeroelastic aspects, e.g., the Project SQUID Meetings on Aeroelasticity Jn Turbomachines 1972 and on Unsteady Flow in Jet Engines 1974, the AGARD 46th Propulsion and Energetics Panel Meetings on Unsteady Phenomena in Turbomachinery 1975, the IUTAM Symposium on Aeroelasticity in Turbomachines 1976, the 2nd IUTAM Symposium on Aeroelasticity in Turbomachines 1980 and the Symposium on Unsteady Aerodynamics of Turbomachines and Propellers 1986. Tn.* idea for a thorough review and assessment of the current state of the art of unsteady turbomachinery aerodynamics dates back to the 1975 AGARD Meeting. Such a review was presented by one of the editors (M. F. Platzer) at the AGARD Conference on Unsteady Aerodynamics 1977 (AGARD-CP-227). A major conclusion of this paper was that further engine performance improvements and the avoidance of expensive engine modifications due to aerodynamic/aeroelastic stability problems will not only depend on the continued systematic research in unsteady turbomachinery aerodynamics. Rather, the need to transfer highly specialized unsteady aerodynamic and aeroelastic information to the turbomachinery design community and the introduction of young engineers to this discipline suggested the compilation of-a "Manual on Aeroelasticity in Turbomachines", similar to the "AGARD Manual on Aeroelasticity" for the aeroelastic design of flight vehicles, due to the lack of any textbook or other comprehensive compendium on unsteady aerodynamics and aeroelasticity in turbomachines. It is noteworthy, however, that several books on this subject have been published in Russia, i.e.

Computational fluid dynamics (CFD) plays an essential role to analyze fluid flows and heat transfer situations by using numerical methods. Turbomachines involve internal and external fluid flow problems in compressors and turbines. CFD at present is one of the most important tools to design and analyze all types of turbomachinery. The main purpose of this paper is to review the state of the art work carried out in the field of turbomachinery using CFD. Literature review of research work pertaining to CFD analysis in turbines, compressors and centrifugal pumps are described. Various issues of CFD codes used in turbomachinery and its parallelization strategy adopted are highlighted. Furthermore, the prevailing merits and demerits of CFD in turbomachinery are provided. Open areas pertinent to CFD investigation in turbomachinery and CFD code parallelization are also described.

1984

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43rd AIAA Aerospace Sciences Meeting and Exhibit, 2005

A threedimensional flow solver has been developed for turbomachinery components utilizing real fluid properties. The code is applicable to both incompressible and compressible flow fields. In this study, the code has been applied to the analysis of inducer and ~ ___ ____ * Aerospace Engineer, Associate Fellow AIAA.

1998

Springer eBooks, 2015

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CFD Open Series, 2023

Fluid mechanics and thermodynamics are the fundamental sciences used for turbine aerodynamic design and analysis. Several types of fluid dynamic analysis are useful for this purpose. The concept through-flow analysis is widely used in axial-flow turbine performance analysis. This involves solving the governing equations for inviscid flow in the hub-to-shroud plane at stations located between blade rows. The flow is normally considered to be axisymmetric at these locations, but still three-dimensional because of the existence of a tangential velocity component. Empirical models are employed to account for the fluid turning and losses that occur when the flow passes through the blade rows. By contrast, hub-to-shroud through-flow analysis is not very useful for the performance analysis of radial-flow turbomachines such as radial-inflow turbines and centrifugal compressors. The inviscid flow governing equations do not adequately model the flow in the curved passages of radial turbomachines to be used as a basis for performance analysis. Instead, a simplified “pitch-line” or “mean-line” one-dimensional flow model is used, which ignores the hub-to-shroud variations. These also continue to be used for axial-flow turbine performance analysis. Computers are sufficiently powerful today that there is really no longer a need to simplify the problem that much for axial-flow turbomachinery. More fundamental internal flow analyses are often useful for the aerodynamic design of specific components, particularly blade rows. These include 2D flow analyses in either the blade-to-blade or hub to shroud (Through Flow) direction, and Quasi-3D flow analyses developed by combining those 2D analyses. Wall boundary layer analysis is often used to supplement these analyses with an evaluation of viscous effects.

Volume 4: Ceramics; Concentrating Solar Power Plants; Controls, Diagnostics and Instrumentation; Education; Electric Power; Fans and Blowers, 2013

The Technological Institute of Aeronautics (ITA) is a Brazilian engineering school supported by the Command of Aeronautics, Ministry of Defense. The topic Gas Turbines taught at the Mechanical-Aeronautical Engineering undergraduate course is focused in engine performance. Handout containing the course essentials is available to the students. The handout covers the basic gas turbine theory, with emphasis on the design and off-design performance. The technological contents are presented during the detailed real cycles study. Simple gas turbines and the more sophisticated engines for aeronautical and industrial applications are covered. Calculations are supported by in-house developed software. Among such software are the ones for component and engine design and analysis and for flow calculation in blade passages, including multi-stage turbomachines. Theory is complemented with lab classes, when the students are presented to practical aspects involving gas turbine operation. The industrial world is presented to the students during visits to industries. The Gas Turbine undergraduate course is described, with details of the teaching process and the experience within the Turbomachines Department.