Flow through axial-flow-turbomachinery blading

Mapping Intimacies ◽

10.1093/oso/9780198719878.003.0014 ◽

2018 ◽

Author(s):

Marcel Escudier

Keyword(s):

Flow Velocity ◽

Compressible Flow ◽

Dimensional Analysis ◽

Incompressible Flow ◽

Compressible Fluid ◽

Axial Flow ◽

Linear Cascade ◽

Dimensional Parameters ◽

Flow Through

This chapter is concerned primarily with the flow of a compressible fluid through stationary and moving blading, for the most part using the analysis introduced in Chapter 11. The principles of dimensional analysis are applied to determine the appropriate non-dimensional parameters to characterise the performance of a turbomachine. The analysis of incompressible flow through a linear cascade of aerofoil-like blades is followed by the analysis of compressible flow. Velocity triangles for flow relative to blades, and Euler’s turbomachinery equation, are introduced to analyse flow through a rotor. The concepts introduced are applied to the analysis of an axial-turbomachine stage comprising a stator and a rotor, which applies to either a compressor or a turbine.

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Forces on Unstaggered Airfoil Cascades in Unsteady In-Phase Motion

Journal of Fluids Engineering ◽

10.1115/1.3448388 ◽

1976 ◽

Vol 98 (3) ◽

pp. 521-530 ◽

Cited By ~ 2

Author(s):

N. H. Kemp ◽

H. Ohashi

Keyword(s):

Flow Velocity ◽

Incompressible Flow ◽

Kutta Condition ◽

Harmonic Motion ◽

Thin Airfoil ◽

Through Flow ◽

Flow Through ◽

Unsteady Effects ◽

Analytical Expressions ◽

Phase Motion

Incompressible flow through an unstaggered cascade in general, unsteady, in-phase motion is considered. By methods of thin-airfoil theory, using the assumptions of wakes trailing back at the through-flow velocity, and the Kutta condition, exact analytical expressions are derived for loading, lift and moment. As application, harmonic motion is considered for plunging, pitching, and sinusoidal gusts. Numerical values of lift and moment for these three cases are given graphically (tables are available from the authors). The results show strong analogies with isolated unsteady thin-airfoil theory. They should prove useful as simple examples of unsteady effects in cascades, and as check cases for other approximate or purely numerical analyses.

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Introduction to Engineering Fluid Mechanics

10.1093/oso/9780198719878.001.0001 ◽

2018 ◽

Author(s):

Marcel Escudier

Keyword(s):

Fluid Mechanics ◽

Dimensional Analysis ◽

Gas Flow ◽

Stokes Equations ◽

Reaction Force ◽

Axial Flow ◽

Hydraulic Turbine ◽

Navier Stokes ◽

Pipe Bend ◽

Flow Through

Turbojet and turbofan engines, rocket motors, road vehicles, aircraft, pumps, compressors, and turbines are examples of machines which require a knowledge of fluid mechanics for their design. The aim of this undergraduate-level textbook is to introduce the physical concepts and conservation laws which underlie the subject of fluid mechanics and show how they can be applied to practical engineering problems. The first ten chapters are concerned with fluid properties, dimensional analysis, the pressure variation in a fluid at rest (hydrostatics) and the associated forces on submerged surfaces, the relationship between pressure and velocity in the absence of viscosity, and fluid flow through straight pipes and bends. The examples used to illustrate the application of this introductory material include the calculation of rocket-motor thrust, jet-engine thrust, the reaction force required to restrain a pipe bend or junction, and the power generated by a hydraulic turbine. Compressible-gas flow is then dealt with, including flow through nozzles, normal and oblique shock waves, centred expansion fans, pipe flow with friction or wall heating, and flow through axial-flow turbomachinery blading. The fundamental Navier-Stokes equations are then derived from first principles, and examples given of their application to pipe and channel flows and to boundary layers. The final chapter is concerned with turbulent flow. Throughout the book the importance of dimensions and dimensional analysis is stressed. A historical perspective is provided by an appendix which gives brief biographical information about those engineers and scientists whose names are associated with key developments in fluid mechanics.

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The Compressible Flow Through Cascade Actuator Discs

Aeronautical Quarterly ◽

10.1017/s0001925900001347 ◽

1958 ◽

Vol 9 (2) ◽

pp. 110-130 ◽

Cited By ~ 7

Author(s):

J. H. Horlock

Keyword(s):

Shear Flow ◽

Compressible Flow ◽

Incompressible Flow ◽

Three Dimensional ◽

Approximate Solutions ◽

Two Dimensional ◽

Guide Vanes ◽

The Past ◽

Flow Through ◽

Annular Cascade

SummaryA theory of the incompressible flow through two- and three-dimensional cascade actuator discs has been developed by several workers over the past ten years, and its accuracy has been confirmed in several experiments. This theory is briefly reviewed, and a parallel theory for subsonic compressible flow through actuator discs is developed. Approximate solutions for several examples are considered, including a compressible shear flow through a two-dimensional cascade, and a compressible flow through an annular cascade of guide vanes.

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A New Thermodynamic Diagram for Representing Steady One-Dimensional Compressible Fluid Flow

Journal of Mechanical Engineering Science ◽

10.1243/jmes_jour_1974_016_033_02 ◽

1974 ◽

Vol 16 (3) ◽

pp. 192-195 ◽

Cited By ~ 2

Author(s):

C. R. Calladine

Keyword(s):

Fluid Flow ◽

Compressible Flow ◽

Compressible Fluid ◽

Specific Volume ◽

Point Of View ◽

Volume Versus ◽

One Dimensional ◽

Compressible Fluid Flow ◽

Flow Through

A graph of specific volume versus velocity is useful for describing effects in steady, one-dimensional compressible fluid flow through a converging–diverging nozzle. From a thermodynamic point of view there is nothing new in the approach, but it may serve as a useful introduction to the characteristics of compressible flow – particularly the special conditions which prevail at the throat of a choked nozzle.

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On the Compressible Flow Losses Through Abrupt Enlargements and Contractions

Journal of Fluids Engineering ◽

10.1115/1.2911846 ◽

1994 ◽

Vol 116 (4) ◽

pp. 756-762 ◽

Cited By ~ 7

Author(s):

Predrag Marjanovic´ ◽

Vladan Djordjevic´

Keyword(s):

Experimental Data ◽

Compressible Flow ◽

Incompressible Flow ◽

System Of Equations ◽

Basic System ◽

Area Change ◽

Flow Losses ◽

Flow Parameters ◽

Flow Through ◽

D Model

The well-known structure of incompressible flow through abrupt enlargements and contractions is applied to the subsonic compressible flow through the same area change. Using the basic system of equations for 1-D model of flow, both cases are solved for adiabatic and isothermal conditions. The changes for all flow parameters (M, v, p, p0, T, T0, s) are obtained analytically and shown graphically. The results are compared with the available experimental data.

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Analysis of Viscous Laminar Incompressible Flow Through Axial-Flow Turbomachines With Infinitesimal Blade Spacing

Journal of Applied Mechanics ◽

10.1115/1.4010711 ◽

1953 ◽

Vol 20 (3) ◽

pp. 401-406

Author(s):

T. P. Torda ◽

H. H. Hilton ◽

F. C. Hall

Keyword(s):

Incompressible Flow ◽

Axial Flow ◽

Power Input ◽

Numerical Example ◽

Input And Output ◽

Flow Through ◽

Flow Variables

Abstract The Lorenz theory has been extended to the viscous, laminar, incompressible flow through axial-flow turbo-machines with infinitesimal blade spacing. Expressions are derived for the velocity components, pressure, power input and output for arbitrary blade surfaces. A numerical example is presented and the flow variables and blade surfaces are plotted.

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A numerical analysis of the flow passing through a cascade with tip clearance(Subsonic flow through a linear cascade composed of flat plates).

TRANSACTIONS OF THE JAPAN SOCIETY OF MECHANICAL ENGINEERS Series B ◽

10.1299/kikaib.56.1985 ◽

1990 ◽

Vol 56 (527) ◽

pp. 1985-1991

Author(s):

Toshinori WATANABE ◽

Isao KANAZAWA ◽

Osamu NOZAKI ◽

Atsuhiro TAMURA

Keyword(s):

Numerical Analysis ◽

Subsonic Flow ◽

Tip Clearance ◽

Flat Plates ◽

Linear Cascade ◽

Flow Through

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Extra Drag Force on a Circular Cylinder Due to the Presence of Solid Particles in Subsonic Compressible Flow

ASME 1991 Computers in Engineering Conference: Volume 1 — Artificial Intelligence; Expert Systems; CAD/CAM/CAE; Computational Fluid/Thermal Engineering ◽

10.1115/cie1991-0068 ◽

1991 ◽

Author(s):

Stanley B. Mellsen

Keyword(s):

Compressible Flow ◽

Incompressible Flow ◽

Aerodynamic Drag ◽

Collection Efficiency ◽

Reynolds Numbers ◽

Solid Particles ◽

Circular Cylinders ◽

Critical Mach Number ◽

Wide Range ◽

Inertia Parameters

Abstract The effect of particles, such as dust in air on aerodynamic drag of circular cylinders was calculated for compressible flow at critical Mach number and for incompressible flow. The effect of compressibility was found negligible for particles larger than about 10 μm, for which the air can be considered a continuum. Drag coefficient and collection efficiency are provided for a wide range of inertia parameters and Reynolds numbers for both compressible and incompressible flow.

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