Fourth Edition — Turbines Compressors And Fans

Printed in the United States of America

10 9 8 7 6 5 4 3 2 1 Preface to the Fourth Edition Acknowledgments Nomenclature Part 1: Fundamentals Chapter 1: Introduction to Turbomachinery 1.1 Historical Development 1.2 Classification of Turbomachines 1.3 Applications and Performance Metrics 1.4 Units and Dimensions 1.5 The Fourth Edition – What’s New

2.1 First and Second Laws 2.2 Isentropic and Polytropic Efficiencies 2.3 Compressible Flow Relations 2.4 Boundary Layers and Loss Mechanisms

Outlet temperature from polytropic relation: [ \fracT_02T_01 = \left(\fracp_02p_01\right)^\frac\gamma-1\gamma \eta_p = (15)^\frac0.41.4 \times 0.89 \approx 15^0.321 = 2.39 ] So ( T_02 = 288 \times 2.39 = 688\ \textK ). Turbines Compressors And Fans Fourth Edition

8.1 Geometry and Volute Design 8.2 Thermodynamic Cycle Analysis 8.3 Applications in Turbochargers and Microturbines Part 4: Matching, Dynamics, and Testing Chapter 9: Turbine-Compressor Matching 9.1 Gas Turbine Engine Matching 9.2 Variable Geometry Solutions 9.3 Transient Operation

Fourth Edition A. M. Y. Razak Professor of Turbomachinery Institute of Aerospace Propulsion University of Manchester McGraw-Hill Education New York • Chicago • San Francisco • Athens • London • Madrid • Mexico City Milan • New Delhi • Singapore • Sydney • Toronto Copyright © 2026 by McGraw-Hill Education All rights reserved. No part of this publication may be reproduced or distributed in any form or by any means, or stored in a database or retrieval system, without the prior written consent of McGraw-Hill Education, including, but not limited to, network or other electronic storage or transmission, or broadcast for distance learning.

6.1 Fan Types – Propeller, Tube-Axial, Vane-Axial 6.2 Fan Laws and System Curves 6.3 Noise Generation and Control Part 3: Turbines Chapter 7: Axial Flow Turbines 7.1 Impulse vs. Reaction Stages 7.2 Velocity Triangles for Power Extraction 7.3 Blade Cooling – Film, Transpiration, and Impingement 7.4 Loss Correlations – Soderberg, Ainley & Mathieson, Kacker-Okapuu Printed in the United States of America 10

Let subscripts 1, 2, 3 denote rotor inlet, rotor outlet, and stator outlet respectively. For axial velocity constant ( C_x ) (free-vortex design assumed), the specific work input per stage is: [ \Delta h_0 = U (C_\theta 2 - C_\theta 1) ] where ( C_\theta ) is the tangential component. Using the change in relative tangential velocity: [ \Delta h_0 = U (W_\theta 1 - W_\theta 2) ]

5.1 Impeller and Diffuser Flow 5.2 Slip Factor and Incidence 5.3 Vaneless and Vaned Diffusers 5.4 Performance Maps and Choke

Stage pressure ratio ( \pi_s = 1.3 ), number of stages ( n = \frac\ln 15\ln 1.3 = \frac2.7080.262 \approx 10.3 ), so 10 stages (final ratio slightly adjusted). 6.1 Fan Types – Propeller

11.1 Cascade Wind Tunnel Testing 11.2 High-Speed PIV and Laser Vibrometry 11.3 Data Acquisition and Uncertainty Analysis

: A compressor stage has ( U = 250\ \textm/s ), axial velocity ( C_x = 180\ \textm/s ), inlet absolute flow angle ( \alpha_1 = 15^\circ ), outlet absolute angle ( \alpha_2 = 45^\circ ). Find specific work.

12.1 Additively Manufactured Blades 12.2 Supercritical CO₂ Turbomachinery 12.3 Hydrogen Fuel Effects

3.1 Buckingham Pi Theorem 3.2 Specific Speed and Specific Diameter 3.3 Compressibility Effects – Mach Number 3.4 Reynolds Number and Efficiency Scaling Part 2: Compressors and Fans Chapter 4: Axial Flow Compressors 4.1 Velocity Triangles 4.2 Stage Performance – Work and Pressure Rise 4.3 Degree of Reaction 4.4 Cascade Aerodynamics 4.5 Diffusion Factor and Blade Loading 4.6 Surge and Stall Phenomena 4.7 Design Example – 10-Stage HP Compressor

ISBN: 978-1-260-14789-2 MHD: 1-260-14789-5