Combustion and Heat Transfer in Gas Turbine Systems
eBook - PDF

Combustion and Heat Transfer in Gas Turbine Systems

Proceedings of an International Propulsion Symposium Held at the College of Aeronautics, Cranfield, April 1969

  1. 416 pages
  2. English
  3. PDF
  4. Available on iOS & Android
eBook - PDF

Combustion and Heat Transfer in Gas Turbine Systems

Proceedings of an International Propulsion Symposium Held at the College of Aeronautics, Cranfield, April 1969

About this book

Combustion and Heat Transfer in Gas Turbine Systems is a compilation of papers from the Proceedings of an International Propulsion Symposium held at the College of Aeronautics, Cranfield in April 1969. This compilation deals with research done by academic and scientific institutions and of industrial organizations, with some research papers covering atomization, fuels, and high-temperature materials. One paper describes the combustion system of the Concorde engine used in commercial flights, temperature of metal parts, and some design modifications to increase the mechanical life of the combustion system. Another paper discusses the evolution of the RB 162 combustion system that is used in the vertical takeoff and landing aircrafts. The RB 162 has many design features of the earlier single reversal chamber and differs in only one or two points. The book then notes the necessity of a plenum chamber burning to further development of supersonic engines and flight. One paper also proposes an alternative theory to the traditional ignition theory of altitude relighting such as those developed by Lewis and von Elbe. Another paper reposts on some observations made of the atomizing characteristics of air-blast atomizers and proposes simple changes to improve the performance of the atomizer by prefilming and allowing air to both sides of the fuel. This compilation will prove very helpful for aeronautical engineers, aviation designers, physicists, students of engineering, and readers who are interested in the design and development of jet engines and supersonic aircrafts.

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Yes, you can access Combustion and Heat Transfer in Gas Turbine Systems by E. R. Norster in PDF and/or ePUB format, as well as other popular books in Technologie et ingénierie & Ingénierie. We have over one million books available in our catalogue for you to explore.

Information

Publisher
Pergamon
Year
2013
Print ISBN
9780080165240
eBook ISBN
9781483151793
Topic
Technologie et ingénierie
Subtopic
Ingénierie

Table of contents

  1. Front Cover
  2. Combustion and Heat Transfer in Gas Turbine Systems
  3. Copyright Page
  4. Table Of Contents
  5. FOREWORD
  6. SESSION 1
  7. Chapter 2. THE COMBUSTION SYSTEM FOR THE OLYMPUS 593 CONCORDE ENGINE
  8. Chapter 3. THE STATISTICAL ANALYSES OF COMBUSTION CHAMBER TEMPERATURE PROFILES
  9. Chapter 4. THE STATISTICAL ANALYSES OF COMBUSTION CHAMBER TEMPERATURE PROFILES
  10. SESSION 2
  11. Chapter 6. THE EVOLUTION OF THE RB 162 COMBUSTION SYSTEM FOR V.T.O.L. APPLICATIONS
  12. Chapter 7. SOME COMBUSTION ASPECTS OF PLENUM CHAMBER BURNING
  13. Chapter 8. SOME COMBUSTION ASPECTS OF PLENUM CHAMBER BURNING
  14. SESSION 3
  15. Chapter 10. A SURVEY OF ANNULAR VAPORIZING COMBUSTION CHAMBERS
  16. Chapter 11. IGNITION THEORY AND ITS APPLICATION TO THE ALTITUDE RELIGHTING PERFORMANCE OF GAS TURBINE COMBUSTORS
  17. Chapter 12. IGNITION THEORY AND ITS APPLICATION TO THE ALTITUDE RELIGHTING PERFORMANCE OFGAS TURBINE COMBUSTORS
  18. SESSION 4
  19. Chapter 14. PREMIXED PRIMARY ZONE STUDIESUSING A MULTIPLE-PORT BAFFLE
  20. Chapter 15. THE AIR RECIRCULATION RATIO IN CAN-TYPE GAS TURBINE COMBUSTION CHAMBERS
  21. Chapter 16. THE AIR RECIRCULATION RATIO IN CAN-TYPE GAS TURBINE COMBUSTION CHAMBERS
  22. Chapter 16. COOLED GAS TURBINE BLADES
  23. Chapter 17. COOLED GAS TURBINE BLADES
  24. Chapter 18. THEORETICAL ASSESSMENT OF FLAME TUBE TEMPERATURES IN A COMBUSTOR OPERATING AT TYPICAL S.S.T. CONDITIONS
  25. Chapter 19. THEORETICAL ASSESSMENT OF FLAME TUBE TEMPERATURES IN A COMBUSTOR OPERATING AT TYPICAL S.S.T. CONDITIONS
  26. SESSION 6
  27. Chapter 21. RADIATION HEAT TRANSFER TO APOROUS SURFACE COOLED BY A TRANSPIRING FLOW
  28. Chapter 22. CORRELATION OF DATA AND PREDICTION OF EFFECTIVENESS FROM FILM COOLING INJECTION GEOMETRIES OF A PRACTICAL NATURE
  29. Chapter 23. CORRELATION OF DATA AND PREDICTION OF EFFECTIVENESS FROM FILM COOLING INJECTION GEOMETRIES OF A PRACTICAL NATURE
  30. SESSION 7
  31. Chapter 25. CORROSION TESTING OF HIGH-TEMPERATURE GAS TURBINE ALLOYS
  32. Chapter 26. HOLLOW-CONE LIQUID SPRAY IN UNIFORM AIR STREAM
  33. Chapter 27. HOLLOW-CONE LIQUID SPRAY IN UNIFORM AIR STREAM
  34. SESSION 8
  35. Chapter 29. FUELS FOR AIRCRAFT GAS TURBINE ENGINES
  36. Chapter 30. LIQUID FUEL ATOMIZERS FOR USE IN GAS TURBINE COMBUSTION MODEL EXPERIMENTS
  37. Chapter 31. LIQUID FUEL ATOMIZERS FOR USE INGAS TURBINE COMBUSTION MODEL EXPERIMENTS
  38. Chapter 32. SOME OBSERVATIONS OF THE ATOMIZING CHARACTERISTICS OF AIR-BLAST ATOMIZERS
  39. Chapter 33. SOME OBSERVATIONS OF THE ATOMIZING CHARACTERISTICS OFAIR-BLAST ATOMIZERS
  40. Chapter 34. SOME CONSIDERATIONS OF THE MEASUREMENT OF TEMPERATURES WITHIN AIRCRAFT COMBUSTION CHAMBERS, USING A CALORIMETRIC PROBE
  41. Chapter 35. SOME CONSIDERATIONS OF THE MEASUREMENT OF TEMPERATURES WITHIN AIRCRAFT COMBUSTION CHAMBERS, USING A CALORIMETRIC PROBE
  42. Chapter 36. THE MEASUREMENT OF TEMPERATURES AND RADICAL CONCENTRATIONS IN HIGH-TEMPERATURE, FLOWING-GAS STREAMS
  43. Chapter 37. THE MEASUREMENT OF TEMPERATURES AND RADICAL CONCENTRATIONS IN HIGH-TEMPERATURE, FLOWING-GAS STREAMS
  44. Delegates