Book contents
- Frontmatter
- Contents
- Preface
- Glossary
- Nomenclature
- Part 1 Design of Engines for a New 600-seat Aircraft
- Part 2 Engine Component Characteristics and Engine Matching
- Part 3 Design of Engines for a New Fighter Aircraft
- Part 4 Return to the Civil Transport Engine
- 19 A Return to the Civil Transport Engine
- 20 To Conclude
- Appendix: Noise and its Regulation
- Bibliography
- References
- Index
- Design sheets for New Large Civil Aircraft and New Fighter Aircraft
19 - A Return to the Civil Transport Engine
from Part 4 - Return to the Civil Transport Engine
- Frontmatter
- Contents
- Preface
- Glossary
- Nomenclature
- Part 1 Design of Engines for a New 600-seat Aircraft
- Part 2 Engine Component Characteristics and Engine Matching
- Part 3 Design of Engines for a New Fighter Aircraft
- Part 4 Return to the Civil Transport Engine
- 19 A Return to the Civil Transport Engine
- 20 To Conclude
- Appendix: Noise and its Regulation
- Bibliography
- References
- Index
- Design sheets for New Large Civil Aircraft and New Fighter Aircraft
Summary
INTRODUCTION
When the engine for a new civil transport, the New Large Aircraft, was considered in Chapters 1 to 10 many assumptions were introduced to make the treatment as simple as possible. In the treatment of the engine for a New Fighter Aircraft in Chapters 13–18 the level of complexity was increased. This increase in complexity included allowing the properties of the gas to be different for burned and unburned air; the effect of the mass flow of fuel added to the burned air passing through the turbine was included; the effect of the cooling air supplied to the turbines was allowed for; and the effect of the pressure losses in the combustor, the bypass duct and the jet pipe were demonstrated. It is appropriate to recalculate the performance of an engine for the civil aircraft with some of these effects included.
Another difference between the treatment for the civil engine in Chapters 1–10 and the treatment for the combat aircraft was the mixing of the core and bypass streams upstream of the final propelling nozzle in the combat engine. Some engines on subsonic transport aircraft also have mixed streams; Fig. 19.1 shows photographs of an unmixed and a mixed engine on the wing of two contemporary aircraft, the Airbus-330 and Airbus-340-300. By a simple treatment it is possible to demonstrate the advantages which the mixed configuration brings.
- Type
- Chapter
- Information
- Jet PropulsionA Simple Guide to the Aerodynamic and Thermodynamic Design and Performance of Jet Engines, pp. 269 - 282Publisher: Cambridge University PressPrint publication year: 2003