Technical notes on next generation aero combustor design-development and related combustion research / Jushan Chin.

Format:

Book

Author/Creator:

Chin, Jushan, author.

Series:

Mechanical engineering theory and applications.

Mechanical Engineering Theory and Applications

Language:

English

Subjects (All):

Aircraft gas-turbines--Combustion.

Aircraft gas-turbines.

Physical Description:

1 online resource (168 pages)

Place of Publication:

New York, NY : Nova Science Publishers, Inc., [2021]

Summary:

"The aim of this book is to identify that extra high-pressure ratio (such as about 70) civil aero engine low emissions combustors and extra high fuel air ratio (FAR) (such as FAR greater than 0.051) military aero engine combustors make up the next generation of aero combustors. The aero thermal design of these combustors is very different from previous combustors and the major design points are proposed. Two types of high-pressure low emissions combustor design have been suggested: one is without fuel staging and the other is with fuel staging. The high FAR combustor design is brand new. The layout of the next-generation aero combustor is very different. There are no primary holes, no intermediate holes, and no dilution holes. They all have direct mixing combustion. For low-emissions combustors, it is lean direct mixing (LDM) combustion. For high-FAR combustors, it is stoichiometric direct mixing combustion. Combustion air fraction is very high (such as greater than 75%). That will induce idle condition lean blow out (LBO) issue. The present book has proposed several design approaches to solve idle LBO issue, which are effective. Pilot fuel air combustion is designed at idle condition. For civil combustor, maximum condition is designed for low emissions, while for high FAR combustor, maximum condition is designed for non-visible smoke, low luminous flame radiation and good combustion efficiency. For each type of combustor, the fuel air module configuration is designed, which is the most essential part of combustor design. The brand-new combustor cooling design has used a compound angle tangential inlet cooling hole configuration. Such a cooling design provides high cooling effectiveness. The diffuser configuration is totally new. It is an air bleeding diffuser, directly stretching forward to contact the dome. The bled air flows to the annular channel as cooling air. Aero combustor development is discussed in this book. In particular, the combustor developments from technology readiness level (TRL) 3 to TRL level 6 have been discussed in detail. Also reported is the technology to run combustor development tests correctly. Three topics of related combustion research by the present author are summarized in the brochure. They are: a. Fuel injection and co-flowing air combination. The key point is, for next generation combustor development, the designer should not only think about atomization. The combination of fuel injection and co-flowing air should be considered together as a whole device. b. Fuel spray evaporation calculation, the key is an engineering calculation of multi-component fuel evaporation shall be used. c. Non-luminous flame radiation calculation, which has been significantly updated. The present book is a summary of the author's ten years of study on next-generation aero combustors after retirement. It represents advanced aero combustor technology level"-- Provided by publisher.

Contents:

Intro

TECHNICAL NOTES ON NEXTGENERATION AERO COMBUSTORDESIGN-DEVELOPMENT ANDRELATED COMBUSTIONRESEARCH

Contents

Preface

Chapter 1Introduction to Aero CombustorDesign

1.1. Starting Points of Aero Combustor Design

1.1.1. Fuel Type

1.1.2. Engine Application

1.1.3. Requirements of Aero Combustor

1.1.4. Engine Cycle Parameters

1.1.5. Geometrical Dimension Limitations

1.2. Combustor Operational and Practical Requirements

1.3. Performance Requirements

1.3.1. Combustion Efficiency

1.3.2. Total Pressure Loss Coefficient

1.3.3. Liner Exit Distribution

1.3.4. Ground Idle Condition Lean Blow Out (LBO)

1.3.5. High Altitude Ignition

1.3.6. Smoke Level

1.3.7. Gaseous Exhaust Emissions

1.4. Combustor Working Parameters

1.4.1. Pressure

1.4.2. Temperature

1.4.3. Air Flow Rate

1.4.4. Fuel Flow Rate

1.4.5. Fuel Injector Pressure Drop

1.4.6. Combustor Fuel-Air Ratio (FAR)

1.4.7. Liner Fuel-Air Ratio

1.4.8. Liner Effective Flow Area ACd

1.4.9. Combustion Instability Pressure Fluctuation

1.5. Technology Development Program Aero Combustorand Type Engine Aero Combustor Design

1.6. Combustor Aero Thermal Design and MechanicalDesign

1.7. Preliminary Design and Detail Design

Chapter 2Briefing on Next GenerationAero Combustor Design

2.1. What Are the Next Generation Aero Combustors?

2.2. High Pressure Civil Aero Combustor Can Not UseLPP Combustion

2.3. LDM Combustion Not LDI Combustion

2.4. High FAR Combustor Needs Direct Mixing Combustionbut Not Lean

2.5. Next Generation Aero Combustors Need Very HighCombustion Air Fractions

2.6. Next Generation Aero Combustor Layout.

Chapter 3Type One High Pressure LowEmissions Civil AeroCombustor (without FuelStaging) Preliminary Design

3.1. Determination of Single Module Combustor LinerDiameter

3.2. Fuel Air Module Configuration

3.3. Idle Condition Design

3.4. Design Air Flow Pattern

3.5. Main Fuel Air Combustion Design

3.6. Main Fuel Injection Design

3.7. Main Air Module Design

3.8. Single Module Tubular Combustor Cooling Design

Chapter 4Type One High Pressure LowEmissions Combustor (withoutFuel Staging) Detail Design

4.1. Full Annular Liner Design

4.2. Transient Operation Design

4.3. Full Annular Combustor Cooling Design

4.3.1. Outer Liner Cooling Design

4.3.2. Non-Uniform Cooling Hole Axial Spacing

4.3.3. Inner Liner Cooling Design

4.4. Cooling Calculation

4.5. Combustor Inlet Diffuser Design

Chapter 5Type Two High Pressure LowEmissions Combustor (with FuelStaging) Design

5.1. Fuel Air Module

5.2. Fuel Staging

5.3. Comparison of Two Types Low Emissions CombustorDesign

Chapter 6Design of High FAR Combustor

6.1. Combustion Air Fraction

6.2. Combustion Organization Design

6.3. Combustion Efficiency Issue

6.4. Exit Distribution

6.5. Cooling Design and Calculation

6.6. Liner Cross Sectional Area

6.7. NO2 Issue

6.8. Modification of Existing Combustor

Chapter 7Next Generation AeroCombustor Development

7.1. Technology Readiness Level (TRL)

7.2. Single Module Tubular Combustor Development -TRL 3

7.4. Full Annular Combustor Development - TRL 5

7.5. Ground Engine Combustor Test - TRL 6

7.6. How to Run Combustor Development Test

7.6.1. Combustion Test Data Must Be Repeatable

7.6.2. Absolutely No Air Leaking and No Fuel Leaking

7.6.3. Take Average Readings

7.6.4. How to Judge Combustor Experiencing a Burning Out

7.6.5. How to Express Combustor Test NOx Data?.

7.6.6. Definition of Combustor Total Pressure Loss

7.6.7. Change of Combustor Test Exhaust Water Flow Rate WillAffect Combustor Pressure

7.6.8. Combustor Test to Determine the Best Main Fuel and PilotFuel Division

7.6.9. One Probe Is Not Enough for Inlet Total Pressure Measurement

7.6.10. If Any Instrument Is Out of Order, There Shall Be No CombustorTest

Chapter 8Research on Fuel Injection andCo-Flowing Air Combination

8.1. Two Types of Fuel Injection and Co-Flowing AirCombination

8.2. Combination of Pressure Swirl Nozzle and Co-Axial Flowing Air

8.3. Combination of Plain Jet Tube Injectors and Co-Axial Flowing Air

Chapter 9Fuel Spray EvaporationResearch

9.1. Some Basic Concepts

9.2. Single Component Fuel Evaporation Calculation

9.3. Multiple Component Fuel Evaporation Calculations

Chapter 10Non-Luminous Flame RadiationCalculation

10.1. Importance of Non-Luminous Flame RadiationCalculation

10.2. Non-Luminous Flame Radiation CalculationMethod Shall Be Greatly Updated

10.3. One Bar Combustion Pressure Water Vapor andCarbon Dioxide Gas Emissivity

10.4. Pressure Effect on Water Vapor Emissivity

10.5. Gas Emissivity Overlapping

10.6. Absorptivity

References

Authors' Contact Information

Index

Blank Page.

Notes:

Description based on print version record.

Other Format:

Print version: Chin, Jushan Technical Notes on Next Generation Aero Combustor Design-Development and Related Combustion Research

ISBN:

9781685071097

OCLC:

1265580571