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Gas Turbine Blade Cooling / edited by Chaitanya D. Ghodke.
- Format:
- Book
- Language:
- English
- Subjects (All):
- Gas-turbines--Cooling.
- Gas-turbines.
- Physical Description:
- 1 online resource (xix, 215 pages) : illustrations
- Edition:
- 1st ed.
- Place of Publication:
- Warrendale, Pennsylvania : SAE International, 2018.
- Summary:
- Gas turbines play an extremely important role in fulfilling a variety of power needs and are mainly used for power generation and propulsion applications. The performance and efficiency of gas turbine engines are to a large extent dependent on turbine rotor inlet temperatures: typically, the hotter the better. In gas turbines, the combustion temperature and the fuel efficiency are limited by the heat transfer properties of the turbine blades. However, in pushing the limits of hot gas temperatures while preventing the melting of blade components in high-pressure turbines, the use of effective cooling technologies is critical. Increasing the turbine inlet temperature also increases heat transferred to the turbine blade, and it is possible that the operating temperature could reach far above permissible metal temperature. In such cases, insufficient cooling of turbine blades results in excessive thermal stress on the blades causing premature blade failure. This may bring hazards to the engine's safe operation. Gas Turbine Blade Cooling, edited by Dr. Chaitanya D. Ghodke, offers 10 handpicked SAE International's technical papers, which identify key aspects of turbine blade cooling and help readers understand how this process can improve the performance of turbine hardware.
- Contents:
- Cover
- Table of contents
- Overview
- Introduction
- CHAPTER 1 High Temperature Turbine Design Considerations
- Material Properties
- Manufacturing Processes
- Cooling Techniques
- Cooling Flow
- Cooling Air Temperature
- Mixing Losses
- Aerodynamic Losses
- Mechanical Design
- Mechanical and Thermal Life
- Metallurgical Stability
- Coatings
- Coating Interactions
- Summary
- Nomenclature
- Acknowledgments
- References
- CHAPTER 2 Summary of NASA Aerodynamic and Heat Transfer Studies in Turbine Vanes and Blades
- Aerodynamic Studies
- Cascade Tests
- Coolant Hole Angle Orientation
- Single and Multirow Coolant Ejection
- Full-Film-Cooled Vane
- Varying Primary-to-Coolant Temperature Ratio
- Effect of Ceramic Coating on Vane Efficiency
- Rotating Stage Tests
- Description of Turbines
- Test Results
- Cooling Studies
- Flat-Plate Heat Transfer Investigations
- Cascade and Engine Investigations
- Summary of Major Results
- Current Programs
- Film Cooling
- Endwall Cooling
- Impingement Cooling
- Thermal Barrier Coatings
- Symbols
- Subscripts
- CHAPTER 3 Cooling Modern Aero Engine Turbine Blades and Vanes
- Part I by Arthur Hare
- Extent of Application of Cooling
- Purposes of Cooling
- Degree of Cooling
- Some Effects on Engine Functioning
- Some Effects on Design
- Some Effects on Engine Development
- Effect on Manufacturing Cost
- Part II by H.H. Malley
- Turbine Entry Temperature
- Blade Cooling Level
- Material Creep Strength
- Cooling Air Feed System
- Combustion-Chamber Exit Temperature Traverse
- Nozzle Guide Vane Cooling
- Early Standard of Vane
- Vane with "Jet Cooled" Leading Edge
- Vane with "Tube Cooling"
- Turbine Blade Cooling
- "Triple Pass" Cooling
- "Double Pass" Cooling
- "Single Pass" Cooling
- Turbine Blade Problems
- Thermal Fatigue.
- Oxidation and Corrosion
- Creep
- Future Trends
- CHAPTER 4 An Investigation of Convective Cooling of Gas Turbine Blades Using Intermittent Cooling Air
- Results of Prior Investigations
- Experimental Results
- Analysis and Correlation
- Conclusions
- CHAPTER 5 The Prospects of Liquid Cooling for Turbines
- History of Liquid Cooling
- Possibilities for Turbine Liquid Cooling
- A Critique of Demonstrated Liquid-Cooled Turbines
- Prospects for Turbine Liquid Cooling
- A Case Study: The Cooled Radial Turbine
- Cycle Impact of Turbine Cooling
- Turbine Aerodynamic Design
- Turbine Cooling
- Appendix A Cycle Performance Data for Small Gas Turbine Components
- Appendix B Typical Turbine Design Calculations
- Turbine Cooling Design
- CHAPTER 6 Feasibility Demonstration of a Small Fluid-Cooled Turbine at 2300°F
- Aero-Thermodynamic Performance
- Turbine
- Correction Factor Analysis
- Turbine Analysis
- Heat Transfer
- Discussion
- Turbine Disc and Blade
- Turbine Inlet Nozzle
- Combustor
- Mechanical-Structural Integrity
- Mechanical Assembly
- Turbine Rotor
- Gearbox
- Turbine Blades
- Airfoil Stress Analysis
- Blade/Disc Pin Attachment
- Blade/Disc Seal
- Disc Stress Analysis
- Fuel Deposits
- Turbine Shroud
- Turbine Nozzle and Combustor Assemblies
- Manufacturing Technology
- Turbine Disc
- Disc Process
- Turbine Blade
- Blade Process
- Nondestructive Testing (NDT)
- CHAPTER 7 Design and Fabrication Aspects of Transpiration Air-Cooled Turbine Blades for 2500°F Turbine Operation
- Synopsis
- General
- Turbine Blade Design Aspects
- Porous Metal Fabrication
- Mechanical Properties of Porous Metals
- Forming of Porous Airfoils.
- Brazing of Porous Material
- Inspection of Brazed Blades
- Engine Test Program
- Summary and Conclusions
- CHAPTER 8 Design and Test of a Small Turbine at 2500°F with Transpiration-Cooled Blading
- Transpiration Cooling
- Program Objectives
- Turbine Design Problems
- Aerodynamic
- Thermal
- Mechanical
- Turbine Fabrication
- Turbine Test Program
- Cascade
- Full Stage Turbine Durability Test
- Reference
- CHAPTER 9 The Role of the Turbulent Prandtl Number in Turbine Blade Heat Transfer Prediction
- Code Selection
- Turbulent Prandtl Number Models
- Experimental Data
- Results
- CHAPTER 10 Parametric Analysis of Aero-Derivative Gas Turbine: Effect of Radiative Heat Transfer on Blade Coolant Requirement
- System Configuration
- Modeling and Governing Equations
- Air/Gas Property Model
- Compressor
- Combustion Chamber
- Cooled Gas Turbine Model
- Air-Film Blade Cooling Scheme
- Horlock et al. [8] Model for Blade Coolant Mass Fraction
- Sanjay et al. [13] Model for Coolant Mass Fraction
- Horlock and Torbidoni Model [12] for Blade Coolant Mass Fraction
- Proposed Model for Blade Coolant Mass Fraction
- Assumptions
- Calculation of Gas Turbine Work
- Results and Discussion
- Effect of TIT on Blade Coolant Mass Fraction
- Effect of Compressor Pressure Ratio on Coolant Mass Fraction
- Effect of Advancement in Blade Material Technology
- Effect of Improvement in Blade Material Temperature
- Effect of Adoption of Single-Crystal Blades
- Effect of TBC Coatings
- Variation in Gas Turbine Efficiency with rpc
- Performance Map for Proposed Model
- Contact Information
- Greek Symbols
- Subscript
- Abbreviations.
- About the Author.
- Notes:
- Description based on publisher supplied metadata and other sources.
- Includes bibliographical references.
- ISBN:
- 9781523140329
- 1523140321
- 9780768095067
- 0768095069
- OCLC:
- 1287869963
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