Thermodynamic Analysis and Performance Characteristics

Aeronautic design SCHOOL OF MECHANICAL ENGINEERING AND DESIGN THE THERMODYNAMIC ANALYSIS AND PERFORMANCE CHARACTRISTICS OF A TURBOFAN JET ENGINE By J. E, Ibok 2011 Supervisor: Dr Lionel Ganippa ABSTRACT This work centers around the exhibition investigation of a twin spool blended stream turbofan motor. The fundamental target was to explore the impacts of utilizing hydrogen, lamp oil and petroleum gas fuel on the presentation qualities, for example, net push, explicit fuel utilization and propulsive effectiveness of the turbofan.Another point of this work was to present the idea of exergy and thermoeconomics investigation for twin spool blended stream turbofan motor and show the segments that contributes the most to the wastefulness of the motor. A conventional reproduction was done utilizing Gas Turb 11 programming to get sensible investigation results that were confirmed with a continuous JT8D-15A turbofan motor. The parametric investigation was accomplished for consistent estimatio n of mass stream pace of fuel and steady turbine gulf temperature for each of the three fuels.The result were legitimately acquired for these examination cases and talked about appropriately. Brunel University Mechanical Engineering Academic Session: 2010/2011 Name of Student: Johnson Essien Ibok Supervisor:Dr Lionel Ganippa Title: The Performance Characteristics and Thermodynamics Exergy and Thermoeconomics examination of a Twin Spool Mixed Flow Turbofan Engine Operating at 30,000ft at M0 0. utilizing Kerosene, gaseous petrol and Hydrogen Fuel. Theoretical: This work centers around the exhibition investigation of a twin spool blended stream turbofan motor. A conventional reenactment was completed utilizing Gas Turb 11 programming to get sensible investigation results that were checked with an ongoing JT8D-15A turbofan motor. The parametric examination was accomplished for consistent estimation of mass stream pace of fuel and steady turbine delta temperature for each of the three fu els.The result were legitimately acquired for these investigation cases and talked about in like manner. Targets: The primary point of this work is to lead the parametric cycle reenactment of a twin spool blended stream turbofan motor and explore the presentation qualities of it. Another point of this work is to show the impacts of utilizing hydrogen, Kerosene and petroleum gas fuel on the general execution of the twin spool blended stream turbofan engine.Also, the reason for this work is to present the utilization of the second law of thermodynamics examination known as exergy and thermoeconomics in investigation the twin spool blended stream turbofan motor Background/Applications: This work is material from numerous points of view with regards to the general execution improvement and practicality examination of a fly motor. This work identifies with the aviation and aeronautics businesses since the turbofan motor is among the tremendous number of fly motor utilized in drive of air crafts.There is expanding pressure in the flight business to lessen contamination and exhaustion of vitality assets while simultaneously keeping up sensible venture cost and high generally speaking execution. Subsequently, this exploration was directed in order to come up with another answer for this issue. Ends: The fundamental end drawn from the presentation examination is that hydrogen fuel created the most noteworthy push level and the least explicit fuel utilization between the three fills for a steady mass stream pace of fuel.Kerosene fuel produced push level can be expanded on the off chance that it is blended in with a limited quantity of hydrogen. The Exit fly speed proportion stayed consistent in spite of the expanding sidestep proportion for each of the three powers at steady mass stream pace of fuel. Utilizing the exergetic examination demonstrated that the burning chamber and the blender contributed the most to the wastefulness of the turbofan motor. The measure of exer gy moved into the turbofan motor by hydrogen was drained in the littlest proportion contrasted with petroleum gas and lamp oil for steady mass stream pace of fuel.The thermoeconomics examination demonstrated that it is desirable over utilize nearby based cost assessment to amount explicit thermoeconomics cost of push than the worldwide technique since the worth was lower. Results: The outcomes got from the reproduction utilizing Gas Turb 11 delivered a blunder scope of 0. 25% †8. 5% when confirmed with the genuine test information of the JT8D-15A turbofan motor. The outcomes acquired for the examination characterized a reference configuration point where the parametric investigation was led on. The investigation was done in three cases as demonstrated plainly in the test grid in table 1 below.Analysis| Parameters being varied| Parameters Kept Constant| Performance Characteristics| case 1| * Bypass proportion * Turbine Inlet temperature| * HPC Pressure Ratio * LPC Pressure Ratio * Fan Pressure Ratio| * Velocity proportion * Fuel-Air-proportion * Turbine gulf temperature * Net push * Specific Fuel Consumption * Thermal proficiency * Propulsive efficiency| case 2| * Bypass Ratio * Three diverse fuelsmH2mCH4mC12H23| * Mass stream pace of fuel * HPC Pressure Ratio * LPC Pressure Ratio * Fan Pressure Ratio| | Case 3| * Bypass Ratio * Three distinctive fuelsmH2mCH4mC12H23| * Turbine delta temperature * HPC Pressure Ratio * LPC Pressure Ratio * Fan Pressure Ratio| | Table 1 The Test framework of the Parametric Analysis. The exergy examination was accomplished for the parametric investigation of case 2 and case 3 where the exergy annihilation rates, exergetic productivity, exergy improvement potential rate and fuel consumption proportion were determined. The dispersion of these outcomes all through every segment of the turbofan motor was spoken to with bar graphs and Grassmann chart. The thermoeconomics investigation was directed for examination case 2 utilizing l amp fuel fuel.The explicit thermoeconomics cost of push was determined utilizing worldwide and nearby based cost assessment techniques. Affirmations First of all, I might want to thank my folks for their money related help and consolation on the grounds that without them I would not be here and have the option to accomplish this work. I am profoundly appreciative to my director, Dr Lionel Ganippa for having confidence in me and allowing me the chance to work with him in this field of study. I am additionally grateful to him for offering the fundamental direction and guidance and his excitement and inventive thoughts propelled me. At long last, I might want to say thanks to Mr Joachim Kurzke for giving me the vital programming required for my thesis. Table of ContentsAcknowledgements I Contents ii List of Notations and Subscripts iv List of Tables vi List of Figures vi Chapter 1: Introduction1 1. 1. Points and Objectives2 1. 2. Computational Modeling3 Chapter 2: Jet Engines4 2. 1. Ex ecution characteristics4 2. 1. 1. Thrust4 2. 1. 2. Warm Efficiency5 2. 1. 3. Propulsive efficiency5 2. 1. 4. Generally speaking efficiency6 2. 1. 5. Explicit Fuel Consumption6 2. 2. Fuel and Propellants For Jet Engines7 Chapter 3: Turbofan Jet Engines †¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦ †¦8 3. 1. Presentation 8 3. 2. Grouping of Turbofan Engines9 3. 3. Significant Components of a Turbofan Engine10 3. 3. 1. Diffuser10 3. 3. 2. Fan and Compressor11 3. 3. 3. Ignition Chamber12 3. 3. 4. Turbine13 3. 3. 5. Fumes Nozzle14 3. 4.Thermodynamic Process and Cycle of a Twin Spool Mixed Flow Turbofan Engine15 Chapter 4: Mathematical and Gas turb 11 Modeling of the turbofan Engine18 4. 1. Station Numbering and Assumptions18 4. 2. Configuration Point Cycle Simulation of the Turbofan Engine18 4. 3. Off-structure Point Cycle Simulation of the Turbofan Engine21 4. 3. 1. Module/Component Matching 22 4. 3. 2. Off-Design Point Component Modeling22 Chapter 5: Methodology, Results and Discussions26 5. 1. General Relationship conditions of the Major Parameters27 5. 2. Results and Discussions of Parametric cycle Analysis of Case 129 5. 3. Results and Discussions of Parametric Cycle Analysis of Case 235 5. 4.Results and Discussions of Parametric Cycle Analysis of Case 343 Chapter 6: Exergy and Thermoeconomics Analysis of the Turbofan Engine49 6. 1. Exergy Analysis49 6. 1. 1. Exergy Analysis Modeling 50 6. 1. 2. Exergy and Energy Balance Equations of the Components58 6. 1. 3. General Relationships in Exergetic Analysis of the Turbofan Engine60 6. 1. 4. Results and Discussions61 6. 1. 5. Grassmann Diagram72 6. 2. Thermoeconomics Analysis74 6. 2. 1. Thermoeconomics Analysis Modelling74 6. 2. 2. Worldwide Based Cost Evaluation76 6. 2. 3. Neighborhood Based Cost Evaluation77 6. 2. 4. Results and Discussion of the Thermoeconomics Analysis78 Chapter 7 Concl usions and Future Work80 Reference Appendix An Exergy Analysis Results Appendix B Thermoeconomics Analysis resultsList of Notations and Units ?| Isentropic efficiency| ?| Total Pressure ratio| m| Mass Flow Rate (kg/s)| f| Fuel/Air Ratio| M| Mach Number| Pt| Total weight (kPa)| Tt| Total Temperature (K)| NCV| Net Calorific Value (MJ/kg)| Ht| Total Enthalpy (kJ/kg)| V| Velocity (m/s)| ?| Bypass Ratio| T| Static Temperature (K)| P| Static Pressure (kPa)| N| Actual Spool Speed (RPM)| Nc| Corrected Spool Speed (RPM)| mc| Corrected Mass Flow Rate (kg/s)| R| Universal Gas Constant (kJ/kmolK)| ?0| Standard Chemical Exergy (kJ/kmol)| Ex| Exergy Rate (MW)| xi| Mole Fraction| cp| Specific Heat at Constant Pressure (kJ/kgK)| ?| Ratio of Chemical Exergy to NCV| ?| Exergetic Efficiency| | Fuel Depletion Ratio| W| Power Rate of Work done (MW)| List of Subscripts| | LPT| Low Pressure Turbine| HPT| High Pressure Turbine| CC| Combustion Chamber| HPC| High Pressure Compressor| LPC| Low Pressure Compre ssor| d| Diffuser| noz| Nozzle| mix| Mixer| dest| Destruction Rate| 0, ambFAR| Ambient conditionFuel-Air-Ratio| CH| Chemical| PH| Physical| KN| Kinetic| PN| Potential| IP| Exergy Improvement Potential Rate (MW)| CRF| Cost Recovery Factor| c| Specific Thermoeconomic Cost (MJ/kg)| STD| Standard Temperature and Pressure| TIT| Turbine Inlet Temperature| TSFC| Thrust Specific Fuel Consumption (g/kNs)| SFC| Specific Fuel Consumption| p| Propulsive| TH|