MONTANA STATE UNIVERSITY DEPARTMENT OF MECHANICAL ENGINEERING EMEC 426 Thermodynamics of Propulsion Systems Spring 2017 Instructor: Dr. Alan H. George Office: Roberts 119 Office Hours: to be announced Format: 3 credit lecture Prerequisites: EMEC 425 Advanced Thermal Systems; or as listed in the current MSU Catalog. Current regulations require that a grade of "C-" or better must be earned in all prerequisite courses. Lecture Periods and Room(s): M W F 08:00-08:50, Roberts Hall 319. Textbook: Philip, H., and Peterson, C., Mechanics and Thermodynamics of Propulsion, second edition, Prentice Hall (formerly by Addison-Wesley Publishing), 1992. Grading Basis: Graded Homework 80% Final Project 20% total 100% Grade intervals are expected to be near the traditional values of 60% minimum for D-, 70% minimum for C-, 80% minimum for B-, and 90% minimum for A. Students who consistently arrive late at class meetings or disrupt normal course activities will have their grades reduced. Chronic complaining about the course content, instructional methods, or course personnel will also be cause for grade reduction. Course Objectives and General Information: The course was created to provide an introduction to computer-aided thermodynamics calculations with applications to the mechanics and thermodynamics of propulsion systems. The objective of the course is to extend previous training in thermodynamics and fluid mechanics. The course depends significantly on the material covered in the EMEC 425 Advanced Thermal Systems course and review of that material is a student responsibility. Specifically, the student should be able to apply the following formulations form the EMEC 425 course: interpretation of thermochemical data such as NIST- JANAF thermochemical tables or similar data sources, chemical equilibrium composition of an ideal gas mixture, thermodynamic properties of the ideal gas mixture, and compressible flow of the calorically perfect gas including adiabatic flow, isentropic flow, normal shock waves, and quasi-one-dimensional flow. Subjects of this course are expected to include additional topics in the mechanics and thermodynamics of compressible fluid flow, accurate calculation of the products of combustion using chemical equilibrium theory and suitable computer codes, with application to turbojet engines, turbofan engines, ramjet engines, and rocket engines. Since air-breathing engines of the types mentioned contain inlets that slow and compress the air, analysis of inlets will also be considered. Several numerical formulations which require a computerized solution, e.g., Mathcad, will be developed.
Therefore, proficiency with Mathcad or some alternative code, e.g., Matlab, is expected and required. An introduction to commercial computer codes, e.g., on-line calculators for compressible flow calculations, GASEQ for computing the equilibrium composition and properties of mixtures, Chemical Equilibrium with Applications (CEA) by NASA for computing the equilibrium composition and properties of mixtures, and Rocket Propulsion Analysis (RPA) will be provided. Supplemental instruction is also available from the MSU Office of Student Success SmartyCats Tutoring [contact (406)-994-7627, smartycats@montana.edu, or go to SUB 177]. This supplemental instruction can be particularly helpful to review topics in the prerequisite courses. Students with learning disabilities or other special academic needs should contact the instructor if they require any special provisions for assignments. In addition, regulations regarding academic integrity and other student conduct may be found on the MSU Webpage, e.g., http://www2.montana.edu/policy/student_conduct/cg600.html. Due to current University policies, the following student learning outcomes are provided: 1. Use and interpret results from common thermochemical data bases such as NIST-JANAF Thermochemical Tables and NASA Thermo-Build. 2. Use and interpret results from commercial chemical equilibrium applications codes, e.g., GASEQ and NASA-CEA. 3. Use and interpret results from commercial code(s) for rocket engine analysis, e.g., Rocket Propulsion Analysis (RPA). 4. Use and interpret results from compressible flow calculators. 5. Analyze both internal and external compressible flows using combinations of manual calculations and compressible flow calculators. 6. Analyze chemical rocket engine performance using the above-mentioned computer codes and student written Mathcad or MATLAB code. 7. Analyze all stages of common air-breathing propulsion systems such as ramjets and turbojets using the above-mentioned computer codes and student written Mathcad or Matlab code.
EMEC 426 Spring 2017 Dr. George Since the course is being offered for the second time, updates to the list of assignments will be made as needed in class material and on the course D2L page. The course does not use D2L-based e-mail or the D2L-based grade book for any purpose. Tentative Topics, Reading, and Homework Assignments. See the course in class material and D2L page for current information. Week of Reading/Problems 09 Jan Additional compressible flow solutions. Oblique shock waves. Notes. Review text Chapter 3 sections 3.1, 3.2, 3.3, and 3.7. Except for differences in notation, this is the same compressible flow material as covered in EMEC 425. Homework 1 Solve Problem 3.1 using isentropic flow equations not isentropic flow tables. To the extent possible, use an on-line compressible flow calculator (see the course D2L page) to check your answers. Due date as specified on handout. 16 Jan Additional compressible flow solutions. Prandtl-Meyer expansion flow, sonic flow area in quasi-one-dimensional flow after a normal shock wave, and supersonic conical flow. Notes. Homework 2. Handout. Prandtl-Meyer flow and oblique shock waves. Due date as specified on handout. 23 Jan Computer codes: on-line compressible flow calculators (limited to calorically perfect gas flow, including isentropic flow, quasi-one-dimensional flow, normal shock waves, oblique shock waves, Prandtl-Meyer expansion flow, and supersonic conical flow). The two-dimensional supersonic airfoil; calculation of lift and drag for various angles of attack by shock-expansion theory. Lift and drag coefficients. Notes. Homework 3. Handout. Two-dimensional Supersonic Airfoil Calculating Lift and Drag Coefficients for Various Angles of Attack (On-line compressible flow calculators possibly combined with Excel or Mathcad code). Conical shock pressure coefficient for several cone angles and/or upstream Mach numbers. Due date as specified on handout.
30 Jan Chemical equilibrium composition of the ideal gas mixture. Review of the formulation. Solution by direct numerical minimization of the Gibbs free energy subject to constraints based on conservation of atomic chemical species. Review text Chapter 2. Except for differences in notation, this is the same material concerning basic equations of fluid motion, ideal gas properties, thermodynamic analysis of chemical reactions (combustion), and the chemical equilibrium formulation for ideal gas mixtures as covered in EMEC 425. Computer codes: on-line compressible flow calculators (limited to calorically perfect gas flow, including isentropic flow, normal shock waves, oblique shock waves, supersonic conical flow, and Prandtl-Meyer expansion flow), chemical equilibrium with applications (GASEQ, NASA-CEA), Thermo-Build (computeraided thermochemical tables), NIST-JANAF Thermochemical Tables (hardcopy and on-line versions), and Computer-Aided Thermodynamic Tables 3. Various examples. How to operate the codes. Homework 4. Handout. GASEQ, individual basis, each student gets a problem with a different set of parameters, an exercise in computer-aided thermodynamics, compressible flow, and chemical equilibrium applications. Probably a study of adiabatic flame temperature both in steady flow and closed volume. Steady flow heat transfer or work rate. Reversible adiabatic expansion and compression. Due date as specified on handout. 06 Feb Computer codes: compressible flow calculators (limited to calorically perfect gas flow, including isentropic flow, normal shock waves, oblique shock waves, supersonic conical flow, and Prandtl-Meyer expansion flow), chemical equilibrium with applications (GASEQ, NASA-CEA), Thermo-Build (computer-aided thermochemical tables), NIST-JANAF Thermochemical Tables (hardcopy and online versions), and Computer-Aided Thermodynamic Tables 3. Various examples. How to operate the codes. Continued. Equilibrium with liquid and solid condensed phases. Temperature change due to adiabatic throttling (Joule-Thomson coefficient). Homework 5. Handout. Torpedo propulsion WWII-type wet-heater system. Compressed air compared to air/fuel compared to air/fuel/water compared to oxygen/fuel/water. Use of seawater (Japan Type 93) compared to on-board water (USA Mark 14). Use NASA-CEA. Compare propulsion systems based on flow availability per unit on-board propellants. Students assigned different fuels to evaluate. Due date as specified on handout.
13 Feb Computer codes: compressible flow calculators (limited to calorically perfect gas flow, including isentropic flow, normal shock waves, oblique shock waves, supersonic conical flow, and Prandtl-Meyer expansion flow), chemical equilibrium with applications (GASEQ, NASA-CEA), Thermo-Build (computer-aided thermochemical tables), NIST-JANAF Thermochemical Tables (hardcopy and online versions), and Computer-Aided Thermodynamic Tables 3. Various examples. How to operate the codes. Continued. Homework 6. Handout. NASA-CEA Probably a study of adiabatic flame temperature for steady flow, closed volume combustion, normal shock waves with chemical reaction, one-dimensional detonation, isentropic adiabatic expansion and compression. Due date as specified on handout. 20 Feb Rocket engine thrust, specific impulse, thrust coefficient, characteristic velocity, and other performance characteristics. Mixture ratio. Characteristic length of combustion chamber L*. Optimal propellants; adiabatic flame temperature, molecular mass of products, specific impulse, density, etc. Analysis using the NASA-CEA code. 27 Feb Rocket engine, analysis based on calorically perfect gas properties based on conditions in the combustion chamber. Mixture ratio. Characteristic length of combustion chamber L*. Optimal propellants; adiabatic flame temperature, molecular mass of products, specific impulse, density, etc. Analysis using the NASA-CEA code. 06 Mar Rocket engine, analysis based on equilibrium flow properties and frozen chemical composition flow properties. [Coverage limited to chemical rockets with gaseous or liquid fuels and oxidizers only; no solid propellants.]. The influence of finite combustion chamber flow area. Analysis using the NASA-CEA code., computer-aided parametric analysis of rocket engine performance; each student gets a problem with a different combination of fuel, oxidizer, and specified range of operating conditions. 13 Mar Spring Break
20 Mar Rocket engine, analysis based on equilibrium flow properties and frozen chemical composition flow properties. [Coverage limited to chemical rockets with gaseous or liquid fuels and oxidizers only; no solid propellants.]. Nozzle design by method of characteristics. The influence of finite combustion chamber flow area. Analysis using the Rocket Propulsion Analysis (RPA) code., computer-aided parametric analysis of rocket engine performance including specification of the nozzle geometry. Each student gets a problem with a different combination of fuel, oxidizer, and specified range of operating conditions. 27 Mar Performance of rocket vehicles. The Rocket Equation and delta-v. Relationships between vehicle mass, propellant mass, engine thrust, burn time, vehicle acceleration, vehicle velocity, and range or altitude achieved. Portions of text Chapter 10. The mechanics of propulsion, thrust, drag, the steady flow momentum equation, and measures of propulsion efficiency. The Breguet Range Equation for level flight. Analysis of common propulsion system elements: inlets, combustion systems (limited coverage), turbines, compressors, and nozzles Portions of text Chapters 5 and 6. 03 Apr Analysis of common propulsion system elements: inlets, combustion systems (limited coverage), turbines, compressors, and nozzles. Continued. Air-Breathing Engines. Ramjet engine. Portions of text Chapters 5 and 6.
10 Apr Air-Breathing Engines. Turbojet engine with afterburner. (Last day to withdraw from the course: Friday, 13 April) Portions of text Chapter 5. 17 Apr Air-Breathing Engines. Turbofan engine. Portions of text Chapter 5. 24 Apr Introduction to the design and operation of subsonic inlets and supersonic inlets. Mention of other applications of thermodynamics, compressible flow, and chemical equilibrium, as related to propulsion systems. 01 May Final Project (due date to be provided).