NOTE: include a copy of your equations and equations/code with your plots 1. (50 points) A...
Fantastic news! We've Found the answer you've been seeking!
Question:
Transcribed Image Text:
NOTE: include a copy of your equations and equations/code with your plots 1. (50 points) A non-afterburning turbojet is being designed for operation at an altitude of 15 km and a Mach number of 1.8. The maximum stagnation temperature at the inlet of the turbine is 1500 K. The fuel is a jet fuel having a LHV of 43124 kJ/kg and fst is 0.06. The following efficiencies apply at this Mach number: na = 0.9 nc = 0.9 1b = 0.98 1b = 0.97 nt = 0.92 1₂ = 0.98 Use a gamma value of 1.4 up to the burner, and a value of 1.3 for the rest of the engine. Assume R is 0.287 kJ/kgK throughout the engine. Plot the specific thrust, TSFC, nth, np, and no as a function of re, the total pressure ratio across the compressor. Is there an optimum re that minimizes TSFC? Is there an optimum re that maximizes specific thrust? Consider a range of re from 2 to 60. Assume the exhaust is ideally expanded. Also plot the nozzle area ratio as a function of re. 2. (50 points) Add an afterburner to the above situation. The maximum stagnation temperature downstream of the afterburner is 2000 K. The afterburner combustion efficiency mab is 0.95 and the total pressure ratio rab is 0.97. All other efficiencies remain the same. Use a gamma value of 1.4 up to the primary burner, and a value of 1.3 for the rest of the engine. Assume R is 0.287 kJ/kgK throughout the engine. Plot the specific thrust, TSFC, nth, np, and no as a function of re, the total pressure ratio across the compressor. Consider a range of re from 2 to 60. Assume the exhaust is ideally expanded. Also plot the nozzle area ratio as a function of re. Comment on the changes that occur due to the addition of the afterburner (i.e. compare the plots to that of problem 1). Note that the overall fuel-to-air ratio can not exceed the stoichiometric value (fb+fab ≤fst). Our stagnation relations for pressure and temperature assume constant specific heats. To attain a more accurate solution, we need to use the temperature dependent specific heats and specific heat ratios tabulated in appendix II from the book. Consider air at static conditions of 300 K and 1 atm. Construct a model to compute T/T and P/P as a function of Mach number from zero to four accounting for variable specific heats (i.e. use the values in the tables for air, and construct it as lookup function in your model), and compare to the results achieved using constant specific heats (i.e. our regular stagnation relations). A reminder, the stagnation process is modeled as isentropic, adiabatic, and no work. Plots the difference as a function of Mach number in terms of the absolute value of the relative error: abs P van ablespecificheats P P P constantspecific heats constantspecificheats abs T vansblespecificheats T constantspecific heats constantspecifichents NOTE: include a copy of your equations and equations/code with your plots 1. (50 points) A non-afterburning turbojet is being designed for operation at an altitude of 15 km and a Mach number of 1.8. The maximum stagnation temperature at the inlet of the turbine is 1500 K. The fuel is a jet fuel having a LHV of 43124 kJ/kg and fst is 0.06. The following efficiencies apply at this Mach number: na = 0.9 nc = 0.9 1b = 0.98 1b = 0.97 nt = 0.92 1₂ = 0.98 Use a gamma value of 1.4 up to the burner, and a value of 1.3 for the rest of the engine. Assume R is 0.287 kJ/kgK throughout the engine. Plot the specific thrust, TSFC, nth, np, and no as a function of re, the total pressure ratio across the compressor. Is there an optimum re that minimizes TSFC? Is there an optimum re that maximizes specific thrust? Consider a range of re from 2 to 60. Assume the exhaust is ideally expanded. Also plot the nozzle area ratio as a function of re. 2. (50 points) Add an afterburner to the above situation. The maximum stagnation temperature downstream of the afterburner is 2000 K. The afterburner combustion efficiency mab is 0.95 and the total pressure ratio rab is 0.97. All other efficiencies remain the same. Use a gamma value of 1.4 up to the primary burner, and a value of 1.3 for the rest of the engine. Assume R is 0.287 kJ/kgK throughout the engine. Plot the specific thrust, TSFC, nth, np, and no as a function of re, the total pressure ratio across the compressor. Consider a range of re from 2 to 60. Assume the exhaust is ideally expanded. Also plot the nozzle area ratio as a function of re. Comment on the changes that occur due to the addition of the afterburner (i.e. compare the plots to that of problem 1). Note that the overall fuel-to-air ratio can not exceed the stoichiometric value (fb+fab ≤fst). Our stagnation relations for pressure and temperature assume constant specific heats. To attain a more accurate solution, we need to use the temperature dependent specific heats and specific heat ratios tabulated in appendix II from the book. Consider air at static conditions of 300 K and 1 atm. Construct a model to compute T/T and P/P as a function of Mach number from zero to four accounting for variable specific heats (i.e. use the values in the tables for air, and construct it as lookup function in your model), and compare to the results achieved using constant specific heats (i.e. our regular stagnation relations). A reminder, the stagnation process is modeled as isentropic, adiabatic, and no work. Plots the difference as a function of Mach number in terms of the absolute value of the relative error: abs P van ablespecificheats P P P constantspecific heats constantspecificheats abs T vansblespecificheats T constantspecific heats constantspecifichents
Expert Answer:
Answer rating: 100% (QA)
Salution A non afterburing turbojet is being designed is the nonafferbaty for 2 calculate ... View the full answer
Related Book For
Quantitative Methods for Business
ISBN: 978-0324651751
11th Edition
Authors: David Anderson, Dennis Sweeney, Thomas Williams, Jeffrey cam
Posted Date:
Students also viewed these physics questions
-
For the set of data points provided below, u 0.3 1.5 4.2 6.3 7.2 V 129.3 -50.7 27.5 3.4 70.9 a) Determine the polynomial in the Newton's form that passes through the points. b) Plot the polynomial...
-
A gas turbine cycle has two stages of compression, with an intercooler between the stages. Air enters the first stage at 100 kPa, 300 K. The pressure ratio across each compressor stage is 5 to 1, and...
-
A gas turbine cycle has two stages of compression, with an intercooler between the stages. Air enters the first stage at 100 kPa, 300 K. The pressure ratio across each compressor stage is 5 to 1, and...
-
Prepare journal entries to record each of the following sales transactions for the sales company. The company uses a perpetual inventory system and the gross method. 1. April 1st Sold for $3,000,...
-
Wilcox Electronics uses a sales journal, a purchases journal, a cash receipts journal, a cash disbursements journal, and a general journal as illustrated in this chapter. Wilcox recently completed...
-
A random point (X, Y) is distributed uniformly on the square with vertices (1, 1), (1,-1), (-1,1), and (-1,-1). That is, the joint pdf is /(x, y) = 1/4 on the square. Determine the probabilities of...
-
Due to a nationwide recession, PC Worlds merchandise inventory is gathering dust. It is now December 31, 2010, and the \($162,000\) that PC World paid for its ending inventory is \($14,000\) higher...
-
Woodland Hotels, Inc., operates four resort hotels in the heavily wooded areas of northern California. The resorts are named after the predominant trees at the resort: Pine Valley, Oak Glen, Mimosa,...
-
Sales (203,000 units at 14,210,000 70) Total variable cost 8,120,000 Contribution margin 6,090,000 Total fixed cost 4,945,500 Operating income 1,144,500 Required: (Make sure you answer each question...
-
Use the following forward and spot prices for Canadian dollars (C$) to answer the question below. The prices are in U.S. dollars ($/C$). Forward rate for 4/15/20 Spot rate delivery of Canadian...
-
Solve Bayesian estimation for this function f(x) = " a-0 X- x%a, 0 < x < 1 - a
-
Differentiate between reciprocity, redistribution, and market exchange, with examples of each.
-
Adam has the following employment-related loans from his employer: (a) A 96,000 loan at interest of 1% p.a. to enable Adam to buy his own home. (b) An interest-free season ticket loan of 10,000. (c)...
-
Discuss the rising cost of higher education.
-
Linda's income statement for the year ended 31 March 2024 is as follows: Notes: (a) Linda draws a salary of 200 per week from the business. This is included in the wages and salaries figure. (b)...
-
Analyze the differences between human language and nonhuman biological communication systems.
-
5. Consider the Atwood machine. The two masses have the values m and m. The system is released from rest with m at height h and m at height h from the floor. Use energy conservation to find the speed...
-
The graph of an equation is given. (a) Find the intercepts. (b) Indicate whether the graph is symmetric with respect to the x-axis, the y-axis, or the origin. -3 6 -6 3 x
-
Consider the following linear program: Min 2A + 2B s.t. 1A + 3B 12 3A + 1B 13 1A - 1B = 3 A, B 0 a. Show the feasible region. b. What are the extreme points of the feasible region? c. Find the...
-
Jackson Hole Manufacturing is a small manufacturer of plastic products used in the automotive and computer industries. One of its major contracts is with a large computer company and involves the...
-
In the Willow Brook National Bank waiting line system, assume that the service times for the drive-up teller follow an exponential probability distribution with a service rate of 36 customers per...
-
Justify the statement: Osmosis is of paramount importance in biological systems.
-
The freezing point of pure benzene is \(5.44^{\circ} \mathrm{C}\) and that of the solution containing \(2.092 \mathrm{~g}\) of benzaldehyde in \(100 \mathrm{~g}\) of benzene is \(4.44^{\circ}...
-
The molality of dissolved gases in water at \(0^{\circ} \mathrm{C}\) and \(1 \mathrm{~atm}\) is \(1.29 \times 10^{-3}\). The decrease in volume during melting of ice is \(0.0907 \mathrm{cc} /...
Study smarter with the SolutionInn App