Parameter thrust Thrust chamber pressure Thrust chamber temperature Working fluid Universal gas constant Ambient pressure: At Sea level value 5MN 7MPa 2800K Air At Room Temperature (Ideal Gas) 8.314 J. (Mol. K) -1 101325N/m² At an altitude of 30km 1185.5 N/m² MW= 29kg/Kw The Following Performance and operation data was obtained from a rocket with a a nozzle designed to produce maximum thrust at sea level: Determine; A) Specific Impulse B) Mass Flow Rate C) Throat Diameter D) Exit Diameter E) Thrust Produced at An altitude of 30KM for the same fixed Nozzle Geometry

Condenser 30 c „Flash Chamber Pi Evaporator OC & 50 kW For a 2-stage ammonia compression system, determine: 1. Draw the PH diagram showing the condenser, evaporator, & compressor discharge temps, intercooler pressure, all enthalpies & compressor suction specific volumes, m/kg 2. Compute the intercooler pressure in Bars & equivalent Ti in °C 3. Compressor discharge temps T: & T4 4. Mass of refrigerants m:, ms & m: in kg/sec 5. Compressor power Wi, W & total W- in kW & HP 6. Compressors PD with equal volumetric efficiency 80%; m/s 7. Condenser capacity, kW 8. Using a single stage compression, calculate & compare the power of the compressor/s in kW & HP

Q.1. A refrigeration process with interstage cooling uses refrigerant HFC-134a, and the outlet of the condenser is to be saturated liquid at 40°C. Refer to the following figure for stream numbers in your solution. The pressure of the flash chamber and the intermediate pressure between compressors is to be 290 kPa. The evaporator is to operate at -20°C and the outlet is to be saturated vapor. The flowrate of stream 1 is 23 kg/h. The flash chamber may be considered adiabatic. The compressors may be considered to be 80% efficient. a) What is the power input required to the first compressor? b) What are the flowrates of streams 6 and 7? What is the enthalpy of stream 4? Hot Side 6 5 Condenser 2nd Stage Compressor Throttle Valve 7 Flash Chamber Vapor Phase Only 1st Stage Compressor 8 Throttle Valve Evaporator 1 2 Cold Side

The following data were obtained from a performance test of a 10 x 9-cm single acting, water jacketed two-stage air compressor: Pressures: Atmospheric, 102 kPaa; leaving first-stage, 634 kPaa; leaving second-stage, 4.20 MPa. Temperatures: Atmospheric, 240C; leaving  first-stage, 1080C; entering 2nd stage, 250C; leaving 2nd stage, 1270C Compressor speed, 648 rpm Power input to motor, 5.65 kW Motor and belt efficiency, 81.5% The following are calculated from test data: Air flow rate, 0.387 ??⁄??? Compression exponents: 1st stage 1.15; 2nd Stage, 1.2 Calculate: a) Approximate indicated power b) Power for isothermal compression c) Shaft power d) 1st stage piston displacement e) Actual volumetric efficiency f) Isothermal compression efficiency g) Mechanical efficiency based on the approximate indicated power h) Over-all efficiency of the compressor

Q4//A// Prove for the condenser: + %3D Cpw (Twz-Tw1) when the temperature of cooling water outlet and inlet is equal to saturation temperature of steam and the condensate leaving the condenser respectively; also, the inlet of condenser is dry steam with unity latent heat. m, Twi

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Fuel in Combustion chamber Turbine Net Power Air in Out Axial compressor Centrifugal compressor Exhaust Figure 1 Figure 1 shows the basic gas turbine cycle. Calculate the efficiency of the system if the temperature for the condition showed in T-s diagram below. Take that mass flow rate is 23 kg/s and the Cp is 35.5 J- K-. mol. TA 8913 °C- 3 4987 °C. 4665 °C- 1276 °CH 2.

3.) An ammonia compressor operates at evaporator pressure of 316.02 kPa and a condenser pressure of 1557 kPa. A twin-cylinder compressor with bore to stroke ratio of 0.85 is to used at 1200 rpm. The actual volumetric efficiency is 92% and compression and mechanical efficiency is 78% and 80% respectively. For a cooling capacity of 25 TR, (a) the sketch the p-h diagram labeling the evaporating and condensing temperature and pressures (b) define the all properties of ammonia taken from saturation table. Determine (c) the quantity of cooling water in the condenser in kg/min if the increase in temperature is 8°C, (d) the bore and stroke expressed in cm and (e) the size of the driving motor in hp. Given: h2 = h at 1557 kPa and s2 = s1 1695 kJ/kg

You have been asked to help with the low-pressure compressor (LPC) design for a turbofan engine with a bypass ratio of 8.4. The preliminary cycle design calls for the LPC to produce a pressure ratio of 9.4 with the following operating conditions and constraints. .Inlet Conditions TO2 Poz Core Air Mass Flowrate (kg/s) (K) (kPa) 282 24.6 47.0 Design Constraints Maximum Polytropic Efficiency 94.1% Maximum Stage Pr 1.55 Estimate the minimum number of stages required for this LPC. Then assuming the 1st stage of the LPC operates at the maximum allowable pressure ratio, determine the stagnation temperature exiting the 1st stage, and the stage's adiabatic efficiency. Also determine the power (W) required to operate the full LPC (not just 1st stage). Finally, what would be the percent change in the required power if the polytropic efficiency was only 90.0%.

Question 3.) An engine has an inlet stagnation condition of 300 bar and 4000 kelvin. Methane and liquid oxygen make up the products of combustion and have a specific heat ratio k = 1.14 and a gas constant R = 383 J / kg-k. The nozzle has an exit to throat area ratio of Ae / Ath = 34.34 and has an exit diameter of 1.3 meters. Calculate the following: (d) For launch at sea level Pb = 101.325 kilopascals, is the nozzle over, under, or perfectly expanded? (e) Is the nozzle flow choked? (f) Exit temperature