The driver and driven gases of a pressure-driven shock tube are both air at 300 K. If the diaphragm pressure ratio is p4/p1 = 5, calculate: a. Strength of the incident shock (P2/P1) b. Strength of tbe reflected sbock (ps/P2) c. Strength of the incident expansion wave (p/p.)

6. In a certain axial-flow turbine stage, the axial velocity cx is constant. The absolute velocities entering and leaving the stage are in the axial direction. If the flow coefficient c/U is 0.6 and the gas leaves the stator blades at 68.2° from the axial direction, calculate a. the stage loading factor, AW/U²; b. the flow angles relative to the rotor blades; c. the degree of reaction; d. the total-to-total and total-to-static efficiencies. The Soderberg loss correlation, Eq. (3.46), should be used.

The quantity of air in a 900 mm diam duct is 15 m/s, the duct resistance is 7.1 Ns/m® and the air density is 1.20 kg/m³. The duct diameter increases to 1400 mm with a shock loss factor of 0.5. What is the end pressure (Pa gauge) with respect to the start. a 45 m'ls passes through a regulator. Using normal values for coefficient of discharge what open area is required for a pressure differential of 450 Pa ?

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Q40 The venturi of a simple carburettor has a throat diameter of 35 mm and aid the coefficient of air flow is 0.85. The fuel orifice has a diameter of 2.3 mm and the coefficient of fuel flow is 0.66. The petrol surface is 5mm below the throat Find The air Fuel ratio for a pressure drop of 0.07 bar when nozzle lip is neglected. ⑥The air Fuel ratio when the nozzle lip is taken into account win wilt to tout The minimum velocity of air (critical air velocity) required to start The fuelut size flow when nozzle lip is provided. [used Approximate method Just Take density of air and fuel as 1.2 and 750 kg/m³ respectively) Enter APS Answers [a_11.93 b-11-96 c_7.83 m/sec ] 2-1 1920

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

Q88 Atest carried out on a single cylinder, twa-stroke oil engine gave the following datag Cylinder bore =200 mm, stroke 250 mm, engine speed-300 rpm, net brake torque 500N.m indicated mean effective Pressure =4.9×10°N/m2,fuel consumption = 5kg/min, Cooling water rate of flow - o0666 kg/sec, temperature rise of cooling water=55k, specific heat capacity of water =4.1868 Kilkg-k. Calculate:@the mechanical efficiency O the specific fuel consumption, and © draw up an energy balance in kw. Answers EO 81.6,60.318 kg/kw.hr,©Qtotal -61a1Kw , n Qb.p=15.7Kwg@cooling water= 15.35 kw ,QExhaust= 30.05 kw]

Hom Work عماد داود عبود (35) Q1: The Fiat car has a four strok engine of 1089 C.C capacity -It develops maximum power 32kw at 5000 r-p.m. The volumetric efficiency at this speed is 75% and the air-fuel ratio 13:1, At peak power the theoretical air speed at the choke is 120 m/sec. The coefficient of discharge for the venturi is 0.85 and that of the main petrol jet is 0.66. An allowance should be made for the emulsion tube, the diameter of which can be taken as (1/2.5) of the choke diameter. the Petrol surface is 6 mm blow the choke at this engine condition. Calculate the size of a suitable chake (D) and main jet (d).The specific gravity of petrol is 0.75 and the atmospheric pressure 1.03 bar and temperature 27°c. [D=23.2mm,d=1.296mm]

5.16.| For a centrifugal compressor rotating at 2500 rpm, find the compression ratio for the following specifications. T = 300 K; nst (volumetric flow rate) = 1.25 m/s and t (the thickness of the flow section at the = 0.85; r, = 0.55; ra = 0.015; B, 60°, exit) =0.15 m.