Consider the generic model of the inflight and stationary turbojet. T -D=mV, where T = Vev(ṁ¡+rṁf) - Viw(ṁ;) + (Pe-P;)A. m¡ = P;VivA ¡ Viv = V¡ + Vv a) Suppose vehicle flight condition is steady (V, = 0), inlet conditions are approximated by the vehicle moving through calm unaltered free stream air (V, = 0), and fuel mass flow rate is negligible compared to the inlet mass flow rate (ṁf << ṁ¡). Derive the algebraic equation (2nd order polynomial equation) governing the vehicle speed. b) For the indicated numeric data, compute the vehicle speed where r = r; = re denotes radius of cylindrical engine shape and is equal at the inlet and exit planes. S = 300 ft² , r= 25 in , Cp= 0.04 %3D P; = 6.75 lbf/in?, ², Vely = 1000 ft/s Pe = 6.95 lbf/in Pi = 0.001266 slug/ft*

Consider the generic model of the inflight and stationary turbojet. T -D=mV, where T = Vev(ṁ¡+rṁf) - Viw(ṁ;) + (Pe-P;)A. m¡ = P;VivA ¡ Viv = V¡ + Vv a) Suppose vehicle flight condition is steady (V, = 0), inlet conditions are approximated by the vehicle moving through calm unaltered free stream air (V, = 0), and fuel mass flow rate is negligible compared to the inlet mass flow rate (ṁf << ṁ¡). Derive the algebraic equation (2nd order polynomial equation) governing the vehicle speed. b) For the indicated numeric data, compute the vehicle speed where r = r; = re denotes radius of cylindrical engine shape and is equal at the inlet and exit planes. S = 300 ft² , r= 25 in , Cp= 0.04 %3D P; = 6.75 lbf/in?, ², Vely = 1000 ft/s Pe = 6.95 lbf/in Pi = 0.001266 slug/ft*

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Similar questions

3. A 4-stroke, 8-cylinder, petrol engine, has the following parameters at sea level; fue consumption = 0.75 Itr/min, engine speed = 50 r.p.s., Ap = 60 mm Hg, venturi diameter = 4 cm, atmospheric pressure = 1.03 kg/cm', C, 0.8, air and fuel densities are 1.15 kg/m' and 700 kg/m' respectively. Calculate: AF when the temperature decreases by 10%.
Part (a) Find the efficiency of an ideal engine operating between these reservoirs. Remember the efficiency is unit-less, therefore so should your number be as well. ( Party a was incorrect can you try again ) Part (d) What if the actual work done (more realistically) is W = 290 J during a single cycle; what is the efficiency of this engine if the energy input is the same (again, the number should be unit-less)? Part (e) What is equation for the new power output per cycle (in Watts) of this new (and more realistic) engine?
Uz な、以う0 Vrz VF = Vz Ure Maxe Dr. Ayser Muneer Turbomachines Example (5-2) An inward flow reaction turbine is supplied with water at a rate of (600 Vsec) with a 3 velocity of flow of (2 m/sec). the velocity of periphery and velocity of whirl at inlet are 24 m/sec and 18 m/sec respectively. Assuming radial discharge at outlet and the velocity of flow to be constant, find; 1- Vane angle at inlet, and 2- Head of water on the wheel. V Solution Vn Q = 0.6 m/sec, Vn=2m/sec, uj=24 m/sec, Vu=18m/sec, V1=Vr2 m/sec
The following data relate to a compound impulse turbine having two rows of moving blades and one row of fixed blades in between them. Steam velocity coming out of nozzle= 450 m/sec., Nozzle angle %3D 15°, Moving blades tip discharge angles %3D 30°, Fixed blade discharge angle = 20°, 6. Friction loss in each blade rows = 10% of %3D the relative velocity. Find the blade velocity, blade efficiency and specific steam consumption for turbine.
Where necessary, assume air as an ideal gas and consider R = 287J/(kg.K), Cp = 1005 J/(kg.K), Cv = 718 J/(kg.K). a) A nozzle is a device that is used to increase the velocity of a fluidby varying the cross-sectional area. At the last section of a jetengine, air with a mass flow rate of 50 kg/s ata pressure of 500 kPa and a temperature of 600 K enters a nozzlewith an inlet cross-sectional area of 5m2. The exit area of thenozzle is 20% of its inlet area. The air leaves the nozzle at avelocity of 300 m/s. The nozzle is not well-insulated and duringthis process, 5 kJ/kg heat is lost. (i) In analysing this nozzle using the 1st law of thermodynamics,the change in which type of energy is negligible? (ii) Determine the density and velocity of the air entering thenozzle.(iii) Calculate the density of the air as it leaves the nozzle.(iv) Determine the temperature of the air as it leaves the nozzle.(v) Calculate the pressure of the air as it leaves the nozzle.
Q4// Answer two of the following: A// Compare briefly between the centrifugal and axial compressors. B// Explain the difference between the intensity and efficiency of combustion. C// Mention in summery the principal components of a nuclear reactor,
‘The following particulars refer to a two-row velocity-compounded impulse wheel which forms the first stage of a combination turbine: ‘Steam velocity at nozzle outlet 1630 mis Mean blade velocity 1125 mls Nozzle angle 1160 Outlet angle, first row of moving blades 18° Outlet angle, fixed guide blades oy Outlet angle, second row of moving blades 36° Steam flow rate 126kgs ‘The ratio of the relative velocity at outlet to that at inlet is 0.84 for all the blade. Determine (a) The velocity of whirl. (b) The tangential thrust on the blades. (c) The axial thrust on the blades. (d) The power developed. (e) The blading efficiency.
/ The following particulars refer to a two-row velocity-compounded impulse wheel which forms the first stage of a combination turbine: Steam velocity at nozzle outlet 1630 mis Mean blade velocity 1125 mls Nozzle angle :16° Outlet angle, first row of moving blades 18 Outlet angle, fixed guide blades inr Outlet angle, second row of moving blades :36° Steam flow rate 126kgs “The ratio of the relative velocity at outlet to that at inlet is 0.84 for all the blade. Determine @) The velocity of whirl.
A diatomic gas engine contracts isothermally from V2 = 2.00 m³ and p2 = 172 kPa to a volume V₁ and pressure 574 kPa. The engine then follows an isobaric process to V2, then an isochoric process to the original pressure, p2. Calculate the engine's efficiency. [Hint: Start by drawing the engine cycle on a pV-diagram.] .1152
Steam enters a control yolume that has one inlet and two exits. At the inlet (location 1) with a diámeterof 5.2 cm, the Steam has 100 bar , 360°C , and as mass flow rate of a Rg/sec. Through one exit (location 2), 15.% of the incoming mass flow rate Teaves the Control volume and the remainder leaves through the otner exit (locatión 3). For steady state opeaton, calculake the mass flow rate at locatlon 3 in kg/sec using 5 Signifigant figiures. रप्री द
‘The following particulars refer to a two-row velocity-compounded impulse wheel which forms the frst stage of a combination turbine: Steam velocity at nozzle outlet :630 mis Mean blade velocity 125 mls Nozzle angle :16° Outlet angle, first row of moving blades 18 Outlet angle, fixed guide blades 1220 Outlet angle, second row of moving blades :36° Steam flow rate 26kgs ‘The ratio of the relative velocity at outlet to that at inlet is 0.84 for all the blade. Determine ) The velocity of whirl. (b) The tangential thrust on the blades.
‘The following particulars refer to a two-row velocity-compounded impulse wheel which forms the frst stage of a combination turbine: Steam velocity at nozzle outlet :630 mis Mean blade velocity 125 mls Nozzle angle :16° Outlet angle, first row of moving blades 18 Outlet angle, fixed guide blades 1220 Outlet angle, second row of moving blades :36° Steam flow rate 26kgs ‘The ratio of the relative velocity at outlet to that at inlet is 0.84 for all the blade. Determine ) The velocity of whirl. () The tangentia thrust on the blades () The axial thrust on the blades. (@) The power developed. (e) The blading efficiency.