A static thrust stand as sketched in the figure shown is used for testing a jet engine. The following conditions are known for a typical test: the fuel enters at a flow rate of 5 kg/swith approximate zero velocity. Intake air velocity is 215 m/s and exhaust gas velocity is 500 m/s; intake cross-sectional area is 1.2 m^2; intake static gauge pressure -30 kPa;intake air density is 0.9 kg/m^3 and exhaust static temperature 800 K; exhaust static pressure 0 kPa. If the atmospheric pressure is 100 kPa, the constant for air and gas is R= 287/(kg. K). The exhaust area in m^2 is:Control volumeFuel inletSelect one:Patrma. 1.04b. 1.09P1U2c. 1.07Section (2)Section (1) A static thrust stand as sketched in the figure shown is used for testing a jet engine. The following conditions are known for a typical test: the fuel enters at a flow rate of 5 kg/swith approximate zero velocity. Intake air velocity is 215 m/s and exhaust gas velocity is 500 m/s; intake cross-sectional area is 1.2 m^2; intake static gauge pressure -30 kPa;intake air density is 0.9 kg/m^3 and exhaust static temperature 800 K; exhaust static pressure 0 kPa. If the atmospheric pressure is 100 kPa, the constant for air and gas is R= 287J/(kg. K). The inlet mass flow rate in kg/s is:Control volumeFuel inletSelect one:Patma. 227.20b. 232.20P1U2c. 237.20Section (2)Section (1)

Answered: Image /qna-images/answer/8d3552ea-1e30-49b2-a4d6-a51595be58bb.jpg

A Static thrust stand as with approximate zero velocity. Intake air velocity is 215 m/s and exhaust gas velocity is 500 m/s; intake cross-sectional area is 1.2 m^2; intake static gauge pressure -30 kPa; ntake air density is 0.9 kg/m^3 and exhaust static temperature 800 K; exhaust static pressure 0 kPa. If the atmospheric pressure is 100 kPa, the constant for air and gas is R= 287 /(kg. K). The exhaust area in m^2 is: ched in the figure showwn is used ting a jet engine. The following conditions are khown for a typical test: the fuel enters at a fiow rate or 5 kg/s Control volume Fuel inlet- Select one: Patm а. 1.04 b. 1.09 P1 U2 c. 1.07 Section (2) Section (1)

A Static thrust stand as with approximate zero velocity. Intake air velocity is 215 m/s and exhaust gas velocity is 500 m/s; intake cross-sectional area is 1.2 m^2; intake static gauge pressure -30 kPa; ntake air density is 0.9 kg/m^3 and exhaust static temperature 800 K; exhaust static pressure 0 kPa. If the atmospheric pressure is 100 kPa, the constant for air and gas is R= 287 /(kg. K). The exhaust area in m^2 is: ched in the figure showwn is used ting a jet engine. The following conditions are khown for a typical test: the fuel enters at a fiow rate or 5 kg/s Control volume Fuel inlet- Select one: Patm а. 1.04 b. 1.09 P1 U2 c. 1.07 Section (2) Section (1)

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

A static thrust stand as sketched in the figure shown is used for testing a jet engine. The following conditions are known for a typical test: the fuel enters at a flow rate of 5 kg/s with approximate zero velocity. Intake air velocity is 215 m/s and exhaust gas velocity is 500 m/s; intake cross-sectional area is 1.2 m^2; intake static gauge pressure -30 kPa; intake air density is 0.9 kg/m^3 and exhaust static temperature 800 K; exhaust static pressure 0 kPa. If the atmospheric pressure is 100 kPa, the constant for air and gas is R= 287 J/(kg. K). The exhaust gas density in kg/m^3 is: Control volume Fuel inlet- Select one: Patm a. 0.44 b. 0.84 P1 c. 1.00 Section (2) Section (1)
A static thrust stand as sketched in the figure shown is used for testing a jet engine. The following conditions are known for a typical test: the fuel enters at a flow rate of 5 kg/s with approximate zero velocity. Intake air velocity is 215 m/s and exhaust gas velocity is 500 m/s; intake cross-sectional area is 1.2 m^2; intake static gauge pressure -30 kPa; intake air density is 0.9 kg/m^3 and exhaust static temperature 800 K; exhaust static pressure 0 kPa. If the atmospheric pressure is 100 kPa, the constant for air and gas is R= 287 J/(kg. K). The exhaust area in m^2 is: Control volume Fuel inlet Select one: Patr a. 1.07 P2 U2 P1 O b. 1.09 c. 1.04 Section (2) Section (1)
A static thrust stand as sketched in the figure shown is used for testing a jet engine. The following conditions are known for a typical test: the fuel enters at a flow rate of 5 kg/s with approximate zero velocity. Intake air velocity is 215 m/s and exhaust gas velocity is 500 m/s; intake cross-sectional area is 1.2 m^2; intake static gauge pressure -30 kPa; intake air density is 0.9 kg/m^3 and exhaust static temperature 800 K; exhaust static pressure 0 kPa. If the atmospheric pressure is 100 kPa, the constant for air and gas is R= 287 J/(kg. K). The inlet air temperature in K is: Control volume Fuel inlet - Select one: a. 300.00 b. 271.00 P1 C. 251.00 Section (2) Section (1)
A static thrust stand as sketched in the figure shown is used for testing a jet engine. The following conditions are known for a typical test: the fuel enters at a flow rate of 5 kg/s with approximate zero velocity. Intake air velocity is 215 m/s and exhaust gas velocity is 500 m/s; intake cross-sectional area is 1.2 m^2; intake static gauge pressure -30 kPa; intake air density is 0.9 kg/m^3 and exhaust static temperature 800 K; exhaust static pressure 0 kPa. If the atmospheric pressure is 100 kPa, the constant for air and gas is R= 287 J(kg. K). The inlet air temperature in K is: Control volume Fuel inlet Section (2) Section (1)
CTQ2 Assuming the clearance is negligible for a single stage compressor with the following data. Atmospheric pressure: 90 kPa Atmospheric temperature: 17 °C Delivery pressure: 7 bar Free air delivery flow rate: 0.2 m/min Take "n" as 1.3, Cp = 1.005 kJ/kg K, Cv = 0.718 kJ/kg K Answer the questions for ethuto test What is the delivery temperature of air for an isentropic compression process in Kelvin to 1 decimal place?
9 A full load test on a two-stroke engine yielded the following results: speed 440 rpm; brake load 50 kg; imep 3 bar; fuel consumption 5.4 kg/h; rise in jacket water temperature 36 °C; jacket water flow 440 kg/h; air-fuel ratio by mass 30; temperature of exhaust gas 350 °C; temperature of the test room 17 °C; baromet ric pressure 76 cm of Hg: cylinder diameter 22 cm; stroke 25 cm: brake diameter 1.2 m; calorific value of fuel is 43 M.J/kg; proportion of hydrogen by mass in the fuel 15%: R 0.287 k.J/kg of mean specific heat of dry exhaust gases 1 kJ /kg K; specific heat of dry steam 2 kJ/kg K. Assume enthalpy of super heated steam to be 3180 k.J/kg. Determine. (i) the indicated thermal efficiency (ii) the specific fuel consumption in g/kW h (iii) volumetric efficiency based on atmospheric conditions Draw up a heat balance for the test on the percentage basis indicating the balance. the content of cach item
B) The air flow to a four cylinder four-stroke engine is 2.15 m³/min. During a test on the engine the following data were recorded: Bore 10.5cm; stroke 12.5cm; engine speed 1200 rpm, torque 150 N.m, fuel consumption 5.5 kg/hr, calorific value of fuel, 43124 kJ/kg, ambient temperature 1-The brake thermal efficiency. and pressure are 20°C and 1.03 barş. Calculate: 2-The brakes mean effective pressure. 3-The volumetric efficiency.
4. The following data were obtained during a test on a diesel engine operating at 2800 rev/min: =132 Nm Dynamometer torque measurement Fuel consumption Intake air flow rate =12 kg/h =168 kg/h Calorific value of fuel =44 400 kJ/kg Engine cooling water flow rate =15.4 kg/min =48°C Engine cooling water temperature rise =8.7 kg/min Exhaust calorimeter cooling water flow rate Exhaust calorimeter cooling water temperature rise Exhaust gas temperature at exit from calorimeter =64°C = 85°C Specific heat of exhaust gas =1.1 kJ/kgK laboratory air temperature = 25°C Draw up percentage-based energy balance for the engine using the laboratory temperature as the datum.
1 The following observations are recorded during a test on a four-stroke petro engine, F.C = 25cc of fuel in 10 sec, speed of the engine is 2600 rpm, B.P = 22 kW, Qair 0.00134 m, piston diameter 90 mm, density of the fuel = 0.85gm/cc , compression ratio = 7.5, CV of fuel = 42000KJ/Kg, room temperature = 24 °C %3D = 140mm, stroke length = %3D %3D %3D 2 A six-cylinder 4-stroke cycle petrol engine is to be designed to develop 250 kW of (b.p) at 2200 rpm the stroke / bore ratio is to be 1.3:1. Assuming nm =80% and an indicated mean effective pressure of 9.5 bar, determine the required bore and stroke. If the compression ratio of the engine is to be 7.5 to 1, determine consumption of petrol in kg/h and in kg/bp.hr. Take the ratio of the indicated thermal efficiency of the engine to that of the constant volume air standard cycle as 0.65 and the calorific value of the petrol as; 44770KJ/kg.
The following data relate to a performance test of a single acting reciprocating air compressor. Bore = 14 cm Stroke = 10 cm Suction pressure = 1.3 bar Suction temperature = 32°C Discharge pressure = 6 bar Discharge temperature = 180°C Speed of the compressor = 1200 rpm Shaft power = 6.25 kW Mass of air delivered = 1.7 kg/min Polytropic index = 1.25 Calculate the following: (i) Volumetric efficiency (ii) Indicated power (iii) Mechanical efficiency
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.
Q1. During a test on a two stroke diesel engine on full load the following observations were recorded: Speed= 350 rpm Net brake load= 590 N Mean effective pressure= 2.8 bar Fuel consumption=4.3 kg/h Jacket cooling water= 500 kg/h Temperature of jacket water at inlet and outlet= 25°C and 509C respectively Air used per kg of fuel= 33kg Temperature of air in test room= 25°C Temperature of exhaust gases= 400°C Cylinder diameter= 220 mm Stroke length= 280 mm Effective brake diameter= 1 m Calorific value= 43900 KI/kg Proportion of hydrogen in fuel= 15% Mean specific heat of dry exhaust gases= 1.0 KI/kg K Specific heat of steam= 2.09 KJ/kg K Calculate: (1) indicated power (2) brake power (3) draw up heat balance sheet on minute basis.