b] Steam enters a nozzle passing a mass flow of14 kg/s at a pressure of 30 bar and atemperature of 300°C. After expansion to a exitpressure of 5 bar, the exit velocity was 800 m/s.(i) Determine the nozzle efficiency and the exitarea (ii) If the losses occur only in the divergentportion, determine the velocity of steam at thethroat.

Answered: Image /qna-images/answer/e70b8b28-4b0d-4f7c-af8a-9f166aa2b3cd.jpg

Answered: b] Steam enters a nozzle passing a mass…

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

At a particular stage of a reaction turbine the mean blade speed is 140 m/sec and the steam is at a pressure of 20 bar with temperature of 250° C. Fixed and moving blades at this stage have inlet angles 30° and exit angles 20°. The stage efficiency is 80%. Determine (1) Specific entholpy drop across the stage in kJ/kg. (i) Drum Dia and blade height if heigh is one-twelfth of the drum dia. and the steam flow is 120 kg/sec. (ii) The percentage increase in the relative velocity across the bladings as a result of pressure drop across the blading.
Steam flows through a turbine at the rate of 100 lb/min with ∆KE = 0 and Q = 0. At entry, its pressure is 175 psia, its volume is 3.16 ft3/lb, and its internal energy is 1166.7 Btu/lb. At exit, its pressure is 0.813 psia, its volume is 328 ft3/lb, and its internal energy is 854.6 Btu/lb. What horsepower is developed? (b) The same as (a) except that the heat loss from the turbine is 10 Btu/lb of steam.
Q1/1In a single-stage axial flow gas turbine of A319 Airbus Airplane has an axial velocity is equal to 250 m/s, and assume equal inlet and outlet velocities. Stage exit swirl angle is 9° , mass flow rate of gas is 15 kg/s, and nozzle efflux angle is 63°. Assume that blade speed is 350 m/s, gas enters at stagnation pressure of 5 bar, and stagnation temperature of 1980 °R. Also, assume y = 1.33, and C,,=1.147 kJ/kg. K. Determine the rotor blade gas angles, output power, blade-loading coefficient, and degree of reaction.
-The throat area of a c-d nozzle is 10 cm^2 and its exit is 20 cm^2. If the stagnation pressure is 1 bar, what is the exit pressure (Pe) range needed to chock the throat? choese 1-greater or equal 0.0935 bar and less or equal 0.937 bar 2-less or equal 0.937 bar 3- greater or equal 0.937 bar and less or equal 1 bar 4- greater or equal 0.935 bar
A turbine is driven by a system that enters the turbine at the ff. conditions: 500 kg/h, 44 atm, 450 deg C, 60 m/s linear speed. The steam exits at a point five meters below the inlet stream of the turbine with the following conditions: atmospheric pressure, 360 m/s speed. 70,000 W of shaft work is delivered by the turbine while 104 kilocalories/h heat is lost. Why is expansion work 0 and why cannot the flow work be calculated?
Each stage of an axial flow compressor is of 0.5 reaction, has the same mean blade speed and the same flow outlet angle of 30 degree relative to the blades. The mean flow coefficient is constant for all stages at 0.5. At entry to the first stage the stagnation temperature is 278 K, the stagnation pressure 101.3 kPa, the static pressure is 87.3 kPa and the flow area 0.372 m. Using compressible flow analysis determine the axial velocity and the mass flow rate.
In a trial run, the De Laval steam turbine at Oman Power Plant rotates at 3000 rpm. The steam is issued from the nozzle at 400 m/s and the nozzle angle is 20o. The blade speed ratio is 0.41and the friction loss in the blade channel is 15%of the kinetic energy corresponding to the relative velocity at the inlet to the blades. As a turbine engineer at that station, how do you determine the (i) power developed by the turbine for a flow rate of 10 kg/s and (ii) suitable inlet and outlet angles for the blades when axial thrust is zero. Also, how would you determine the size of the turbine wheel required? Draw a suitable velocity diagram.
a=2 , b=1 The properties of the air in the inlet section with A1 = 0.25ab m2 in a converging-diverging channel are given as U1 = 25a,b m/s, T1 = 3ab K, P1 = 13a,b kPa (absolute). Find the required cross-sectional area, pressure, temperature, velocity and mass flow rate to obtain sonic (Ma2=1.0) flow at the outlet. Calculate critical values of A*, U*, T*, P*. Solve the problem by making the necessary assumptions and drawing the schematic figure.
can you please solve this for me, thanks. 10 kg/s of steam (H2O) enters a turbine at 10 m/s and a specific enthalpy of 3500 kJ/kg and leaves at an outlet 10m below the inlet with a specific enthalpy of 2500 kJ/kg and a velocity of 20 m/s. Assume steady-state steady-flow. If the heat lost from the turbine is 20% that of the turbine work, determine a.) the turbine horsepower. If the turbine is coupled to a generator with a 90% electrical efficiency, and the turbine horsepower has an 80% mechanical efficiency, b.) how much income will a power plant generate in one year if the electrical energy is sold at PhP 3.51 per kW-hr? (Hint: Mechanical efficiency = actual turbine work / ideal turbine work. Electrical efficiency of a generator = electrical output / actual turbine work.)
Steam enters a nozzle at pressure of 1.2 MPa, temperature of 500 oC, and a velocity of 38 m/s and leaves as saturated vapor at 75 kPa, what is the exit velocity (m/s) when a heat loss of 19.5 kJ/kg is present? a. 1263.3 b. Not listed c. 159.9 d. 1273.4 e. 1276.8
A large reservoir maintains air at 6.8×105 P a and 15°C. The air flows isentropically through a convergent and divergent nozzle to another large reservoir where the back pressure can be varied. The area of the throat is 25 cm2 and the area of the nozzle exit is 100 cm2 . Find (a) The maximum mass flow rate through the nozzle. (b) The two values of the Mach number at the nozzle exit corresponding to this mass flow rate. (c) The back pressures required to produce these Mach numbers.
Each stage of an axial-flow compressor is 0.5 reaction,, has the same blade speed and the same flow outlet angle of 30 deg relative to the blades. the mean flow coeficcient is constant for all stages at 0.5. At entry to the first stage the stagnation temperature is 278 K, the stagnation pressure 101.3 kPa, the static pressure is 87.3 kPa and the flow area 0.372 m2. Using compressoble flow analysis determine the axial velocity and the mass flow rate. Determine also the shaft power needed to drive the compressor when there are 6 stages and the mechanical efficiency is 0.99.

SEE MORE QUESTIONS

Recommended textbooks for you

Elements Of Electromagnetics

Mechanical Engineering

ISBN:

9780190698614

Author:

Sadiku, Matthew N. O.

Publisher:

Oxford University Press

Mechanics of Materials (10th Edition)

Mechanical Engineering

ISBN:

9780134319650

Author:

Russell C. Hibbeler

Publisher:

PEARSON

Thermodynamics: An Engineering Approach

Mechanical Engineering

ISBN:

9781259822674

Author:

Yunus A. Cengel Dr., Michael A. Boles

Publisher:

McGraw-Hill Education

Elements Of Electromagnetics

Mechanical Engineering

ISBN:

9780190698614

Author:

Sadiku, Matthew N. O.

Publisher:

Oxford University Press

Mechanics of Materials (10th Edition)

Mechanical Engineering

ISBN:

9780134319650

Author:

Russell C. Hibbeler

Publisher:

PEARSON

Thermodynamics: An Engineering Approach

Mechanical Engineering

ISBN:

9781259822674

Author:

Yunus A. Cengel Dr., Michael A. Boles

Publisher:

McGraw-Hill Education

Control Systems Engineering

Mechanical Engineering

ISBN:

9781118170519

Author:

Norman S. Nise

Publisher:

WILEY

Mechanics of Materials (MindTap Course List)

Mechanical Engineering

ISBN:

9781337093347

Author:

Barry J. Goodno, James M. Gere

Publisher:

Cengage Learning

Engineering Mechanics: Statics

Mechanical Engineering

ISBN:

9781118807330

Author:

James L. Meriam, L. G. Kraige, J. N. Bolton

Publisher:

WILEY

SEE MORE TEXTBOOKS