7. A converging-diverging nozzle receives steam at apressure of 380 psia with temperature of 480F andexpands it to a pressure of 50 psia. Assuming the velocity coefficient of 0.98throat condition and an overall nozzle efficiency of92 percent, calculate the following:A. The actual throat velocity, fus 7532B.The mass rate of flow for a throat diameter of0.50 in, lb/min60.1The actual kinetic energy available at the nozzleexit, Btu/lb148.5.The actual nozzle exit velocity, ft/sec 272+The required nozzle exit diameter, inches andF. The length of the divergent section of the nozzle,in inches, for an included angle of 12 degreesbetween nozzle sides.1,05C.D.E.0.72

Answered: Image /qna-images/answer/8f4fb095-d863-4a9d-8448-dfff0042678e.jpg

Answered: 7. A converging-diverging nozzle…

7. A converging-diverging nozzle receives steam at a pressure of 380 psia with temperature of 480F and expands it to a pressure of 50 psia. Assuming the

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

EMERGENY!!!! A perfect gas of adiabatic type expands from 1200K and 900kPa to 700k. Calculate the volumetric flow at the turbine inlet when the power generated by the turbine is 400kW. (CP=1.13kj/kg K Cu =0.83kj/kg K VE R=0.30 kj/kgK )
3. A converging nozzle is fed with air from a large reservoir where the temperature and pressure are 400 K and 170 kPa, respectively. The nozzle has an exit cross - sectional area of 0.001 m2 and discharges into the atmosphere with a pressure of 100 kPa. The flow is isentropic throughout the nozzle. Determine the pressure, Mach number, temperature and velocity at the exit plane, and also find the mass flow rate. (Ans: 100 kPa, 0.9, 344.8 K, 334.8 m - s1, 0.3388 kg - s').
Air is flowing in a convergent nozzle. At a particular location within the nozzle the pressure is 280 kPa, the stream temperature is 345 K. and the velocity is 150 m/s. If the cross-sectional area at this location is 9.29 x 103 m², find: (a) The Mach number at this location, (b) The stagnation temperature and pressure. (c) The area, pressure, and temperature at the exit where M-1.0. (d) The mass rate of flow for the nozzle. Indicate any assumptions you may make and the source of data used in the solution.
In thehydroelectric power plant, water enters the turbine nozzles at 700 kPa absolute witha low velocity. If the nozzle outlets are exposed to atmospheric pressure of 100 kPa. Using Bernoulli equation, determine the maximum velocity to which watercan be accelerated by the nozzles before striking the turbinebuckets.
(b) Steam is expanded isentropically in a convergent-divergent nozzle from 15 bar pressure and 380 °C temperature to a pressure of 1.5 bar at the nozzle exit. The mass of steam that has to pass the nozzle is 3.18 kg/sec. Neglecting the inlet velocity to the nozzle, calculate; i. the throat area of the nozzle, ii. the required exit area of the nozzle for equilibrium flow. Take r = 1.4, and R = 287 J/kg K.
The compressor of a jet engine tested at sea level on a stationary test bed on a day when the atmospheric temperature and pressure is 298 K and 101kPa, respectively. When running at its design operating point, the masss flow rate through the compressor is measured as 15 kg/s and the rational speed is 6200 rpm. Determine the mass flow rate and the rational speed when the compressor is operating at the design operating point during high altitude cruise with an onlet stagnation temperature of 236 K and an inlet stagnation pressure of 10.2 kpa. The design pressure ratio of compressor is 20. If the compressor isentropic efficiency is determined from the test to be 85=, calculate the power input at the cruise condition. Assume for air that y=1. 4 and Cp=1005 kJ/kg-K throughout.
3. A converging nozzle is fed with air from a large reservoir where the temperature and pressure are 400 K and 170 kPa, respectively. The nozzle has an exit cross-sectional area of 0.001 m? and discharges into the atmosphere with a pressure of 100 kPa. The flow is isentropic throughout the nozzle. Determine the pressure, Mach number, temperature and velocity at the exit plane, and also find the mass flow rate. (Ans: 100 kPa, 0.9, 344.8 K, 334.8 m-s, 0.3388 kg-s).
3. A converging nozzle is fed with air from a large reservoir where the temperature and pressure are 400 K and 170 kPa, respectively. The nozzle has an exit cross-sectional area of 0.001 m? and discharges into the atmosphere with a pressure of 100 kPa. The flow is isentropic throughout the nozzle. Determine the pressure, Mach number, temperature and velocity at the exit plane, and also find the mass flow rate. (Ans: 100 kPa, 0.9, 344.8 K, 334.8 m-s1, 0.3388 kg-s´).
A multi-stage high-pressure steam turbine is supplied with steam at a stagnation pressure of 7 MPa. and a stagnation temperature of 500°C. The corresponding specific enthalpy is 3410 kJ/kg. The steam exhausts from the turbine at a stagnation pressure of 0.7 MPa, the steam having been in a superheated condition throughout the expansion. It can be assumed that the steam behaves like a perfect gas over the range of the expansion and that y = 1.3. The specific volume of superheated steam is represented by pv = 0.231(h-1943) where p is in kPa, v is in mkg and h is in kJ/kg. Given that the turbine flow process has a small-stage efficiency of 0.82, detemine the temperature and specific volume at the end of the expansion. Following the Q1, find out the reheat factor RH.
The tunnel exhausts to the ambient environment, where the back pressure is Patm. The starting stagnation temperature of the supply air is 300 K for all conditions, unless specified otherwise. PartB: Considering only tunnel Mach numbers of 1.5, 2 and 3, with test section cross-sectional areas of 6 x 6 in and 12 x 12 in and a diffuser divergence angle of 3°; calculate the following. 1. An angle of the sidewalls of the test section that would be required to keep the Mach number in the test section constant. Use a test section length of 2 times its height.
1)Air is supplied to a converging nozzle from a large reservoir where the temperature and pressure are 400 Kand 150 kPa, respectively. At a certain cross-section where the area Is 0.01 m2, the pressure and velocity are 100 kPa and 120 ms·', respectively. Assuming adiabatic flow, find the Mach number at this cross-section and determine the mass flow rate. 2) Helium flows adiabatically through a duct. At some section, where the area is 0.02 m2, the velocity is 500 ms·1 and the pressure is 100 kPa. Find the Mach number at the given section, and determine the mass flow rate if the stagnation temperature is 300 K
6 A converging nozzle Is fed with air from a large reservoir where the . temperature and pressure are 400 K and 170 kPa, respectively. The nozzle has an exit cross-sectional area of 0.001 m2 and discharges into the atmosphere with a pressure of 100 kPa. The flow Is isentropic throughout the nozzle. Determine the pressure, Mach number, temperature and velocity at the exit plane, and also /ind the mass flow rate.