Q8: Two engine inlets, one a straight tube, the other a converging-diverging diffuser. Both with M = 2.0 at their inlets, T = 300.K, pi = 0.50 atm. Both slow flow down to same Me. The CD diffuser %3D flow is isentropically and straight diffuser with shock. Compare performance of diffusers of Me, Te, Pe, poe/po.
Q: An engine has an inlet stagnation condition of 300 bar and 4000 kelvin. Methane and liquid oxygen…
A: Given: stagnation pressure = 300 bar stagnation temperature = 4000 K Ae/Ath = 34.34
Q: The velocity of flow after a normal shock wave when (Tx= ,315 K, vx= 555 ms-1) 275.7 ms-1 O 396.1…
A:
Q: QUESTION 2 A compressor blade design tested in a cascade is found to choke with an inlet Mach number…
A: Refer the compressible flow tables,
Q: 8.6 A single sided centrifugal compressor is to deliver 14 kg of air per second when operating at a…
A:
Q: A commercial aircraft flies at 0.86 at altitude of 10000 feet above sea level. The inlet has been…
A: Given: gamma = 1.38 Mach number , M = 0.86 pressure recovery = 0.96
Q: Helium, at T0 = 400 K, enters a nozzle isentropically. Atsection 1, where A1 = 0.1 m2, a…
A: The adiabatic index for Helium is 1.66 and the characteristic gas constant is 2077 J/kg.k, (a) The…
Q: Consider a reciprocating air compressor with two-stage, 6.8 m/min free air delivery at atmospheric…
A: two stage reciprocating compressor with the intercooler given v=6.8 m3/min =0.113 m3/sP1=100…
Q: hand writtten plz Q3. A 2000 CC four stroke CI engine intakes air at a rate (mass flow rate) of…
A:
Q: A single-sided centrifugal compressor designed with no pre-whirl has the following dimensions and…
A:
Q: The Mach no. of a fixed geometry inlet at overspeeded for starting mode (Ai= 0.13 m2, ,At= 0.095 m2)
A: Given data: Area at inlet, Ai = 0.13 m2 Area at throat, At = 0095 m2
Q: A high-pressure air reservoir is connected to the inlet of a convergent-divergent nozzle with an…
A: Nozzle : It is a device which having reducing cross sectional area from entrance to exit. This…
Q: Example 14.3 A supersonic two-dimensional inlet is to be operate at M 3.0. Two possibilities will be…
A:
Q: Assuming the clearance is negligible for a single stage compressor with the following data.…
A:
Q: conditions are 101.3 kPa and 15°C. The clearance volume is 6% of the stroke volume and the…
A:
Q: A three-stage, single-acting air compressor with a polytropic index of 1.22 in all stages, runs in…
A:
Q: Albert bought a portable device to pump his truck tyres. On the manual, he found out that the device…
A:
Q: Consider a reciprocating air compressor with two-stage, 8.4 m/min free air delivery at atmospheric…
A:
Q: A single-stage, single-acting air compressor with runs at speed 600 rpm. It has a polytropic index…
A:
Q: bar respectively, and AF = 15. Calculate: (i) Throat diameter of the carburetor. (ii) Fuel orifice…
A:
Q: Consider a reciprocating air compressor with two-stage, 6.8 m3/min free air delivery at atmospheric…
A: Given: The FAD = 6.8 m^3/min The inlet pressure, P1 = 107 kPa The inlet temperature, T1 = 19 C The…
Q: (7) The entropy change across a normal shock wave (Tox= 505 K, vx= 490 ms-1), * O 0.0008 Jkg-1K-1…
A: Given:Tox=505 KVx=490 m/s
Q: Q1/ An aircraft has a turbojet engine and a convergent nozzle. Where the inlet section parameters…
A: Convergent nozzle increases the flow speed by restricting the flow path. For high nozzle pressure,…
Q: (5) The impulse at exit section of an isentropic converging-diverging nozzle operates at chocking…
A:
Q: An IFR turbine rotor is designed with 13 vanes and is expected to produce 400 kW from a supply of…
A:
Q: A single-acting single-stage reciprocating air compressor running at 1000 rev/min delivers air at 25…
A:
Q: 6.33 A normal-shock inlet operates in a Mach 1.86 stream with ambient static pressure of Po = 30…
A: given; mach number(M)=1.86static pressure(P0)=30KPaspecific heat ratio of air (k)=1.4dynamic…
Q: 7. A four-stroke, 6-cylinder, 3.6 Itr SI engine, is designed to have a maximum speed of 6000 r.p.m…
A: Carburetion is defined as the mixture of proper amount of fuel with air prior to entering in the…
Q: Consider a reciprocating air compressor with 2-stage, 6.9 m/min free air delivery at atmospheric…
A:
Q: Example 7.10 The following particulars relate to a single-sta rtex design: Inlet temperature, Tot…
A: T01=1100Kp01=4barCpg=1.147kJ/kgγ=1.33
Q: 5, bypass ratio 0.3 and total air mass fle essure ratio 0.98. tropic efficiency 0 89 first-stage…
A: The Snecma M88 is a French afterburning turbofan motor created by Snecma for the Dassault Rafale…
Q: 10.26 An axial-flow fan operates in seal-level air at 1350 rpm and has a blade tip diameter of 3 ft…
A: Calculate the velocity at mean blade radius. U=Dmean2ω=3+2.522π×135060=388.77 ft/s
Q: Q88 A test carried out on a single cylinder, twe- stroke oil engine gave the fallowing datag…
A: Write the given data with suitable variables. d=200 mm=0.2 m1000 mm1 mL=250 mm=0.25 mN=300…
Q: A single stage, double acting air compressor delivers 15 m^3 of air per minute measured at 1.013 bar…
A: An air compressor is a machine which takes in atmospheric air, compresses it with the help of some…
Q: A Laval nozzle exhaust air from a large reservoir into ambient conditions (Ps = 100 kPa) and (Mexit…
A:
Q: Assuming the clearance is negligible for a single stage compressor with the following data.…
A:
Q: A single-stage, single-acting air compressor running at 1000 rev/min delivers air at 2.5 MPa bar.…
A: To find: The bore and stroke, swept volume, delivery temperature, the volumetric efficiency, the…
Q: 10 m3 /min of free air is to be compressed to 8 bar gauge in two stages. Assuming an intercooler…
A:
Q: What is the intake valve diameter (in mm) required for good volumetric efficiency for a square…
A:
Q: . Calculate 1.The delivery air indicated power in KW to two decimal places. 1.The volume of air…
A:
Q: 6.33 A normal-shock inlet operates in a Mach 1.86 stream with ambient static pressure of Po = 30kPa.…
A: a) For Mach numberM0 1.86 from normal shack table: P02P01=.7855 P02=30*.7855=23.565 kPa
Q: QUESTION 7 Consider a reciprocating air compressor with two-stage, 6.8 m/min free air delivery at…
A: For solution refer below images,
Q: 6. A four-stroke, 6-cylinder, 3.6 Itr SI engine, is designed to have a maximum speed of 6000 rn m At…
A: Given Data:
Q: (a) A pitot tube indicates a pressure of 265 kPa in an airstream in which the temperature is 10°C…
A: Given that, Po=265 kPa,To=10 °C=283 K,Mach number, M=1.5, The pressure ratio is given as,…
Q: A single stage, double acting air compressor is required to deliver 14 m³ of air per min measured at…
A:
Q: 6. The first stage of an axial flow compressor is designed for free vortex conditions, with no inlet…
A: Given: N=13000 rpm∆Ts=18°Ck=0.6ηW=0.94η=0.91v=150 m/sp01=1 barT01=300 K
Q: Q3: A single stage, double acting air compressor running at 1000 rev./min delivers air at 25 bar and…
A:
Q: The mass flow rate from a converging-diverging nozzle (Ae= 0.02 m2, po= 200 kPa, To= 345 K, pb= 160…
A: Ae=.02 m2P0=200 kPaT0=345 KPb=160 kPaMass flow rate m˙=A0P0kRT0 2k+1k+12(k-1)Where R=.287 kj/kgK and…
Q: Calculate the air standard efficiency and work of a Diesel cycle, has a clearance volume of 0.00025…
A: given: Vc = V2 = 0.00025 m3 bore diameter = 152.5mm and stroke length = 200mm P1 = 100kPa ; T1 =…
Q: The engine for a supersonic aircraft has a variable-geometry exhaust nozzle. Determine the optimum…
A:
Step by step
Solved in 2 steps with 3 images
- 3.11) The conditions of air at the entry of an axial compressor stage are: Рi %3D 768 тт Hg & Ti = 314 K. The air angles are B1 = 51°, B2 = 9°, a1 = az = 7°. The mean diameter 50 ст. The peripheral speed 100 m/s. Mass-flow rate 25 kg/s work done factor 0.95 mechanical efficiency 92 % stage efficiency 88 % (a) Air angle at the stator entry, [a2 50.18°] (b) Blade height at entry and the hub-tip diameter ratio, [h, = 19 cm ; dn/d = 0.449] (c) Stage loading coefficient. [V = 0.754] (d) Stage pressure ratio. [Po3/Po1 1.075] (e) The power required to drive the stage. [Power = 204.75 kW]7. A four-stroke, 6-cylinder, 3.6 Itr SI engine, is designed to have a maximum speed of 6000 r.p.m with a volumetric efficiency of 92%. Apa 0.07 bar, C, = 0.85, Cf 0.6, fuel density is 700 %3D %3D = 1.03 bar, and AF 15. Calculate: (i) Throat diameter of the kg/m'. At sea level T 27°C, Pa carburetor. (ii) Fuel orifice area. (iii) AF at altitude of 2000 ma ull 36 ull zain IQ Asiacell 7:1A IC K/s HW9-2.jpg HW9-2 The rc (cutoff ratio) expression, which derived to form as qin * R (1+): (T, rk-1) B (Ctrl) for an air-standard Diesel cycle. D
- AIR W COMP. IN COMPRESSOR DE T1= 26.85°C P1= IBAR QUESTION b) c) = 6700kW T2 = P2 = T5 MASS FLOW RATE iN g/s PS = PA 346.85°C 12 BAR OF EN TRO PY Plo Дис пого AIR AIR (4 unuy REGENERATIVE #EAT EXCHANGER IN GAS TURBINE POTENTIAL ENERGY, KINETIC INERGY, STRAY HEAT ARE NOT SIGNIFICANT. RATE 11 ms T4= P4 = PS m₁ = T3 P3 = P2 = 506.85°C 486.85°C GOING INTO COMPRESSORA power generator with two-cylinder, four-stroke gas engine has a bore of480 mm and a stroke of 585 mm. At 300 rev/min the torque developed is10 kNm. The generator is supplied with a mixture of gas and air in theproportion of 1 to 8 by volume. The estimated volumetric efficiency is 80% and the net calorific values of the fuel is 48.6 MJ/m3. Calculate: 1. the swept volume in m3/min, 2. the volume of mixture induced in m3/min 3. the gas flow to engine m3/min4. the energy supplied by gas5. the brake thermal efficiencyFor two row velocity compounded simple impulse turbine wheel derive the expressions for Diagram Power and Diagram Efficiency and also prove that : i. (P )max = 8 Cb? ii. ( na )max = Cos'ai
- 20 stages of MSF-M with the following main parameters: intake: 1500 kg/s, 35,000 ppm, 20 C; blow down brine: 38 C, 69,000 ppm recycle brine about 79% of blow down brine steam supplied to brine heater: 2kg/s, 115 C The top brine temperature : 100 C performance ratio: 8.5 calculate all the characteristics of the system for first stage (x, tin, tout, Tin, Tout, Mdi, Mbi, TVi, Ai, Ab and the width and the lengthSteam heating system air, water vapor passing throughit is heated by passing over pipes. Air and steamits streams are continuous streams. 200 kPa to the steam heat exchanger and200oC temperature, 8 kg per minute flow entering, 180 kPapressure is rising at 100oC and temperature. Air pressure of 100 kPa andIt enters at a temperature of 25oC and exits at a temperature of 47oC. Aircalculate the volumetric flow rate at the input.Air enters an adiabatic diffuser at P = 82000 Pa and 291.15 K while u = 230 m/s. It exits at P = 97000 Pa and u = 0 m/s. Calculate the exit temperature. Cp air = 3.5R where R = 8.314 J/mol K. a. 45.11 °C b. 46.01 °C c. 44.36 °C d. 47.09 °C
- Q.1 formula (CH19O..1) produces 300 Nm @ 2400 rpm. The displacement volume of the engine is 2 litres and A 4-stroke, 4-cylinder diesel engine operating with bio-diesel fuel with an equivalent molecular the intake air flow rate is 69.6 g/s. LHV of fuel is 41 MJ/kg. Measurement of the engine exhaust gives the following volumetric concentrations: 200 ppm CO 32 mg soot / m of exhaust Assuming a brake thermal efficiency of 40%, density of exhaust as 1.15 kg/m' and molar mass of exhaust as 29 kg/kmol, determine the soot and CO emissions in g/kWh6. Air as an ideal gas flows through the turbine and heat exchanger arrangement. Data for the two flow streams are shown on the figure. Heat transfer to the surroundings can be neglected, as can all kinetic and potential energy effects. Determine T3, in K, and the power output of the second turbine, in kW, at steady state.A test on a single cylinder, four stroke oil engine having a bore of 15cm and stroke 30 cm gave the following results: speed 300 rpm, brake torque 200 Nm, indicated mean effective pressure 7 bar, fuel consumption 2.4 kg/h, air fuel ratio 22, room temperature 20°C and pressure at 1 bar. The fuel has a calorific value of 42 MJ/kg and contains of 15% by weight of hydrogen. Calculate: i. indicated thermal efficiency ii. volumetric efficiency