Lab 2 Recip Engines

The following data is given for a four-stroke diesel engine: Cylinder bore = 250 mm, Length of stroke = 300 mm, Speed = 600 rpm, Indicated mean effective pressure = 0.6 Mpa, Mechanical efficiency 80% Maximum gas pressure = 4 Mpa, Fuel consumption = 0.25 kg per BP per h Higher calorific value of fuel = 44 000 kJ/kg, Assume that 5% of the total heat developed in the cylinder is transmitted by the piston. The piston is made of grey cast iron FG 200 (Sut = 200 N/mm² and k = 46.6 W/m/°C) and the factor of safety is 5. The temperature difference between the centre and the edge of the piston head is 220°C. () Calculate the thickness of piston head by strength consideration. (i) Calculate the thickness of piston head by thermal consideration. (ii) Which criterion decides the thickness of piston head? (iv) State whether the ribs are required. (v) If so, calculate the number and thickness of piston ribs. (vi) State whether a cup is required in the top of the piston head. (vii) If so, calculate…

A four-stroke, four-cylinder diesel engine running at 2000 rpm develops 60 kW. Brake thermal efficiency is 30% and calorific value of fuel (CV) is 42MJ / k_{g} . Engine has a bore of 120 mm and stroke of 100 mm. Take p_{a} = 1.15 kg / (m ^ 3) air-fuel ratio- 15:1 and eta_{m} = .8 Calculate (i) furl consumption kg/s) : (ii) air consumption (m^ 3/s );(ii) indicated thermal efficiency; (iv) volumetric efficiency: (v) brake mean effective pressure and (vi) mean piston speed.

4. The following data provide details for a piston-propeller engine combination for a single-seater aircraft: Table 4 Parameter Value Pistons 4 Bore 11.1 cm Stroke 9.84 cm Compression ratio 6.75 Mechanical efficiency 0.83 Propeller efficiency 0.85 Fuel-to-air ratio 0.08 Pintake 1 atm Tintake 11.85°C RPM 2800 Fuel properties: Density Energy released per kg Oxidizer properties: Y R Ср 0.51 kg/m³ 46.1 MJ/kg 1.4 288 J/kg. K 1008 J/kg. K (a). Graph the ideal and actual P-V diagram for the above engine. Calculate: (b). The power available. (c). The mean effective pressure.

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?

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 o that at nlet is 0.84 for all the blade. Determine (@) The velocity of whirl. (b) The tangential thrust on the blades. (c) The axial thrust on the blades.

Please solve it correctly before it's solved wrong

18 A single-cylinder, two-stroke cycle model airplane engine with a 7.54-cm displace ment produces 142 kW of brake power at 23,000 RPM using glow plug ignition. The square en- gine (bore stroke) uses 31.7 gm/min of castor oil-methanol-nitrome thane fuel at an air-fuel ratio AF = 4.5. During intake scavenging, 65% of the incoming air-fuel mixture gets trapped in the cylinder, while 35% of it is lost with the exhaust be fore the exhaust port closes. Combustion efficie ncy n = 0.94. Calculate: (a) Brake specific fuel consumption. [gm/kW-hr] (b) Average piston speed. [m/sec] (c) Unburned fuel exhausted to atmosphere. [gm/min] (d) Torque. [N-m]

I need a rules used in the ventilation system for the report "air quality and safe entertainment in sports halls" like this photo below but for ventilation system formulas

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

High pressure turbine blades experience the most hostile combination of conditions of any component in a gas turbine engine. Briefly describe this environment and design measures intended to improve turbine blade survival.

Please answer

The following data were obtained during a test of six cylinder otto cycle engine. Speed 2000 rpm, bore 3.5 in stroke 3.75 in, specific fuel consumption base on brake hp.66 lbs. / bhp-hr, brake arm 1.05 ft. HHV of fuel 20000 Btu/lb, Brake Torque 133 ft-lb, friction torque 40 ft-lb room temperature 90 F. barometric pressure 14.7 psia Find:a.) BHP=b.) BMEP=c.) IMEP=d.) IHP=e.) BRAKE THERMAL EFFICIENCY=f.) INDICATED THERMAL EFFICIENCY=

last digit 5 The Snecma M88 is a French afterburning turbofan engine developed by Snecma (now known as Safran Aircraft Engines) for the Dassault Rafale fighter. The following are some preliminary design data at takeoff conditions. The engine pressure ratio 24.5, bypass ratio 0.3 and total air mass flow rate 60+last digit kg/s. Inlet diffuser: stagnation pressure ratio 0.98. Fan: pressure ratio 1.3, isentropic efficiency 0.89, first-stage hubtip diameters 0.22/0.66 m, 0.96. 1. The air inlet velocity to the fan is 150 m/s entering axially and the LP-spool rotating speed is 5000 rpm. Draw the velocity triangle and blade shapes. Calculate maximum inlet relative Mach number. Check if there is any shock formation.

Parameter thrust Thrust chamber pressure Thrust chamber temperature Working fluid Universal gas constant Ambient pressure: At Sea level value 5MN 7MPa 2800K Air At Room Temperature (Ideal Gas) 8.314 J. (Mol. K) -1 101325N/m² At an altitude of 30km 1185.5 N/m² MW= 29kg/Kw The Following Performance and operation data was obtained from a rocket with a a nozzle designed to produce maximum thrust at sea level: Determine; A) Specific Impulse B) Mass Flow Rate C) Throat Diameter D) Exit Diameter E) Thrust Produced at An altitude of 30KM for the same fixed Nozzle Geometry

& Calculate the air standard efficiency of a four stroke Otto cycle engine with the following data : Piston diameter (bore) = 137 mm ; Length of stroke = 130 mm ; Clearance volume 0.00028 m². Express clearance as a percentage of swept volume. [Ans. 56.1% ; 14.6%)