Lab 2 Recip Engines PDF

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…

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.

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

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?

Please answer

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.

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

Explain how the following jet engine works. Refer to each section of the engine andexplain the purpose of each section.

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.

Please , solve all two questions completely by clear handwritten

intake valve intake compression JO BI Tuel injector the temperature of the gas; power exnaust vaive 0010 exhaust The diagrams show the cylinder of a petrol engine in 4 stages. Petrol vapour and air are drawn into the cylinder, The mixture is then squeezed together, and then exploded by a spark. The explosion pushes down the piston. The exhaust gases are then expelled from the cylinder. Use the first law of thermodynamics to analyse the energy changes during the process. At each stage explain what happens to i) the pressure of the gas; ii)

Using the basic relations given below and detailing your method and assumptions,Develop all the analytical relations required to:1) Determine the temperatures and pressures at all stages of an ideal air-standard SIOtto cycle analysis2) Show that the thermal efficiency of any internal combustion engine can besimplified as a ratio of temperature differences 3) Discuss the concept of Brake Specific Fuel Consumption (BSFC) and propose a rationale for the Figure 1 below (in other words, explain why the BSFC is decreasingbefore increasing with engine speed)

2 A six-cylinder, four-stroke, direct-injection oil engine is to deliver 120 kW at 1600 rpm. The fuel to be used has a calorific value of 43 MJ/kg and its percentage composition by mass is carbon 86.0%, hydrogen 13.0%, non combustibles 1.0%. The absolute volumetric efficiency is assumed to 80%, the indicated thermal efficiency 40% and the mechan- ical efficiency 80%. The air consumption to be 110% in excess of that required for theoretically correct combustion. (i) Estimate the volumetric composition of dry exhaust gas (ii) Determine the bore and stroke of the engine, taking a stroke to bore ratio as 1.5. Assume the volume of 1 kg of air at the given conditions as 0.77 m³. Oxygen in air is 23% by mass and 21% by volume.

Please solve immediately ,I have less time. Answer must be correct to get thumb up.

Please do

You have been asked to help with the low-pressure compressor (LPC) design for a turbofan engine with a bypass ratio of 8.4. The preliminary cycle design calls for the LPC to produce a pressure ratio of 9.4 with the following operating conditions and constraints. .Inlet Conditions TO2 Poz Core Air Mass Flowrate (kg/s) (K) (kPa) 282 24.6 47.0 Design Constraints Maximum Polytropic Efficiency 94.1% Maximum Stage Pr 1.55 Estimate the minimum number of stages required for this LPC. Then assuming the 1st stage of the LPC operates at the maximum allowable pressure ratio, determine the stagnation temperature exiting the 1st stage, and the stage's adiabatic efficiency. Also determine the power (W) required to operate the full LPC (not just 1st stage). Finally, what would be the percent change in the required power if the polytropic efficiency was only 90.0%.

•B// Derive an expression for the degree of reaction in reaction turbine stage by means of flow and blade velocities with exit and entrance angles.

answer please vv

| As a mechanical engineering technician, you are asked by your building manager to investigate the performance of a steam turbine at the main university building. Criticaly compare how heat transfer efficiency will affect the lifetime of the turbine.