Thermal efficiency of turbojet engine Calculator

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Jet Propulsion

Components of Gas Turbine

Rocket Propulsion

Thermodynamics and Governing Equations

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Turbojets

Performance Parameters

Turbofans

Turbomachinery Equations

Turboprops

✖Propulsive Power refers to the power generated by a propulsion system, crucial in measuring the engine's ability to produce thrust and propel an object or vehicle forward.ⓘ Propulsive Power [P]			+10% -10%
✖Fuel Flow Rate represents the rate at which fuel is consumed or supplied over a specified period, crucial for monitoring fuel consumption and efficiency in various engines or systems.ⓘ Fuel Flow Rate [m_f]			+10% -10%
✖Fuel Calorific Value denotes the amount of heat energy released per unit mass of fuel upon complete combustion.ⓘ Fuel Calorific Value [Q]			+10% -10%

✖Turbojet Thermal Efficiency signifies the ratio of the work output of a turbojet engine to the heat input from fuel.ⓘ Thermal efficiency of turbojet engine [η_th]

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Formula

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Thermal efficiency of turbojet engine

Formula

`"η"_{"th"} = "P"/("m"_{"f"}*"Q")`

Example

`"0.682689"="980kW"/("0.033kg/s"*"43500kJ/kg")`

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Thermal efficiency of turbojet engine Solution

STEP 0: Pre-Calculation Summary

Formula Used

Turbojet Thermal Efficiency = Propulsive Power/(Fuel Flow Rate*Fuel Calorific Value)
η_th = P/(m_f*Q)
This formula uses 4 Variables

Variables Used

Turbojet Thermal Efficiency - Turbojet Thermal Efficiency signifies the ratio of the work output of a turbojet engine to the heat input from fuel.
Propulsive Power - (Measured in Watt) - Propulsive Power refers to the power generated by a propulsion system, crucial in measuring the engine's ability to produce thrust and propel an object or vehicle forward.
Fuel Flow Rate - (Measured in Kilogram per Second) - Fuel Flow Rate represents the rate at which fuel is consumed or supplied over a specified period, crucial for monitoring fuel consumption and efficiency in various engines or systems.
Fuel Calorific Value - (Measured in Joule per Kilogram) - Fuel Calorific Value denotes the amount of heat energy released per unit mass of fuel upon complete combustion.

STEP 1: Convert Input(s) to Base Unit

Propulsive Power: 980 Kilowatt --> 980000 Watt (Check conversion here)
Fuel Flow Rate: 0.033 Kilogram per Second --> 0.033 Kilogram per Second No Conversion Required
Fuel Calorific Value: 43500 Kilojoule per Kilogram --> 43500000 Joule per Kilogram (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

η_th = P/(m_f*Q) --> 980000/(0.033*43500000)

Evaluating ... ...

η_th = 0.682688958551028

STEP 3: Convert Result to Output's Unit

0.682688958551028 --> No Conversion Required

FINAL ANSWER

0.682688958551028 ≈ 0.682689 <-- Turbojet Thermal Efficiency

(Calculation completed in 00.004 seconds)

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Credits

Created by Chilvera Bhanu Teja

Institute of Aeronautical Engineering (IARE), Hyderabad

Chilvera Bhanu Teja has created this Calculator and 300+ more calculators!

Verified by Sagar S Kulkarni

Dayananda Sagar College of Engineering (DSCE), Bengaluru

Sagar S Kulkarni has verified this Calculator and 200+ more calculators!

< 14 Turbojets Calculators

Mass Flow Rate in Turbojet given Thrust

Go Mass Flow Rate Turbojet = (Net Thrust of Turbojet-Nozzle Exit Area*(Nozzle Exit Pressure-Ambient Pressure))/((Exit Velocity-Flight Speed)*(1+Fuel Air Ratio))

Exhaust Velocity given Thrust in Turbojet

Go Exit Velocity = (Net Thrust of Turbojet-Nozzle Exit Area*(Nozzle Exit Pressure-Ambient Pressure))/(Mass Flow Rate Turbojet*(1+Fuel Air Ratio))+Flight Speed

Flight Speed given Thrust in Turbojet

Go Flight Speed = Exit Velocity-(Net Thrust of Turbojet-Nozzle Exit Area*(Nozzle Exit Pressure-Ambient Pressure))/(Mass Flow Rate Turbojet*(1+Fuel Air Ratio))

Nozzle Exit Area in Turbojet

Go Nozzle Exit Area = (Net Thrust of Turbojet-Mass Flow Rate Turbojet*(1+Fuel Air Ratio)*(Exit Velocity-Flight Speed))/(Nozzle Exit Pressure-Ambient Pressure)

Net Thrust Produced by Turbojet

Go Net Thrust of Turbojet = Mass Flow Rate Turbojet*(1+Fuel Air Ratio)*(Exit Velocity-Flight Speed)+Nozzle Exit Area*(Nozzle Exit Pressure-Ambient Pressure)

Exhaust Velocity given Gross Thrust in Turbojet

Go Exit Velocity = (Gross Thrust of Turbojet-(Nozzle Exit Pressure-Ambient Pressure)*Nozzle Exit Area)/(Mass Flow Rate Turbojet*(1+Fuel Air Ratio))

Mass Flow Rate of Turbojet given Gross Thrust

Go Mass Flow Rate Turbojet = (Gross Thrust of Turbojet-(Nozzle Exit Pressure-Ambient Pressure)*Nozzle Exit Area)/((1+Fuel Air Ratio)*Exit Velocity)

Turbojet Gross Thrust

Go Gross Thrust of Turbojet = Mass Flow Rate Turbojet*(1+Fuel Air Ratio)*Exit Velocity+(Nozzle Exit Pressure-Ambient Pressure)*Nozzle Exit Area

Thermal efficiency of turbojet engine

Go Turbojet Thermal Efficiency = Propulsive Power/(Fuel Flow Rate*Fuel Calorific Value)

Net Thrust of Turbojet given Gross Thrust

Go Net Thrust of Turbojet = Gross Thrust of Turbojet-Ram Drag of Turbojet

Gross Thrust of Turbojet given Net Thrust

Go Gross Thrust of Turbojet = Net Thrust of Turbojet+Ram Drag of Turbojet

Ram Drag of Turbojet given Gross Thrust

Go Ram Drag of Turbojet = Gross Thrust of Turbojet-Net Thrust of Turbojet

Mass Flow Rate of Exhaust Gases

Go Mass Flow Rate Turbojet = Mass Flow Rate Turbojet+Fuel Flow Rate

Mass Flow Rate of Exhaust Gases given Fuel Air Ratio

Go Mass Flow Rate = Mass Flow Rate Turbojet*(1+Fuel Air Ratio)

Thermal efficiency of turbojet engine Formula

Turbojet Thermal Efficiency = Propulsive Power/(Fuel Flow Rate*Fuel Calorific Value)
η_th = P/(m_f*Q)

What is thermal efficiency?

Thermal efficiency is a dimensionless performance measure of a device that uses thermal energy, such as an internal combustion engine, a steam turbine or a steam engine, a boiler, furnace.

How to Calculate Thermal efficiency of turbojet engine?

Thermal efficiency of turbojet engine calculator uses Turbojet Thermal Efficiency = Propulsive Power/(Fuel Flow Rate*Fuel Calorific Value) to calculate the Turbojet Thermal Efficiency, The Thermal efficiency of turbojet engine formula is defined as the ratio of propulsive power to the product of fuel flow rate and calorific value of fuel. Turbojet Thermal Efficiency is denoted by η_th symbol.

How to calculate Thermal efficiency of turbojet engine using this online calculator? To use this online calculator for Thermal efficiency of turbojet engine, enter Propulsive Power (P), Fuel Flow Rate (m_f) & Fuel Calorific Value (Q) and hit the calculate button. Here is how the Thermal efficiency of turbojet engine calculation can be explained with given input values -> 0.042473 = 980000/(0.033*43500000).

FAQ

What is Thermal efficiency of turbojet engine?

The Thermal efficiency of turbojet engine formula is defined as the ratio of propulsive power to the product of fuel flow rate and calorific value of fuel and is represented as η_th = P/(m_f*Q) or Turbojet Thermal Efficiency = Propulsive Power/(Fuel Flow Rate*Fuel Calorific Value). Propulsive Power refers to the power generated by a propulsion system, crucial in measuring the engine's ability to produce thrust and propel an object or vehicle forward, Fuel Flow Rate represents the rate at which fuel is consumed or supplied over a specified period, crucial for monitoring fuel consumption and efficiency in various engines or systems & Fuel Calorific Value denotes the amount of heat energy released per unit mass of fuel upon complete combustion.

How to calculate Thermal efficiency of turbojet engine?

The Thermal efficiency of turbojet engine formula is defined as the ratio of propulsive power to the product of fuel flow rate and calorific value of fuel is calculated using Turbojet Thermal Efficiency = Propulsive Power/(Fuel Flow Rate*Fuel Calorific Value). To calculate Thermal efficiency of turbojet engine, you need Propulsive Power (P), Fuel Flow Rate (m_f) & Fuel Calorific Value (Q). With our tool, you need to enter the respective value for Propulsive Power, Fuel Flow Rate & Fuel Calorific Value and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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