Gas Turbine Ideal Cycle Analysis


The simplest way to predict the behaviour of a gas turbine engine is to use an ideal one dimensional gas dynamics/ thermodynamic analysis. Assuming the engine operates on an ideal Brayton cycle, then the problem becomes one of tracking gas flow through an ideal intake, isentropic compression, constant pressure combustion and finally isentropic expansion through a turbine and nozzle.

Some simple assumptions are needed to allow for the calculations to proceed.

1. Isentropic intake and compression (no losses)

2. Constant pressure combustion. As the flow is relatively slow in the inlet to the combustion chamber then it can be assumed that the pressure is roughly equal to the stagnation pressure of the flow at this point. The stagnation temperature rise is based on the mass flow rate of fuel injected and its calorific value, giving rise to an enthalpy change CpTo

3. The turbine provides all required energy to drive the compressor and/or fan.

4. Isentropic expansion through the exhaust nozzle back to surrounding ambient pressure.

For a simple core only engine, the change in velocity of the exhaust gas compared to inlet stream will be an ideal measure of the thrust generated.

where is the mass flow rate of air and fuel through the core of the engine.

When the engine is also driving a fan to produce cooler bypass flow then the total thrust can be found by summing the momentum change to both bypass and core gas streams.

In the following application, the prediction of thrust for a typical commercial aircraft turbo-fan engine can be investigated. To explore a range of operating conditions input values can be set for

Stream Conditions : Altitude, Flight Mach Number

Engine Conditions/Geometry : Compressor Pressure Ratio (CPR), Fan Pressure Ratio (FPR), Bypass Ratio, Fuel-Air Ratio.

The application predicts thrust and specific fuel consumption based on these input conditions. Note, the solution does not include any second order effects and does not check whether the engine is operating within sensible physical limits.


Ideal Cycle Analysis for TurboFan

MS Windows Application : Gasturbine (811kB)


For an overview on the operation of many types of aircraft engine
visit the
Pratt & Whitney information pages.

 

© Copyright 2004, Aerospace, Mechnical and Mechatronic Engg.
University of Sydney.