Heat transfer in a Gas Turbine

Recently many gas turbine manufacturers are trying to improve the efficiency by increasing the temperature in the combustion chamber

but this temperature is limited due to constrain in material properties and cooling efficiency of hot gas path parts.

(1) Plesae tell me in detail how does heat transfer process take place in a brayton cycle gas turbine?

(2) What is the heat balance equation?

Ever hear of Google ???

Look here http://www.google.com/search?sourceid=gmail&q=heat%20transfer%20in%20the%20brayton%20cycle

Turbo Man

Gas Turbine manufacturers have made great strides in increasing efficiency. The "recoup" design is the way many of them are going. They recover exhaust heat by preheating the compressor discharge air before it enters the combustor. Efficiencies into the 60 & 70% ranges and beyond have been seen. IMO it makes little economic and environmental sense to dump hot exhaust into the atmosphere. Closed and/or combined cycle is the way to go if you have a use or customer for the waste heat you recover. Edmund

Thermodynamic efficiency will vary depending on make of the turbine. The full mathematical equation for calculating Gas Turbine efficiency can be found on the web (as the previous post said) a good place to check is www.vibronurse.com (odd name but a very good engineering reference site) they have a Gas Turbine efficiency calculator and more importantly a complete listing of the mathematics involved.

They also have a chart of nominal performances however some of the numbers for RR are way off. The calculation method is sound we have tried it on the our Plant (we run some RR Avons) and the numbers tie in with our Control Systems estimate.