What is a gas turbine combustor?
A gas turbine combustor must satisfy a wide range of requirements whose relative importance varies among engine types. However, the basic requirements of all combustors may be listed as follows:
1. High-combustion efficiency (i.e., the fuel should be completely burned so that all its chemical energy is liberated as heat)
2. Reliable and smooth ignition, both on the ground (especially at very low ambient temperatures) and, in the case of aircraft engines, after a flameout at high altitude
3. Wide stability limits (i.e., the flame should stay alight over wide ranges of pressure and air/fuel ratio)
4. Low pressure loss
5. An outlet temperature distribution (pattern factor) that is tailored to maximize the lives of the turbine blades and nozzle guide vanes
6. Low emissions of smoke and gaseous pollutant species
7. Freedom from pressure pulsations and other manifestations of combustion- induced instability
8. Size and shape compatible with engine envelope
9. Design for minimum cost and ease of manufacturing
10. Maintainability
11. Durability
12. Petroleum, synthetic, and biomass-based multifuel capability.
For aircraft engines, size and weight are important considerations, whereas for industrial engines more emphasis is placed on other items, such as long operating life and multifuel capability. For all types of engines, the requirements of low fuel consumption and low pollutant emissions are paramount.
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