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![Page 1: Analysis of Turbo Combustor P M V Subbarao Professor Mechanical Engineering Department A Device to Anchor the Flame…. The Cause of Major component of.](https://reader035.fdocuments.net/reader035/viewer/2022070401/56649f1b5503460f94c312d3/html5/thumbnails/1.jpg)
Analysis of Turbo Combustor
P M V Subbarao
Professor
Mechanical Engineering Department
A Device to Anchor the Flame….The Cause of Major component of Running Cost…..
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Reciprocating Engine Vs Jet Engine
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Fire is An Accident…
How to make it More reliable Resource….
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Laws of Combustion
• A Special Device is required to hold the flame, called Burner.
• The maximum quantity of fuel that can be handled by a single burner is limited.
• The maximum allowable air to establish efficient combustion of a given amount of fuel is limited.
• The maximum temperature due to efficient combustion is always higher than the maximum safe temperature: limited by turbine blades.
• Infra structure should be provided to facilitate these conditions.
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Requirements of A Reliable Combustion
MATt Theory
• Mixing: Fuel preparation systems.
• Air: Draught systems.
• T : Preheating of fuel.
• t : Dimensions of combustion chamber. : Turbulence generation systems.
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Combustion Section• The combustion section contains the combustion
chambers, igniter plugs, and fuel nozzle or fuel injectors.
• Designed to burn a fuel-air mixture and to deliver combusted gases to the turbine at a temperature not exceeding the allowable limit at the turbine inlet.
• Theoretically, the compressor delivers 100 percent of its air by volume to the combustion chamber.
• The fuel-air mixture suitable for efficient combustion has a ratio of l5 parts air to 1 part fuel by weight.
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Combustion Section Contd…….
• Approximately 25 – 30 percent of total compressor air is used to attain the desired fuel-air ratio.
• The remaining 70 -- 75 percent is used to form an air blanket around the burning gases and to dilute the temperature.
• The diluted temperature may reach as high as 1500º C, by approximately one-half of the flame temperature.
• This ensures that the turbine section will not be destroyed by excessive heat.
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Air Distribution in A Combustor
Compressor end Turbine end
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Functions• The air used for burning is known as primary air; • Remaining for cording is secondary air. • Secondary air is controlled and directed by holes and
louvers in the combustion chamber liner. • Igniter plugs function during starting only; they are shut
off manually or automatically. • Combustion is continuous and self-supporting. • After engine shutdown or failure to start, a pressure -
actuated valve automatically drains any remaining unburned fuel from the combustion chamber.
• The primary function of the combustion section is, of course, to bum the fuel-air mixture, thereby adding heat energy to the air.
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• To do this efficiently, the combustion chamber must
• Provide the means for mixing the fuel and air to ensure good combustion.
• Bum this mixture efficiently.
• Cool the hot combustion products to a temperature which the turbine blades can withstand under operating conditions.
• Deliver the hot gases to the turbine section.
• The location of the combustion section is directly between the compressor and turbine sections.
.
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• The combustion chambers are always arranged coaxially with the compressor and turbine, regardless of type, since the chambers must be in a through-flow position to function efficiently.
• All combustion chambers contain the same basic elements:
• A casing • A perforated inner liner. • A fuel injection system. • Some means for initial ignition. • A fuel drainage system to drain off unburned fuel
after engine shutdown.
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Basic Anatomy of A Combustor
Casing
LinerSwirler
Liner holes
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Classification of Combustors
• Basis for this classification:• A burner handles finite amount of fuel.• Arrangement of multiple burners.• There are currently three basic types of Burner
Arrangements• The multiple-chamber or can type. • The annular or basket type. • The can-annular type.