Rapid-quench axially staged combustor

Power plants – Combustion products used as motive fluid – Combustion products generator

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60754, F02C 100

Patent

active

059963514

ABSTRACT:
A combustor cooperating with a compressor in driving a gas turbine includes a cylindrical outer combustor casing. A combustion liner, having an upstream rich section, a quench section and a downstream lean section, is disposed within the outer combustor casing defining a combustion chamber having at least a core quench region and an outer quench region. A first plurality of quench holes are disposed within the liner at the quench section having a first diameter to provide cooling jet penetration to the core region of the quench section of the combustion chamber. A second plurality of quench holes are disposed within the liner at the quench section having a second diameter to provide cooling jet penetration to the outer region of the quench section of the combustion chamber. In an alternative embodiment, the combustion chamber quench section further includes at least one middle region and at least a third plurality of quench holes disposed within the liner at the quench section having a third diameter to provide cooling jet penetration to at least one middle region of the quench section of the combustion chamber.

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Battista et al., "Design and Performance of Low Heating Value Fuel Gas Turbine Combustors", American Society of Mechanical Engineers, Paper No. 96-GT-531 (1996), pp. 1-9.
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MB Cutrone, "Low NOx Heavy Fuel Combustor Concept Program Phase 1A Gas Tests", NASA CR-167877 (Apr. 1982).

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