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US 2014/0338351 A1Published application
Gas turbine engine combustor with tailored temperature profile
AssigneeUnited Technologies Corporation
InventorsTimothy S. Snyder, Randal G. McKinney, James B. Hoke
Life of this patent
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Abstract
A method of tailoring a combustor flow for a gas turbine engine includes controlling an airflow into a swirler to be generally uniform and controlling an airflow into a quench zone to provide a desired pattern factor.
Claims20
A method of tailoring a combustor flow for a gas turbine engine, comprising:
- controlling an airflow into a swirler;
- and
- controlling an airflow into a quench zone to provide a desired pattern factor.
A method of tailoring a combustor flow for a gas turbine engine, comprising:
- controlling interaction of a fuel-air mixture from a swirler with an airflow into a quench zone.
A combustor of a gas turbine engine comprising:
- a liner assembly with a quench hole and a multiple of trim holes downstream thereof.
Dependencies are inferred from the claim text.