Modulated combustor bypass
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United States of America Patent
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Nov 10, 2020
Grant Date -
Apr 18, 2019
app pub date -
Oct 12, 2017
filing date -
Oct 12, 2017
priority date (Note) -
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Abstract
A combustor section of a gas turbine engine includes a combustor having a combustor inlet, and a combustor bypass passage having a passage inlet located upstream of the combustor inlet. The combustor bypass passage is configured to divert a selected bypass airflow around the combustor. A combustor bypass valve is located at the combustor bypass passage to control the selected bypass airflow along the combustor bypass passage. A method of operating a gas turbine engine, includes urging a core airflow from a compressor section toward a combustor section, flowing a first portion of the core airflow into the combustor section via a combustor inlet, and flowing a second portion of the core airflow into a combustor bypass passage via a combustor bypass valve, thereby bypassing the combustor with the second portion of the core airflow.
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