Modulated combustor bypass and combustor bypass valve
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United States of America Patent
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Jul 13, 2021
Grant Date -
Jul 11, 2019
app pub date -
Jan 8, 2018
filing date -
Jan 8, 2018
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 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. The combustor bypass valve including a valve element configured to rotate about an engine central longitudinal axis A to move one or more valve openings relative to one or more bypass passage openings.
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