Structure for cooling gas turbine engine
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United States of America Patent
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Oct 20, 2020
Grant Date -
Feb 1, 2018
app pub date -
Jul 27, 2016
filing date -
Jul 27, 2016
priority date (Note) -
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Abstract
Formed in a wall part of a dome part of an annular combustor encircling an axis of a gas turbine engine are multiple fuel supply holes spaced at predetermined intervals in circumferential direction around the axis and many cooling holes extending through the wall part in direction inclined to a normal thereof. When two adjacent fuel supply holes are defined as first and second fuel supply holes, a virtual boundary line contacting an outer semi-circular portion, far from the axis, of the first fuel supply hole and an inner semi-circular portion, close to the axis, of the second fuel supply hole is set. The first cooling holes in region radially outward, relative to the axis, of the line are inclined toward the second fuel supply hole, and the second cooling holes in region radially inward, relative to the axis, of the line are inclined toward the first fuel supply hole.
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