Thermal control passages for horizontal split-line flanges of gas turbine engine casings

摘要

A casing for a gas turbine engine having a longitudinal axis extending therethrough, including a first casing portion having a substantially arcuate section and a split-line flange extending from each end thereof and a second casing portion having a substantially arcuate section and a split-line flange extending from each end thereof. The first and second casing portions are mated at each end by connecting together respective pairs of the split-line flanges. A channel is formed in at least one mating surface of the split-line flanges to provide an axial passage therethrough so that air flow provided to the axial passage reduces a temperature gradient between the arcuate sections and the flanges of the first and second casing portions. The gas turbine engine casing also includes a first radial channel formed in at least one mating surface of the split-line flanges to provide an entrance to the axial passage and a second radial channel formed in at least one mating surface of the split-line flanges to provide an exit to the axial passage so that flow communication is established between a flowpath through the casing and the axial passage.