FIELD: engines and pumps.
SUBSTANCE: double-flow gas turbine engine, namely aircraft double-flow jet turbine engine includes intermediate casing between primary flow channel and secondary flow channel, which is located in axial direction between low pressure compressor and high pressure compressor. Gas turbine engine also includes unloading passage to remove some part of gas flow supplied by low pressure compressor in the direction of secondary flow channel behind the stream from support brackets located on peripheral part of intermediate casing. Gas turbine engine has unloading hole opening in the flow direction before support brackets and sliding gate valve occupying three positions. In closed position the sliding gate valve fully covers the unloading passage and unloading hole. In intermediate position the unloading hole opening in flow direction before support brackets is shutoff while the unloading passage allowing to provide the removal of some part of gas flow behind support brackets in flow direction is open. When in open position, both the unloading hole opening in flow direction before support brackets and unloading passage opening in flow direction behind support brackets are open.
EFFECT: invention provides satisfactory hail removal.
6 cl, 6 dwg
