FIELD: engines and pumps.
SUBSTANCE: invention relates to multi-stage compressor for turbomachine, in particular for aircraft turboprop or turbojet engines. Proposed compressor comprises housing with dual wall, inner wall being made up of shrouds enveloping appropriate circular rows of stator rotating vanes and circular rows of straightening vanes. Note here that aforesaid shrouds are attached to housing outer wall by independent attachments.
EFFECT: chances of controlling radial clearance between outer ends of rotating vanes and shrouds, independently in several compression stages.
12 cl, 3 dwg
