FIELD: engine building.
SUBSTANCE: invention relates to a unit comprising housing (12) of gas turbine engine and impeller (14) with blades installed inside said housing. Housing (12) has inner wall (20) including circular strip (24) of abradable material. Blades ends are located opposite strip of abradable material and annular groove (30) contained in housing, wherein band of abradable material is located upstream front, and annular groove (30)—downstream. A strip of abradable material limits annular groove (30) to the rear part. Rear edge of annular groove (30) in axial direction is located at level of rear edges (18B) of blades (18) or behind them.
EFFECT: such design provides optimum use of strip from abradable material in gas turbine engine housing.
11 cl, 7 dwg
