TURBOCOMPRESSOR Russian patent published in 2001 - IPC

FIELD: mechanical engineering; axial-flow, direct-flow and mixed-flow compressors of gas turbine plants. SUBSTANCE: special over-rotor device is placed over ends of blades of impellers 2. This device consists of ring space 3 and ring lattice formed by straight-line ribs and slots between ribs. Space 3 communicates with compressor blading through this lattice. Ring space 3 can be made variable in height and provided with additional plates installed behind the lattice. Walls of ring space 3 can be made curvilinear, and additional plates can be made curvilinear and shaped. Compressor can be furnished with additional chamber connected to space 3. EFFECT: enlarged range of gas-dynamic stability of compressor and aeroelastic stability of its blades with preservation of efficiency level. 7 cl, 5 dwg