FIELD: engine manufacture; axial-flow compressors for gas-turbine engines.
SUBSTANCE: proposed axial-flow compressor has stator with return-circuit rig vanes as well as drum-and-disk rotor incorporating separate impellers joined together in tandem by means of tight-fitting bolts. Each impeller has blades built of shaped feather and root, disks with rims, sheet, hub, annular fillet with flange, and fillet holes to receive tight-fitting bolts. Each impeller is provided with two disks disposed in tandem along flow in longitudinal sectional area of drum. Both disks are joined together by means of annular fillet of first disk and seating ring with holes in second-disk sheet; annular fillet of second disk forms channel drum shell under return-circuit rig vanes to function as spacer between second and first disks of each next compressor stage. Moving-blade root is made in the form of shelf with stiffening ribs on its inner side; assembled shelves form bushing-type channel drum shells of impellers and have wedge-shaped annular projections on front and rear ends along flow. Rims of impeller disks have mating wedge-shaped annular depressions which form annular dovetailed slot upon installation and tightening of tight-fitting bolts in first and second disks of each impeller for contacting wedge-shaped annular projections at ends of moving-blade shelves.
EFFECT: reduced mass of compressor rotor.
1 cl, 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| GAS-TURBINE ENGINE AXIAL-FLOW COMPRESSOR (VERSIONS) | 2004 |
|
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