FIELD: mechanical engineering; stators of axial-flow compressors of gas-turbine engines. SUBSTANCE: stator includes inner casing with guiding devices mounted in it, outer casing embracing the inner casing forming circular chamber, device located inside this chamber and used for regulation of radial clearances between stator and rotor blades; inner casing is divided lengthwise by means of circular slits; device for regulation of radial clearances is made in form of segment reservoirs of box-shaped section mounted on each section of inner casing embracing it in spaced relation. Holes of side walls of boxes are used for receiving the tubes embracing the casing in areas between boxes; perforated holes are directed towards inner casing; wall of boxes directed towards housing are perforated; each box is provided with branch pipe for delivery of cooling agent to its cavity. EFFECT: enhanced efficiency. 2 dwg
Title | Year | Author | Number |
---|---|---|---|
AIR-GAS BURNER | 1997 |
|
RU2146788C1 |
METHOD AND DEVICE FOR PROCESSING HYDROCARBON RAW MATERIALS | 1995 |
|
RU2132956C1 |
TURBO-MACHINE STAGE | 1998 |
|
RU2148732C1 |
AIRCRAFT GAS-TURBINE ENGINE AXIAL-FLOW MULTI-STAGE COMPRESSOR | 2002 |
|
RU2212568C1 |
ANNULAR COMBUSTION CHAMBER | 1996 |
|
RU2161756C2 |
COMPRESSOR OF GAS-TURBINE ENGINE | 2000 |
|
RU2175409C1 |
IGNITER | 1994 |
|
RU2103610C1 |
INJECTION BURNER | 1994 |
|
RU2118753C1 |
HIGH-REVVING HIGH-TEMPERATURE STAGE OF HIGH-PRESSURE TURBINE | 1993 |
|
RU2081334C1 |
BURNER OF GAS-TURBINE ENGINE COMBUSTION CHAMBER | 1993 |
|
RU2107869C1 |
Authors
Dates
1999-07-20—Published
1995-11-22—Filed