FIELD: mechanical engineering; turbojet engines.
SUBSTANCE: invention relates to compressors of double-flow turbojet engines with wide-chord blades. Proposed intermediate hosing of compressor of double-flow turbojet engine has load-bearing posts arranged between outer and inner loops whose output edges are connected by ring divider of engine loops. Said divider is made in form of ring fairing formed by two conical shells, with ring partition placed in its space. Ring partition is formed by conical surfaces equidistant to outer and inner surfaces of fairing and it forms a closed space with fairing. Closed space is divided by ring and radial partitions into separate spaces, each communicating with compressor space through at least one hole.
EFFECT: reduced amplitude of pressure fluctuations in gas-air duct of compressor of double-flow turbojet engine.
5 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| LOAD-BEARING SUPPORT OF TURBOJET ENGINE COMPRESSOR | 2004 |
|
RU2269677C1 |
| TURBOJET ENGINE AFTERBURNER COMBUSTION CHAMBER COMBUSTION ZONE STABILIZATION METHOD AND THE TURBOJET ENGINE AFTERBURNER COMBUSTION CHAMBER | 2017 |
|
RU2680781C1 |
| METHOD FOR PROTECTING GAS GENERATOR OF TURBOJET BY-PASS ENGINE FROM DUST PARTICLES | 2020 |
|
RU2752681C1 |
| DEVICE FOR AIR CLEANING FROM FOREIGN OBJECTS IN COMPRESSOR OF DOUBLE-FLOW TURBOJET ENGINE | 2019 |
|
RU2725034C1 |
| AXIAL-FLOW FAN OR COMPRESSOR IMPELLER AND FAN OF BYPASS FANJET INCORPORATING SAID IMPELLER | 2010 |
|
RU2460905C2 |
| TURBOJET ENGINE WITH CONTROLLABLE BY-PASS RATIO | 2002 |
|
RU2204045C1 |
| FAN | 1995 |
|
RU2133382C1 |
| AIR FLOW CONTROL SYSTEM FOR COOLING TURBINE OF BYPASS TURBOJET ENGINE | 2015 |
|
RU2614460C1 |
| ALL-ASPECT REACTION NOZZLE OF TURBOJET ENGINE | 2006 |
|
RU2312245C1 |
| DOUBLE-FLOW JET TURBINE ENGINE | 2017 |
|
RU2711895C2 |
