FIELD: engines and pumps.
SUBSTANCE: invention relates to engine building. Aircraft turbojet engine low-pressure compressor rotor shaft garter contact sealing is installed between oil cavity and front support breathing cavity. Garter seal includes contact bushing with movable abuting to garter sealing rings contact surfaces, resilient-movably installed in roller bearing housing. Contact bushing consists of inner and outer rings. Outer ring is made with internal spiral fins. Garter consists of three multi-section rings. Its inner sealing and radially embracing outer rings are installed in garter on front side. Third ring is made rear and adjoins first two with side edge. Each of garter rings is made of local sections assembled with angular frequency of γs.b.u.=(0.47÷0.79) [unit/rad]. Back ring is made with radial height corresponding to total radial height Σh of garter internal sealing and external rings. Garter rings are equipped with discharge air channels. Garter external and rear rings outer surfaces are equipped with annular slot for spring rings tightening section. From axial displacement garter is elastically fixed by thrust and retaining rings. For this purpose in each rear ring section at least two blind holes are made, in which compression springs are installed resting against stop ring. Against displacement along circumference each section of external and rear rings is facing towards locking elements. Each section of inner ring is shifted in garter relative to locking element axial plane of symmetry by half of section arc length and equipped with in middle part with prismatic recess to fixing by locking element.
EFFECT: group of inventions technical result consists in twofold increasing of compressor service life and duration of engine interrepair operation by 18-20 % due to reduced wear of AC TJE LPC support elements.
14 cl, 2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| TURBOJET ENGINE ROTOR SHAFT SUPPORT (VERSIONS), TURBOJET ENGINE ROTOR SHAFT SUPPORT GARTER SEAL, TURBOJET ENGINE ROTOR SHAFT SUPPORT SEALING GARTER ASSEMBLY, TURBOJET ENGINE ROTOR SHAFT SUPPORT GARTER SEAL RING SECTION | 2015 |
|
RU2603389C1 |
| TURBOJET ENGINE ROTOR SHAFT SUPPORT (VERSIONS), TURBOJET ENGINE ROTOR SHAFT SUPPORT BODY, JET TURBINE ENGINE ROTOR SHAFT SUPPORT ROLLER BEARING HOUSING, TURBOJET ENGINE ROTOR SHAFT SUPPORT SEALING STAGES | 2015 |
|
RU2603386C1 |
| ROTOR SHAFT BEARING OF LOW-PRESSURE COMPRESSOR OF TURBOJET ENGINE (VERSIONS), SEALING SPOOL OF ROTOR SHAFT BEARING, ROTOR SHAFT BEARING BLOCK, CONTACT HUB OF ROTOR SHAFT BRACELET SEALING, OIL-CONTROL RING OF ROTOR SHAFT | 2016 |
|
RU2614017C1 |
| ROTOR SHAFT BEARING OF LOW-PRESSURE COMPRESSOR OF TURBOJET ENGINE (VERSIONS), CYLINDER CONSTITUENT OF ROTOR SHAFT, EXTERNAL TIGHTENING COMPONENT OF ROTOR SHAFT | 2016 |
|
RU2614018C1 |
| GAS TURBINE ENGINE ROTOR SHAFT SUPPORT, GAS TURBINE ENGINE ROTOR SHAFT SUPPORT BODY (VERSIONS), GAS TURBINE ENGINE ROTOR SHAFT SUPPORT ROLLER BEARING HOUSING | 2015 |
|
RU2603375C1 |
| FIRST STAGE DISC OF TURBOJET ENGINE LOW-PRESSURE COMPRESSOR ROTOR SHAFT (VERSIONS) | 2015 |
|
RU2603217C1 |
| ROTOR SHAFT BEARING OF LOW-PRESSURE COMPRESSOR OF TURBOJET ENGINE (VERSIONS), CASING OF ROTOR SHAFT REAR BEARING, ROTOR SHAFT COMPONENT, POLYFUNCTIONAL EXTERNAL TIGHTENING COMPONENT OF ROTOR SHAFT, CONNECTION COMPONENT OF ROTOR SHAFT, CASING OF BEARING OF ROTOR SHAFT REAR BEARING | 2016 |
|
RU2614029C1 |
| SUPPORT OF SHAFT ROTOR OF LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE (VERSIONS), BODY OF SHAFT SUPPORT AND BODY OF BALL-BEARING ROTOR SHAFT SUPPORT | 2016 |
|
RU2614020C1 |
| GAS TURBINE ENGINE ROTOR SHAFT SUPPORT (VERSIONS), GAS TURBINE ENGINE ROTOR SHAFT SUPPORT UNIT, GAS TURBINE ENGINE ROTOR SHAFT SUPPORT RESILIENT RING, GAS TURBINE ENGINE ROTOR SHAFT TRUNNION END BUSHING | 2015 |
|
RU2603374C1 |
| LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE | 2016 |
|
RU2614709C1 |
