FIELD: machine building.
SUBSTANCE: invention relates to gas turbine engines of aircraft and ground applications, in particular to rotors of compressors and turbines. High-pressure rotor support of gas turbine engine, comprising radial thrust bearing, comprising outer and inner rings with smooth running tracks, oil supply and discharge systems, wherein in each possible contact area of balls and races under axial load on the latter there is at least one radial oil-conducting groove.
EFFECT: technical result of invention is higher reliability of high-pressure rotor support by reducing effect of oil wedge parameters on balls of its bearing and, as a result, reduced temperature gradient and reduced possibility of slippage.
1 cl, 2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| GAS TURBINE ENGINE INTER-ROTOR SUPPORT | 2015 |
|
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| COMBINED BEARING | 2017 |
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| GAS TURBINE ENGINE ROTOR SUPPORT | 2019 |
|
RU2730557C1 |
