| 摘要 |
FIELD: gas-turbine engines. SUBSTANCE: gas-turbine engine support includes bearing whose inner race is mounted on rotor shaft forming oil passage between them. Inlet of this oil passage is connected via central radial holes with bath formed on inner surface of shaft and two outlets are connected with injector orifices for delivery of oil to both sides of cage. On both sides of cage, oil manifolds are formed before injector orifices. These manifolds are connected with oil bath means of additional oil supply holes. Oil passage under inner race of bearing is made in form of separate longitudinal axis of shaft at angle of 60 to 75 deg. Relationship of products of reduced flow coefficients to area of holes between additional and central radial oil supply holes is selected in the following interval: mu1F1/mu2F2=3 to 7 and mu3F3/mu2F2=2.0 to 4.0, where mu1, mu2 and mu3 are reduced flow coefficients of left-hand additional, central radial and right-hand additional oil supply holes, respectively; F1, F2 and F3 are areas of left-hand additional, central radial and right-hand additional oil supply holes, respectively. Hydraulic diameter of cross section of separate longitudinal groove oil passage is lesser than that of injector orifice. EFFECT: minimum losses of pressure of oil fed to injector orifices at optimal cooling of inner race of bearing; possibility of using bearings with standard inner races; avoidance of choking of injector orifices with coke particles which are likely to form in oil passage under bearing race in case of stoppage of engine. 3 cl, 3 dwg
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