LUBRICATING SYSTEM OF GAS-TURBINE ENGINE Russian patent published in 1998 - IPC

FIELD: gas-turbine engines. SUBSTANCE: during engine starting, delivery pump 7 takes oil from oil tank 8 and conveys it to inlet of heat-transfer section 6 that uses fuel of main combustion chamber. With afterburner operating, spring-loaded gate valve 24 shuts line 25 off section 6 of heat-transfer apparatus and conveys oil to line 26 and then through line 4 delivers it to injectors 3. Oil does not flow through path of heat-transfer section 5 using fuel of afterburner and, hence, fuel filling its hydraulic path does not coke. Hot gases penetrating into space 1 are mixed up with oil atomized by injectors 3. Oil jet dumped to inlet region of breathing line 9 scatters gas flow and gases start flowing at higher speed. Connection of channel 13 for oil discharge from breather 12 to inlet of dump pump 14 contributes to this process and also prevents closure of flow section for escape of breather gases into atmosphere. With afterburner turned on, its fuel flows over line 28 to control space 27, spring-loaded gate valve 26 shifts to the right, shuts line 26 off section 6, and connects the latter to line 25. Engine stopping ceases oil supply to space 1 and to control space 21 of two- position valve 19. The latter opens to provide for communication between lines 18 and 20, and breathing line 9. Oil is discharged through line 15 from hot space 1 of rotor mount to cold compensating space 17; during next starting of engine, it is conveyed by means of dump pump 16 to oil tank 8 to empty this space for admitting next portion of oil during next engine stopping. EFFECT: improved reliability due to eliminating overheating and coking of oil in engine mounts and breathing lines. 5 cl, 1 dwg