GAS-TURBINE ENGINE OIL SYSTEM WITH CONTINUOUS REDUNDANCY DEVICE Russian patent published in 2005 - IPC

Abstract RU 2244141 C2

FIELD: mechanical engineering; gas-turbine engines of helicopters.

SUBSTANCE: invention is aimed at creating recirculation oil systems in which reservoir oil is repeatedly used for lubrication and cooling of supports, and overfilling of supports in case of failure of main oil system is prevented. According to invention, oil system of gas-turbine engine with continuous redundancy device contains space of at least one support rotor accommodating main and additional nozzles, main and additional oil tanks breathers, shutoff valve with control and operating spaces and delivery and pump-out main lines. Main oil tank communicates with delivery main line with main nozzles, control space of shutoff valve and additional oil tank with bottom part and communicating with additional nozzles. Oil system includes reducer space. Space of one support is combined with space of reducer to form common space having bottom and central parts. Additional nozzles and additional oil tank are located in central part of common space. Additional oil tank communicates with main oil tank through jet. Shutoff valve is located in bottom part of additional oil tank and its operating space can communicate with additional oil tank and with central part of common space. System has second similar shutoff valve installed in common space under additional oil tank. Valve control space is connected with main oil tank delivery main line, and operating space is connected with bottom part of common space and pump-out main line, and it can communicate with central part of common space. Circulator with oil receiver is installed in common space to communicates its bottom part with additional nozzles. To lubricate second support in proposed oil system, space of second support communicates with common space by breathing main line, and additional nozzles arranged in said space communicate with bottom part of common space through ejector.

EFFECT: increased service line and improved reliability of oil system.

2 cl, 1 dwg

Similar patents RU2244141C2

Title Year Author Number
OIL SYSTEM OF HELICOPTER GEARBOX WITH REDUNDANCY OF LUBRICATION AND COOLING CIRCUITS 2017
  • Orekhov Yurij Vasilevich
  • Plushchevskij Aleksej Mikhajlovich
RU2652867C1
MACHINE LUBRICATION SYSTEM (VERSIONS) 2010
  • Zakota Anatolij Ivanovich
  • Klikoduev Nikolaj Grigor'Evich
  • Kucherenko Jurij Stefanovich
  • Mishchenko Anatolij Petrovich
  • Shcheglov Valerij Anatol'Evich
RU2454550C2
OIL LUBRICATING SYSTEM OF GAS-TURBINE ENGINE WITH OIL RESERVING DEVICE 1998
  • Osipov V.N.
  • Markin A.K.
RU2136931C1
OIL SYSTEM OF GAS-TURBINE ENGINE 2016
  • Golubov Aleksandr Nikolaevich
  • Semenov Vadim Georgievich
  • Fomin Vyacheslav Nikolaevich
RU2618996C1
OIL SYSTEM OF AIR GAS TURBINE ENGINE 2013
  • Golubov Aleksandr Nikolaevich
  • Semenov Vadim Georgievich
  • Fomin Vjacheslav Nikolaevich
RU2535796C1
AIRCRAFT GAS TURBINE ENGINE OIL SYSTEM 2014
  • Golubov Aleksandr Nikolaevich
  • Semenov Vadim Georgievich
  • Marchukov Evgenij Juvenalevich
RU2578784C1
OIL SYSTEM OF AN AIRCRAFT GAS TURBINE ENGINE 2021
  • Kuznetsov Igor Sergeevich
  • Fedorov Ivan Vasilevich
  • Fomin Vyacheslav Nikolaevich
RU2784589C1
OIL SYSTEM OF GAS-TURBINE ENGINE 2014
  • Golubov Aleksandr Nikolaevich
  • Semenov Vadim Georgievich
RU2539928C1
LUBRICATING SYSTEM OF GAS-TURBINE ENGINE 1995
  • Golubov A.N.
  • Ezhova N.P.
  • Zhibkov Ju.M.
  • Puzakova O.R.
  • Fomin V.N.
RU2117794C1
METHOD OF GREASING AND COOLING FRONT SUPPORT OF THE ROTOR OF THE GAS TURBINE ENGINE 2016
  • Tishin Aleksej Petrovich
  • Shekhovtseva Evgeniya Vladimirovna
RU2623854C1

RU 2 244 141 C2

Authors

Markin A.K.

Tishin A.P.

Dates

2005-01-10Published

2003-03-24Filed