FIELD: pumps.
SUBSTANCE: invention relates to stepped vortex pump used in oil wells. Pump includes inlet housing in contact with pumped liquid and discharge housing connected to pump housing and several adjacent pump stages (24). Each stage (24) has stator (240), first diffuser (250), second diffuser (250) and disk rotor (260) with central hole (261) and rim (262) with blades (263). Stator (240), diffusers (250) and rotor (260) contain shaft, which is connected to hole (261) of rotor (260) and engine, and at least two inlets (E1, E2) of stage are formed. Each rotor (260) includes at least one through hole (264) along axial direction between hole (261) and rim (262). Each inlet (E1, E2) is connected by means of corresponding annular channel (C1, C2) with corresponding outlet (S1, S2) of the stage. Outlets of previous stage (24) are connected to the appropriate inlets of the next stages. Each diffuser (250) has a disc shape with front surface (253) and rear surface (254) and central opening (251) and rigidly connected to front annular gasket with outer surface protruding beyond surface (253) of diffuser (250) and in contact with rear side of previous adjacent rotor (260) and subsequent annular gasket (72) with outer surface protruding beyond surface (254) of diffuser (250) and in contact with front side of next adjacent rotor (260). Hole (251) of each diffuser (250) is tightly connected to bushing (82), having central hole (823), front and rear sides with annular grooves. Front gasket is tightly connected with front groove, and rear gasket (72) is with rear groove.
EFFECT: invention is aimed at elimination of excessive load on rotors.
1 cl, 10 dwg
Title | Year | Author | Number |
---|---|---|---|
CONTINUOUS ACTION VORTEX PUMP | 2014 |
|
RU2659692C2 |
ROTATION-PREVENTING SPACER WITH TRANSVERSE KEYS | 2019 |
|
RU2773854C2 |
IMPROVED METHOD OF TURBINE COMPRESSOR CHARACTERISTICS | 2017 |
|
RU2741172C2 |
SURGE IN THE GAS COMPRESSOR PREDICTING METHOD | 2016 |
|
RU2678155C1 |
TURBO-MACHINE COMPONENT WITH INTERNAL COOLING | 2018 |
|
RU2737270C1 |
FLANGED COMPONENT FOR GAS TURBINE ENGINE | 2017 |
|
RU2742013C2 |
HEAT-RADIATING PLANT AND HEAT GENERATOR | 2009 |
|
RU2413905C2 |
TAPERED GAS TURBINE ENGINE LIQUID GALLERY | 2014 |
|
RU2664904C2 |
FUEL INJECTOR WITH CENTER BODY ASSEMBLY | 2019 |
|
RU2790900C2 |
GAS TURBINE ENGINE COMPRESSOR ROTOR ASSEMBLY WITH BALANCING SYSTEM | 2013 |
|
RU2660981C2 |
Authors
Dates
2019-12-11—Published
2016-01-26—Filed