RU2002125947A - GAS TURBINE ENGINE COMPRESSOR STATOR - Google Patents

GAS TURBINE ENGINE COMPRESSOR STATOR

Info

Publication number
RU2002125947A
RU2002125947A RU2002125947/06A RU2002125947A RU2002125947A RU 2002125947 A RU2002125947 A RU 2002125947A RU 2002125947/06 A RU2002125947/06 A RU 2002125947/06A RU 2002125947 A RU2002125947 A RU 2002125947A RU 2002125947 A RU2002125947 A RU 2002125947A
Authority
RU
Russia
Prior art keywords
drive ring
gas turbine
turbine engine
engine compressor
compressor stator
Prior art date
Application number
RU2002125947/06A
Other languages
Russian (ru)
Other versions
RU2219378C1 (en
Inventor
Адольф Павлович Иванов
Василий Юрьевич Критский
Original Assignee
Адольф Павлович Иванов
Василий Юрьевич Критский
Filing date
Publication date
Application filed by Адольф Павлович Иванов, Василий Юрьевич Критский filed Critical Адольф Павлович Иванов
Priority to RU2002125947A priority Critical patent/RU2219378C1/en
Priority claimed from RU2002125947A external-priority patent/RU2219378C1/en
Application granted granted Critical
Publication of RU2219378C1 publication Critical patent/RU2219378C1/en
Publication of RU2002125947A publication Critical patent/RU2002125947A/en

Links

Claims (1)

Статор компрессора газотурбинного двигателя, содержащий корпус, поворотные лопатки, установленные в корпусе и связанные рычагами с кольцом привода через штыри, закрепленные на рычагах и антифрикционные втулки с заплечиками, закрепленными на кольце привода, отличающийся тем, что кольцо привода на наружной поверхности снабжено открытыми прямоугольными пазами с аварийным зазором, где установлены рычаги лопаток, а заплечики втулок размещены с внутренней поверхности кольца привода, при этом кольцо привода на внутренней поверхности снабжено двумя кольцевыми буртиками, в отверстиях которых установлены Z-образные стопоры втулок, расположенные напротив их заплечиков.A gas turbine engine compressor stator comprising a housing, rotary blades mounted in the housing and connected by levers to the drive ring through pins fixed to the levers and anti-friction bushings with shoulders fixed to the drive ring, characterized in that the drive ring on the outer surface is provided with open rectangular grooves with emergency clearance, where the blades are mounted, and the shoulders of the bushes are located on the inner surface of the drive ring, while the drive ring on the inner surface is provided with but with two annular flanges, in the openings of which Z-shaped stoppers of the bushings are located, located opposite their shoulders.
RU2002125947A 2002-10-01 2002-10-01 Compressor stator of gas-turbine engine RU2219378C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2002125947A RU2219378C1 (en) 2002-10-01 2002-10-01 Compressor stator of gas-turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2002125947A RU2219378C1 (en) 2002-10-01 2002-10-01 Compressor stator of gas-turbine engine

Publications (2)

Publication Number Publication Date
RU2219378C1 RU2219378C1 (en) 2003-12-20
RU2002125947A true RU2002125947A (en) 2004-04-10

Family

ID=32067096

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2002125947A RU2219378C1 (en) 2002-10-01 2002-10-01 Compressor stator of gas-turbine engine

Country Status (1)

Country Link
RU (1) RU2219378C1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007011990B4 (en) * 2007-03-09 2019-01-10 Tlt-Turbo Gmbh Device for the hydraulic adjustment of the blades of an impeller of an axial fan
FR3055374B1 (en) * 2016-08-23 2018-08-03 Safran Aircraft Engines INTERFACE PIECE FOR RECONDITIONING A CONTROL RING OF A MOTOR COMPRESSOR, AND ASSOCIATED RECONDITIONING METHOD

Similar Documents

Publication Publication Date Title
CN104956034B (en) The method for dismounting of turbine rotor, turbine and shrouding
MX168121B (en) IMPROVEMENTS IN COMPRESSOR DIAPHRAGM
BR8605750A (en) EXHAUST GAS POWERED TURBO
JP2007071205A (en) Sacrificial inner shroud liner for gas turbine engine
RU2008103002A (en) VARIABLE STEER TURBIN SCREW ENGINE
FR2419390A1 (en) ORIENTABLE VANE DISTRIBUTOR FOR AXIAL TURBINE OF GAS TURBINE ENGINE
KR920006615A (en) Structure of compressor case
DE502007003972D1 (en) BLADE ARRANGEMENT
CA2366758A1 (en) Stationary blade shroud of a gas turbine
CA2560003A1 (en) Seal for generators
KR890006962A (en) Variable capacity exhaust turbine supercharger
RU2002125947A (en) GAS TURBINE ENGINE COMPRESSOR STATOR
CN207454034U (en) A kind of synchronous ring structure for nozzle assembly
EA200601933A1 (en) SNOWLED PISTON ENGINE FOR INTERNAL COMBUSTION
RU2001109680A (en) TURBOCHARGER
KR102273470B1 (en) Turbo charger
FR2835573B1 (en) PUMP
BR112017021584A2 (en) gas turbine engine
RU2002101464A (en) ROTOR OF A MULTI-STAGE TURBINE OF A GAS-TURBINE ENGINE
CN205744255U (en) Multipurpose low pressure promotes turbine
RU2000125037A (en) GAS TURBINE ENGINE COMPRESSOR STATOR
RU2004136041A (en) GAS TURBINE ENGINE
RU94043412A (en) Turbodrill
RU2002111383A (en) Turbocharger diesel engine boost
RU2021124230A (en) Engine with internal aerodynamic thrust