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RU2003104040A - TURBINE OF A GAS-TURBINE ENGINE - Google Patents

TURBINE OF A GAS-TURBINE ENGINE Download PDF

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Publication number
RU2003104040A
RU2003104040A RU2003104040/06A RU2003104040A RU2003104040A RU 2003104040 A RU2003104040 A RU 2003104040A RU 2003104040/06 A RU2003104040/06 A RU 2003104040/06A RU 2003104040 A RU2003104040 A RU 2003104040A RU 2003104040 A RU2003104040 A RU 2003104040A
Authority
RU
Russia
Prior art keywords
nut
turbine
shank
radial
annular
Prior art date
Application number
RU2003104040/06A
Other languages
Russian (ru)
Inventor
Виталий Владимирович Иванов (RU)
Виталий Владимирович Иванов
Валерий Алексеевич Кузнецов (RU)
Валерий Алексеевич Кузнецов
Original Assignee
Открытое акционерное общество "Авиадвигатель" (RU)
Открытое акционерное общество "Авиадвигатель"
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Открытое акционерное общество "Авиадвигатель" (RU), Открытое акционерное общество "Авиадвигатель" filed Critical Открытое акционерное общество "Авиадвигатель" (RU)
Priority to RU2003104040/06A priority Critical patent/RU2003104040A/en
Publication of RU2003104040A publication Critical patent/RU2003104040A/en

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  • Turbine Rotor Nozzle Sealing (AREA)

Claims (1)

Турбина газотурбинного двигателя, включающая диск, закрепленный на валу гайкой и лабиринтной втулкой, установленной на внутренней поверхности гайки, отличающаяся тем, что гайка выполнена с утолщенным передним резьбовым выступом и удлиненным хвостовиком, радиальное кольцевое ребро которого зафиксировано с задним хвостовиком лабиринтной втулки, передний хвостовик которой установлен в осевом кольцевом выступе вала и закреплен в окружном направлении радиальными штифтами, в радиальном направлении зафиксированными кольцевым радиальным выступом, который расположен на внутренней поверхности удлиненного хвостовика гайки, причем между хвостовиком гайки и лабиринтной втулкой выполнена кольцевая замкнутая полость.A turbine of a gas turbine engine, including a disk fixed to the shaft by a nut and a labyrinth sleeve mounted on the inner surface of the nut, characterized in that the nut is made with a thickened front threaded protrusion and an elongated shank, the radial annular rib of which is fixed with the rear shank of the labyrinth sleeve, the front shank of which mounted in the axial annular protrusion of the shaft and secured in the circumferential direction by radial pins, in the radial direction fixed by an annular radial a protrusion, which is located on the inner surface of the elongated shank of the nut, and an annular closed cavity is made between the shank of the nut and the labyrinth sleeve.
RU2003104040/06A 2003-02-11 2003-02-11 TURBINE OF A GAS-TURBINE ENGINE RU2003104040A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2003104040/06A RU2003104040A (en) 2003-02-11 2003-02-11 TURBINE OF A GAS-TURBINE ENGINE

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2003104040/06A RU2003104040A (en) 2003-02-11 2003-02-11 TURBINE OF A GAS-TURBINE ENGINE

Publications (1)

Publication Number Publication Date
RU2003104040A true RU2003104040A (en) 2004-09-10

Family

ID=35635521

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2003104040/06A RU2003104040A (en) 2003-02-11 2003-02-11 TURBINE OF A GAS-TURBINE ENGINE

Country Status (1)

Country Link
RU (1) RU2003104040A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2484257C1 (en) * 2012-04-23 2013-06-10 Открытое акционерное общество "Авиадвигатель" Rotor of compressor of turbofan engine
RU2492328C2 (en) * 2008-04-24 2013-09-10 Снекма Rotor of gas turbine engine compressor, comprising facilities of centrifugal air intake and gas turbine engine
RU2500892C2 (en) * 2008-04-24 2013-12-10 Снекма Rotor of compressor of gas turbine engine and gas turbine engine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2492328C2 (en) * 2008-04-24 2013-09-10 Снекма Rotor of gas turbine engine compressor, comprising facilities of centrifugal air intake and gas turbine engine
RU2500892C2 (en) * 2008-04-24 2013-12-10 Снекма Rotor of compressor of gas turbine engine and gas turbine engine
US8894360B2 (en) 2008-04-24 2014-11-25 Snecma Turbomachine compressor rotor including centripetal air bleed means
RU2484257C1 (en) * 2012-04-23 2013-06-10 Открытое акционерное общество "Авиадвигатель" Rotor of compressor of turbofan engine

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Legal Events

Date Code Title Description
FA91 Application withdrawn (on applicant's request)

Effective date: 20050318