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RU2002116340A - TURBINE OF A GAS-TURBINE ENGINE - Google Patents

TURBINE OF A GAS-TURBINE ENGINE

Info

Publication number
RU2002116340A
RU2002116340A RU2002116340/06A RU2002116340A RU2002116340A RU 2002116340 A RU2002116340 A RU 2002116340A RU 2002116340/06 A RU2002116340/06 A RU 2002116340/06A RU 2002116340 A RU2002116340 A RU 2002116340A RU 2002116340 A RU2002116340 A RU 2002116340A
Authority
RU
Russia
Prior art keywords
turbine
gas
hub
engine
turbine engine
Prior art date
Application number
RU2002116340/06A
Other languages
Russian (ru)
Other versions
RU2226609C2 (en
Inventor
Сергей Иванович Фадеев
Валерий Алексеевич Кузнецов
Владимир Михайлович Язев
Original Assignee
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" filed Critical Открытое акционерное общество "Авиадвигатель"
Priority to RU2002116340/06A priority Critical patent/RU2226609C2/en
Publication of RU2002116340A publication Critical patent/RU2002116340A/en
Application granted granted Critical
Publication of RU2226609C2 publication Critical patent/RU2226609C2/en

Links

Landscapes

  • Turbine Rotor Nozzle Sealing (AREA)

Claims (1)

Турбина газотурбинного двигателя, включающая диск с установленным на нем дефлектором со ступицей и полотном, отличающаяся тем, что дефлектор установлен на диске с помощью болтов через осевые отверстия в ступице, между которыми выполнены осевые пазы, открытые с внутренней стороны ступицы, причем наружная стенка паза расположена на большем радиусе, чем отверстия, а отношение диаметра отверстия к радиальному расстоянию от оси отверстия до наружной стенки паза d/δ=0,-1,5.A turbine of a gas turbine engine, including a disk with a deflector installed on it with a hub and a blade, characterized in that the deflector is mounted on the disk with bolts through axial holes in the hub, between which axial grooves are made, open on the inside of the hub, and the outer wall of the groove is located over a larger radius than the holes, and the ratio of the diameter of the hole to the radial distance from the axis of the hole to the outer wall of the groove d / δ = 0, -1.5.
RU2002116340/06A 2002-06-17 2002-06-17 Turbine of gas-turbine engine RU2226609C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2002116340/06A RU2226609C2 (en) 2002-06-17 2002-06-17 Turbine of gas-turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2002116340/06A RU2226609C2 (en) 2002-06-17 2002-06-17 Turbine of gas-turbine engine

Publications (2)

Publication Number Publication Date
RU2002116340A true RU2002116340A (en) 2004-01-10
RU2226609C2 RU2226609C2 (en) 2004-04-10

Family

ID=32465173

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2002116340/06A RU2226609C2 (en) 2002-06-17 2002-06-17 Turbine of gas-turbine engine

Country Status (1)

Country Link
RU (1) RU2226609C2 (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2353777C1 (en) * 2007-08-29 2009-04-27 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Cooled turbine of gas-turbine engine
FR2931869B1 (en) * 2008-05-29 2014-12-12 Snecma ANNULAR BRACKET FOR FIXING A ROTOR OR STATOR ELEMENT
RU2378517C1 (en) * 2008-06-26 2010-01-10 Открытое акционерное общество "Авиадвигатель" Gas turbine rotor
FR2937371B1 (en) * 2008-10-20 2010-12-10 Snecma VENTILATION OF A HIGH-PRESSURE TURBINE IN A TURBOMACHINE
FR2938292B1 (en) * 2008-11-07 2010-12-24 Snecma ANNULAR FLANGE FOR FIXING A ROTOR OR STATOR ELEMENT IN A TURBOMACHINE
RU2470170C1 (en) * 2011-06-06 2012-12-20 Открытое акционерное общество "Авиадвигатель" Gas turbine engine rotor
FR3030614B1 (en) * 2014-12-17 2019-09-20 Safran Aircraft Engines TURBOMACHINE HIGH PRESSURE TURBINE ASSEMBLY

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4659289A (en) * 1984-07-23 1987-04-21 United Technologies Corporation Turbine side plate assembly
US4645424A (en) * 1984-07-23 1987-02-24 United Technologies Corporation Rotating seal for gas turbine engine
RU2042831C1 (en) * 1991-10-28 1995-08-27 Копейский машиностроительный завод Loading machine
RU2151882C1 (en) * 1998-08-03 2000-06-27 Открытое акционерное общество "Авиадвигатель" Turbine rotor part reconditioning method
FR2825748B1 (en) * 2001-06-07 2003-11-07 Snecma Moteurs TURBOMACHINE ROTOR ARRANGEMENT WITH TWO BLADE DISCS SEPARATED BY A SPACER

Also Published As

Publication number Publication date
RU2226609C2 (en) 2004-04-10

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Effective date: 20111220

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