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RU2003134024A - GAS-TURBINE ENGINE TURBINE NOZZLE DEVICE - Google Patents

GAS-TURBINE ENGINE TURBINE NOZZLE DEVICE Download PDF

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Publication number
RU2003134024A
RU2003134024A RU2003134024/06A RU2003134024A RU2003134024A RU 2003134024 A RU2003134024 A RU 2003134024A RU 2003134024/06 A RU2003134024/06 A RU 2003134024/06A RU 2003134024 A RU2003134024 A RU 2003134024A RU 2003134024 A RU2003134024 A RU 2003134024A
Authority
RU
Russia
Prior art keywords
inner ring
annular
nozzle
turbine
gas
Prior art date
Application number
RU2003134024/06A
Other languages
Russian (ru)
Other versions
RU2260700C2 (en
Inventor
Владимир Константинович Сычев (RU)
Владимир Константинович Сычев
Владимир Михайлович Язев (RU)
Владимир Михайлович Язев
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 RU2003134024/06A priority Critical patent/RU2260700C2/en
Publication of RU2003134024A publication Critical patent/RU2003134024A/en
Application granted granted Critical
Publication of RU2260700C2 publication Critical patent/RU2260700C2/en

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  • Turbine Rotor Nozzle Sealing (AREA)

Claims (2)

1. Сопловой аппарат турбины газотурбинного двигателя, содержащий сопловые лопатки с цапфами и кольцевыми выступами, на внутренних полках которых зафиксировано внутреннее кольцо с кольцевой канавкой, в которой установлен кольцевой выступ лопатки, отличающийся тем, что один из фланцев внутреннего кольца снабжен вынесенным в осевом направлении кольцевым буртом с радиальным пазом, в котором размещена цапфа сопловой лопатки, a L1-L2&γτ; 0,1. A nozzle apparatus of a turbine of a gas turbine engine, comprising nozzle vanes with pins and annular protrusions, on the inner shelves of which an inner ring with an annular groove is fixed, in which an annular protrusion of the vanes is installed, characterized in that one of the flanges of the inner ring is provided with an axially extended annular a shoulder with a radial groove in which the pin of the nozzle blade is located, a L 1 -L 2 &γτ; 0 где L1 - расстояние от оси болта крепежного фланца внутреннего кольца до внутренней поверхности кольцевого выступа сопловой лопатки;where L 1 is the distance from the axis of the bolt of the mounting flange of the inner ring to the inner surface of the annular protrusion of the nozzle vanes; L2 - расстояние от оси болта крепежного фланца внутреннего кольца до наружной обрабатываемой поверхности цапфы сопловой лопатки.L 2 is the distance from the axis of the bolt of the mounting flange of the inner ring to the outer machined surface of the spigot of the nozzle blade. 2. Сопловой аппарат по п.1, отличающийся тем, что поверхность дна радиального паза кольцевого бурта выполнена параллельной плоскости крепления крепежного фланца внутреннего кольца.2. The nozzle apparatus according to claim 1, characterized in that the bottom surface of the radial groove of the annular shoulder is made parallel to the plane of attachment of the mounting flange of the inner ring.
RU2003134024/06A 2003-11-24 2003-11-24 Turbine nozzle box of gas-turbine engine RU2260700C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2003134024/06A RU2260700C2 (en) 2003-11-24 2003-11-24 Turbine nozzle box of gas-turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2003134024/06A RU2260700C2 (en) 2003-11-24 2003-11-24 Turbine nozzle box of gas-turbine engine

Publications (2)

Publication Number Publication Date
RU2003134024A true RU2003134024A (en) 2005-05-20
RU2260700C2 RU2260700C2 (en) 2005-09-20

Family

ID=35820073

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2003134024/06A RU2260700C2 (en) 2003-11-24 2003-11-24 Turbine nozzle box of gas-turbine engine

Country Status (1)

Country Link
RU (1) RU2260700C2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113811669A (en) * 2019-05-21 2021-12-17 赛峰航空发动机公司 Removable pins on distributors of turbomachinery

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2908153B1 (en) * 2006-11-07 2011-05-13 Snecma DEVICE FOR HITCHING A DISTRIBUTOR (8) OF A TURBINE, TURBINE COMPRISING THEM, AND AN AIRCRAFT ENGINE WHICH IS EQUIPPED
RU2348816C1 (en) * 2007-08-01 2009-03-10 Открытое акционарное общество "Силовые машины-ЗТЛ, ЛМЗ, Электросила, Энергомашэкспорт" (ОАО "Силовые машины") Gas turbine stator with attached combustion chamber
FR2935429B1 (en) * 2008-08-26 2011-11-25 Snecma FIXED BLADE OF TURBOMACHINE WITH REDUCED MASS AND TURBOMACHINE COMPRISING AT LEAST ONE SUCH FIXED AUBAGE

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4011718A (en) * 1975-08-01 1977-03-15 United Technologies Corporation Gas turbine construction
US4194869A (en) * 1978-06-29 1980-03-25 United Technologies Corporation Stator vane cluster
DE3003470C2 (en) * 1980-01-31 1982-02-25 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Turbine guide vane suspension for gas turbine jet engines
US4655683A (en) * 1984-12-24 1987-04-07 United Technologies Corporation Stator seal land structure
RU2038487C1 (en) * 1992-06-15 1995-06-27 Акционерное общество открытого типа "Авиадвигатель" Stator for multi-stage turbine
US5289677A (en) * 1992-12-16 1994-03-01 United Technologies Corporation Combined support and seal ring for a combustor
RU2205276C1 (en) * 2001-12-24 2003-05-27 Федеральное государственное унитарное предприятие "Московское машиностроительное производственное предприятие "Салют" Turbomachine stator

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113811669A (en) * 2019-05-21 2021-12-17 赛峰航空发动机公司 Removable pins on distributors of turbomachinery

Also Published As

Publication number Publication date
RU2260700C2 (en) 2005-09-20

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Effective date: 20101007

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Free format text: LICENCE FORMERLY AGREED ON 20101007

Effective date: 20110826

PD4A Correction of name of patent owner