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RU2002122564A - TURBINE OF A GAS-TURBINE ENGINE - Google Patents

TURBINE OF A GAS-TURBINE ENGINE

Info

Publication number
RU2002122564A
RU2002122564A RU2002122564/06A RU2002122564A RU2002122564A RU 2002122564 A RU2002122564 A RU 2002122564A RU 2002122564/06 A RU2002122564/06 A RU 2002122564/06A RU 2002122564 A RU2002122564 A RU 2002122564A RU 2002122564 A RU2002122564 A RU 2002122564A
Authority
RU
Russia
Prior art keywords
turbine
stage
disk
flange
shaft
Prior art date
Application number
RU2002122564/06A
Other languages
Russian (ru)
Other versions
RU2232901C2 (en
Inventor
Виталий Владимирович Иванов
Валерий Алексеевич Кузнецов
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 RU2002122564/06A priority Critical patent/RU2232901C2/en
Publication of RU2002122564A publication Critical patent/RU2002122564A/en
Application granted granted Critical
Publication of RU2232901C2 publication Critical patent/RU2232901C2/en

Links

Landscapes

  • Turbine Rotor Nozzle Sealing (AREA)

Claims (1)

Турбина газотурбинного двигателя с двухступенчатым ротором, диск первой ступени которого зафиксирован на радиальном фланце вала осевыми болтами, диск второй ступени в осевом направлении зафиксирован на валу гайкой, отличающаяся тем, что радиальный фланец вала размещен между дисками турбины, а диск второй ступени дополнительно зафиксирован в окружном направлении передним фланцем на радиальном фланце вала осевыми штифтами, причемA turbine of a gas turbine engine with a two-stage rotor, the first-stage disk of which is fixed on the radial shaft flange by axial bolts, the second-stage disk is axially fixed to the shaft by a nut, characterized in that the radial shaft flange is placed between the turbine disks, and the second-stage disk is additionally fixed in the circumferential the direction of the front flange on the radial flange of the shaft axial pins, and D/d=1,2-1,6 и d/d1=1,1-1,3,D / d = 1.2-1.6 and d / d 1 = 1.1-1.3, где D - диаметр расположения осевых болтов диска первой ступени;where D is the diameter of the arrangement of the axial bolts of the disk of the first stage; d - диаметр расположения осевых штифтов диска второй ступени;d is the diameter of the location of the axial pins of the disk of the second stage; d1 - диаметр вала турбины перед радиальным фланцем вала.d 1 - the diameter of the turbine shaft in front of the radial shaft flange.
RU2002122564/06A 2002-08-20 2002-08-20 Turbine of gas-turbine engine RU2232901C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2002122564/06A RU2232901C2 (en) 2002-08-20 2002-08-20 Turbine of gas-turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2002122564/06A RU2232901C2 (en) 2002-08-20 2002-08-20 Turbine of gas-turbine engine

Publications (2)

Publication Number Publication Date
RU2002122564A true RU2002122564A (en) 2004-02-27
RU2232901C2 RU2232901C2 (en) 2004-07-20

Family

ID=33412835

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2002122564/06A RU2232901C2 (en) 2002-08-20 2002-08-20 Turbine of gas-turbine engine

Country Status (1)

Country Link
RU (1) RU2232901C2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116025433A (en) * 2022-10-28 2023-04-28 中国航发湖南动力机械研究所 A turbine disk flange connection structure and aero-engine

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2369746C1 (en) * 2008-01-24 2009-10-10 Открытое акционерное общество "Авиадвигатель" Gas turbine engine rotor
RU2375587C1 (en) * 2008-04-28 2009-12-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Turbomachine rotor
RU2453709C1 (en) * 2010-12-23 2012-06-20 Открытое акционерное общество "Авиадвигатель" Gas turbine engine turbine rotor

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3376443D1 (en) * 1982-05-11 1988-06-01 Kuehnle Kopp Kausch Ag Steam turbine
FR2607866B1 (en) * 1986-12-03 1991-04-12 Snecma FIXING AXES OF TURBOMACHINE ROTORS, MOUNTING METHOD AND ROTORS THUS MOUNTED
RU2130124C1 (en) * 1996-05-28 1999-05-10 Акционерное общество "Авиадвигатель" Multistage turbine rotor
RU2167309C2 (en) * 1999-05-25 2001-05-20 Открытое акционерное общество "Авиадвигатель" Single-shaft gas-turbine unit with multistage turbine
RU2193091C2 (en) * 2000-02-16 2002-11-20 Открытое акционерное общество "Авиадвигатель" High-temperature turbine of gas turbine engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116025433A (en) * 2022-10-28 2023-04-28 中国航发湖南动力机械研究所 A turbine disk flange connection structure and aero-engine

Also Published As

Publication number Publication date
RU2232901C2 (en) 2004-07-20

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Legal Events

Date Code Title Description
QB4A Licence on use of patent

Effective date: 20101007

QZ41 Official registration of changes to a registered agreement (patent)

Free format text: LICENCE FORMERLY AGREED ON 20101007

Effective date: 20110826

PD4A Correction of name of patent owner