RU99110967A - SINGLE GAS TURBINE INSTALLATION - Google Patents

SINGLE GAS TURBINE INSTALLATION

Info

Publication number
RU99110967A
RU99110967A RU99110967/06A RU99110967A RU99110967A RU 99110967 A RU99110967 A RU 99110967A RU 99110967/06 A RU99110967/06 A RU 99110967/06A RU 99110967 A RU99110967 A RU 99110967A RU 99110967 A RU99110967 A RU 99110967A
Authority
RU
Russia
Prior art keywords
rotor
disk
gas turbine
turbine installation
continuous
Prior art date
Application number
RU99110967/06A
Other languages
Russian (ru)
Other versions
RU2180043C2 (en
Inventor
Александр Александрович Иноземцев
Даниил Дмитриевич Сулимов
Валерий Алексеевич Кузнецов
Сергей Валентинович Торопчин
Original Assignee
Открытое акционерное общество "Авиадвигатель"
Filing date
Publication date
Application filed by Открытое акционерное общество "Авиадвигатель" filed Critical Открытое акционерное общество "Авиадвигатель"
Priority to RU99110967/06A priority Critical patent/RU2180043C2/en
Priority claimed from RU99110967/06A external-priority patent/RU2180043C2/en
Publication of RU99110967A publication Critical patent/RU99110967A/en
Application granted granted Critical
Publication of RU2180043C2 publication Critical patent/RU2180043C2/en

Links

Claims (1)

Одновальная газотурбинная установка, содержащая входное устройство, компрессор, камеру сгорания и многоступенчатую турбину, включающую консольный ротор с полым валом и последним по потоку газа сплошным диском, отличающаяся тем, что в роторе турбины перед сплошным диском выполнен по меньшей мере один диск с центральным отверстием, а также расположенные между ними промежуточные диски, причем сплошной диск ротора закреплен в центральной полости вала ротора через промежуточную шлицевую втулку стяжным болтом.A single-shaft gas turbine installation comprising an inlet device, a compressor, a combustion chamber and a multi-stage turbine including a cantilever rotor with a hollow shaft and the last continuous disk gas flow, characterized in that at least one disk with a central hole is made in the turbine rotor in front of the continuous disk, as well as intermediate disks located between them, and a continuous rotor disk is fixed in the central cavity of the rotor shaft through an intermediate spline sleeve with a coupling bolt.
RU99110967/06A 1999-05-25 1999-05-25 One-shaft gas-turbine plant RU2180043C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU99110967/06A RU2180043C2 (en) 1999-05-25 1999-05-25 One-shaft gas-turbine plant

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU99110967/06A RU2180043C2 (en) 1999-05-25 1999-05-25 One-shaft gas-turbine plant

Publications (2)

Publication Number Publication Date
RU99110967A true RU99110967A (en) 2001-03-20
RU2180043C2 RU2180043C2 (en) 2002-02-27

Family

ID=20220320

Family Applications (1)

Application Number Title Priority Date Filing Date
RU99110967/06A RU2180043C2 (en) 1999-05-25 1999-05-25 One-shaft gas-turbine plant

Country Status (1)

Country Link
RU (1) RU2180043C2 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1318760C (en) * 2002-03-13 2007-05-30 三洋电机株式会社 Multi-stage compressive rotary compressor and refrigerant return device
GB201309952D0 (en) * 2013-06-04 2013-07-17 Siemens Ag Shaft arrangement
US9453427B2 (en) 2013-10-30 2016-09-27 General Electric Company Systems and methods for purging an aft joint of a last stage wheel
RU2579526C2 (en) * 2014-07-02 2016-04-10 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Method of converting turbo shaft engine into ground-based gas-turbine plant

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