RU96110803A - MULTI-STAGE TURBINE ROTOR - Google Patents

MULTI-STAGE TURBINE ROTOR

Info

Publication number
RU96110803A
RU96110803A RU96110803A RU96110803A RU96110803A RU 96110803 A RU96110803 A RU 96110803A RU 96110803 A RU96110803 A RU 96110803A RU 96110803 A RU96110803 A RU 96110803A RU 96110803 A RU96110803 A RU 96110803A
Authority
RU
Russia
Prior art keywords
stage turbine
turbine rotor
disks
shaft
rotor
Prior art date
Application number
RU96110803A
Other languages
Russian (ru)
Other versions
RU2130124C1 (en
Inventor
А.А. Иноземцев
Н.А. Иванов
Е.К. Павлов
В.М. Язев
В.А. Кузнецов
С.И. Фадеев
Original Assignee
Акционерное общество "Авиадвигатель"
Filing date
Publication date
Application filed by Акционерное общество "Авиадвигатель" filed Critical Акционерное общество "Авиадвигатель"
Priority to RU96110803A priority Critical patent/RU2130124C1/en
Priority claimed from RU96110803A external-priority patent/RU2130124C1/en
Publication of RU96110803A publication Critical patent/RU96110803A/en
Application granted granted Critical
Publication of RU2130124C1 publication Critical patent/RU2130124C1/en

Links

Claims (1)

Ротор многоступенчатой турбины, содержащий вал и диски с рабочими лопатками, в котором диск первой ступени закреплен непосредственно на валу, диски снабжены вынесенными фланцами крепления, отличающийся тем, что диски второй и последующих ступеней соединены с валом через дополнительные втулки, а фланцы крепления дисков выполнены со стороны выходных кромок рабочих лопаток.A rotor of a multi-stage turbine containing a shaft and disks with rotor blades, in which the first-stage disk is mounted directly on the shaft, the disks are provided with remote mounting flanges, characterized in that the disks of the second and subsequent stages are connected to the shaft through additional bushings, and the disk mounting flanges are made with side of the outlet edges of the blades.
RU96110803A 1996-05-28 1996-05-28 Multistage turbine rotor RU2130124C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU96110803A RU2130124C1 (en) 1996-05-28 1996-05-28 Multistage turbine rotor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU96110803A RU2130124C1 (en) 1996-05-28 1996-05-28 Multistage turbine rotor

Publications (2)

Publication Number Publication Date
RU96110803A true RU96110803A (en) 1998-08-20
RU2130124C1 RU2130124C1 (en) 1999-05-10

Family

ID=20181228

Family Applications (1)

Application Number Title Priority Date Filing Date
RU96110803A RU2130124C1 (en) 1996-05-28 1996-05-28 Multistage turbine rotor

Country Status (1)

Country Link
RU (1) RU2130124C1 (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2904048B1 (en) * 2006-07-19 2012-12-14 Snecma COMBUSTION CHAMBER WALL VENTILATION SYSTEM IN TURBOMACHINE
FR2904037B1 (en) * 2006-07-19 2010-11-12 Snecma VENTILATION OF A DOWNWARD CAVITY OF CENTRIFUGAL COMPRESSOR WHEEL
FR2904047B1 (en) * 2006-07-19 2013-03-01 Snecma COMBUSTION CHAMBER WALL VENTILATION SYSTEM
RU2532390C1 (en) * 2013-09-10 2014-11-10 Открытое акционерное общество "Авиадвигатель" High-pressure turbine rotor
RU2614018C1 (en) * 2016-03-22 2017-03-22 Публичное Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Пао "Умпо") Rotor shaft bearing of low-pressure compressor of turbojet engine (versions), cylinder constituent of rotor shaft, external tightening component of rotor shaft
RU2661566C2 (en) * 2016-12-28 2018-07-17 Акционерное общество "ОДК-Авиадвигатель" Multistage turbine rotor
US11629596B1 (en) 2021-10-08 2023-04-18 Pratt & Whitney Canada Corp. Rotor assembly for a gas turbine engine and method for assembling same

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