RU2000103876A - HIGH TEMPERATURE TURBINE OF A GAS-TURBINE ENGINE - Google Patents

HIGH TEMPERATURE TURBINE OF A GAS-TURBINE ENGINE

Info

Publication number
RU2000103876A
RU2000103876A RU2000103876/06A RU2000103876A RU2000103876A RU 2000103876 A RU2000103876 A RU 2000103876A RU 2000103876/06 A RU2000103876/06 A RU 2000103876/06A RU 2000103876 A RU2000103876 A RU 2000103876A RU 2000103876 A RU2000103876 A RU 2000103876A
Authority
RU
Russia
Prior art keywords
turbine
gas
high temperature
turbine engine
rotor
Prior art date
Application number
RU2000103876/06A
Other languages
Russian (ru)
Other versions
RU2193091C2 (en
Inventor
Виталий Владимирович Иванов
Валерий Алексеевич Кузнецов
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 RU2000103876/06A priority Critical patent/RU2193091C2/en
Priority claimed from RU2000103876/06A external-priority patent/RU2193091C2/en
Publication of RU2000103876A publication Critical patent/RU2000103876A/en
Application granted granted Critical
Publication of RU2193091C2 publication Critical patent/RU2193091C2/en

Links

Claims (1)

Высокотемпературная турбина газотурбинного двигателя, содержащая ротор с промежуточным элементом между дисками ротора, отличающаяся тем, что промежуточный элемент выполнен из двух закрепленных на валу ротора с помощью фланца промежуточных дисков, установленных с натягом в осевом направлении, противоположном потоку газа в проточной части турбины, и выполненных с гибкими полотнами, ступицы которых соприкасаются по торцам.A high-temperature turbine of a gas turbine engine, comprising a rotor with an intermediate element between the rotor disks, characterized in that the intermediate element is made of two intermediate disks mounted on the rotor shaft using an intermediate flange mounted with an interference fit opposite the gas flow in the turbine flow section, and made with flexible canvases, the hubs of which touch at the ends.
RU2000103876/06A 2000-02-16 2000-02-16 High-temperature turbine of gas turbine engine RU2193091C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2000103876/06A RU2193091C2 (en) 2000-02-16 2000-02-16 High-temperature turbine of gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2000103876/06A RU2193091C2 (en) 2000-02-16 2000-02-16 High-temperature turbine of gas turbine engine

Publications (2)

Publication Number Publication Date
RU2000103876A true RU2000103876A (en) 2001-12-20
RU2193091C2 RU2193091C2 (en) 2002-11-20

Family

ID=20230738

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2000103876/06A RU2193091C2 (en) 2000-02-16 2000-02-16 High-temperature turbine of gas turbine engine

Country Status (1)

Country Link
RU (1) RU2193091C2 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2487333C1 (en) * 2012-04-12 2013-07-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Turbojet, method of turbojet testing (versions) and method of turbojet production method of turbojet industrial production, and method of turbojet operation

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