RU2000123998A - GAS TURBINE ENGINE COMPRESSOR ROTOR - Google Patents

GAS TURBINE ENGINE COMPRESSOR ROTOR

Info

Publication number
RU2000123998A
RU2000123998A RU2000123998/06A RU2000123998A RU2000123998A RU 2000123998 A RU2000123998 A RU 2000123998A RU 2000123998/06 A RU2000123998/06 A RU 2000123998/06A RU 2000123998 A RU2000123998 A RU 2000123998A RU 2000123998 A RU2000123998 A RU 2000123998A
Authority
RU
Russia
Prior art keywords
gas turbine
turbine engine
compressor rotor
engine compressor
disk
Prior art date
Application number
RU2000123998/06A
Other languages
Russian (ru)
Other versions
RU2186259C2 (en
Inventor
Анатолий Иванович Тункин
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 RU2000123998/06A priority Critical patent/RU2186259C2/en
Priority claimed from RU2000123998/06A external-priority patent/RU2186259C2/en
Application granted granted Critical
Publication of RU2186259C2 publication Critical patent/RU2186259C2/en
Publication of RU2000123998A publication Critical patent/RU2000123998A/en

Links

Claims (1)

Ротор компрессора газотурбинного двигателя, включающий вал, рабочие диски и закомпрессорный лабиринт, закрепленный на диске последней ступени байонетным соединением, отличающийся тем, что полотна дисков первой и последней ступеней выполнены утолщенными в осевом направлении, при этом отношение высоты к толщине полотна эакомпрессорного лабиринта находится в интервале 10-50.The compressor rotor of a gas turbine engine, including a shaft, working disks and a compressor labyrinth, mounted on a disk of the last stage with a bayonet connection, characterized in that the disk webs of the first and last stages are made axially thickened, while the ratio of height to thickness of the ecompressor labyrinth web is in the range 10-50.
RU2000123998/06A 2000-09-19 2000-09-19 Rotor of gas turbine engine compressor RU2186259C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2000123998/06A RU2186259C2 (en) 2000-09-19 2000-09-19 Rotor of gas turbine engine compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2000123998/06A RU2186259C2 (en) 2000-09-19 2000-09-19 Rotor of gas turbine engine compressor

Publications (2)

Publication Number Publication Date
RU2186259C2 RU2186259C2 (en) 2002-07-27
RU2000123998A true RU2000123998A (en) 2002-09-27

Family

ID=20240219

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2000123998/06A RU2186259C2 (en) 2000-09-19 2000-09-19 Rotor of gas turbine engine compressor

Country Status (1)

Country Link
RU (1) RU2186259C2 (en)

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