RU2000113307A - COMPRESSOR OF A GAS TURBINE ENGINE - Google Patents

COMPRESSOR OF A GAS TURBINE ENGINE

Info

Publication number
RU2000113307A
RU2000113307A RU2000113307/06A RU2000113307A RU2000113307A RU 2000113307 A RU2000113307 A RU 2000113307A RU 2000113307/06 A RU2000113307/06 A RU 2000113307/06A RU 2000113307 A RU2000113307 A RU 2000113307A RU 2000113307 A RU2000113307 A RU 2000113307A
Authority
RU
Russia
Prior art keywords
gas turbine
turbine engine
compressor
bypass valves
bypass
Prior art date
Application number
RU2000113307/06A
Other languages
Russian (ru)
Other versions
RU2189499C2 (en
Inventor
Валерий Алексеевич Кузнецов
Анатолий Иванович Тункин
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 RU2000113307A priority Critical patent/RU2189499C2/en
Priority claimed from RU2000113307A external-priority patent/RU2189499C2/en
Publication of RU2000113307A publication Critical patent/RU2000113307A/en
Application granted granted Critical
Publication of RU2189499C2 publication Critical patent/RU2189499C2/en

Links

Claims (1)

Компрессор газотурбинного двигателя, содержащий статор с корпусом перепуска и внутренним корпусом, образующие между собой замкнутые полости, соединенные на входе с проточной частью компрессора, а на выходе - с клапанами перепуска, отличающийся тем, что клапаны перепуска установлены в одной радиальной плоскости и последовательно чередуются между собой в окружном направлении, при этом вторая по потоку воздуха кольцевая замкнутая полость сообщена с клапанами перепуска через замкнутые полости.A gas turbine engine compressor containing a stator with a bypass housing and an inner housing, forming closed cavities between themselves, connected at the inlet to the compressor flow part, and at the outlet to bypass valves, characterized in that the bypass valves are installed in one radial plane and alternately alternate between in the circumferential direction, while the second annular closed cavity is in communication with the bypass valves through the closed cavities.
RU2000113307A 2000-05-26 2000-05-26 Gas-turbine engine compressor RU2189499C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2000113307A RU2189499C2 (en) 2000-05-26 2000-05-26 Gas-turbine engine compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2000113307A RU2189499C2 (en) 2000-05-26 2000-05-26 Gas-turbine engine compressor

Publications (2)

Publication Number Publication Date
RU2000113307A true RU2000113307A (en) 2002-04-10
RU2189499C2 RU2189499C2 (en) 2002-09-20

Family

ID=20235239

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2000113307A RU2189499C2 (en) 2000-05-26 2000-05-26 Gas-turbine engine compressor

Country Status (1)

Country Link
RU (1) RU2189499C2 (en)

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