RU96102616A - GAS TURBINE ENGINE COMPRESSOR STATOR - Google Patents

GAS TURBINE ENGINE COMPRESSOR STATOR

Info

Publication number
RU96102616A
RU96102616A RU96102616/06A RU96102616A RU96102616A RU 96102616 A RU96102616 A RU 96102616A RU 96102616/06 A RU96102616/06 A RU 96102616/06A RU 96102616 A RU96102616 A RU 96102616A RU 96102616 A RU96102616 A RU 96102616A
Authority
RU
Russia
Prior art keywords
gas turbine
turbine engine
compressor stator
engine compressor
stator
Prior art date
Application number
RU96102616/06A
Other languages
Russian (ru)
Other versions
RU2121082C1 (en
Inventor
А.И. Тункин
Н.И. Рокка
В.А. Кузнецов
И.В. Максимов
Original Assignee
Акционерное общество "Авиадвигатель"
Filing date
Publication date
Application filed by Акционерное общество "Авиадвигатель" filed Critical Акционерное общество "Авиадвигатель"
Priority to RU96102616A priority Critical patent/RU2121082C1/en
Priority claimed from RU96102616A external-priority patent/RU2121082C1/en
Publication of RU96102616A publication Critical patent/RU96102616A/en
Application granted granted Critical
Publication of RU2121082C1 publication Critical patent/RU2121082C1/en

Links

Claims (1)

Статор компрессора газотурбинного двигателя с системой управления радиальными зазорами между статором и ротором, содержащий наружный корпус, соединенный с опорами ротора, и внутренний корпус, имеющий соединения со стороны передних ступеней компрессора с наружным корпусом, а со стороны задних ступеней - с наружным корпусом и через спрямляющий аппарат с закомпрессорным лабиринтом и опорой ротора, отличающийся тем, что по меньшей мере одно из соединений между корпусами выполнено упругим.The compressor stator of a gas turbine engine with a radial clearance control system between the stator and the rotor, comprising an outer casing connected to the rotor supports and an inner casing having connections from the front compressor stages to the outer casing, and from the rear stages, to the outer casing and through a straightening casing apparatus with a compressor labyrinth and a rotor support, characterized in that at least one of the joints between the bodies is made elastic.
RU96102616A 1996-02-13 1996-02-13 Stator of compressor of gas-turbine engine RU2121082C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU96102616A RU2121082C1 (en) 1996-02-13 1996-02-13 Stator of compressor of gas-turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU96102616A RU2121082C1 (en) 1996-02-13 1996-02-13 Stator of compressor of gas-turbine engine

Publications (2)

Publication Number Publication Date
RU96102616A true RU96102616A (en) 1998-04-27
RU2121082C1 RU2121082C1 (en) 1998-10-27

Family

ID=20176776

Family Applications (1)

Application Number Title Priority Date Filing Date
RU96102616A RU2121082C1 (en) 1996-02-13 1996-02-13 Stator of compressor of gas-turbine engine

Country Status (1)

Country Link
RU (1) RU2121082C1 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2463465C1 (en) * 2011-04-29 2012-10-10 Открытое акционерное общество "Авиадвигатель" Gas turbine engine
BR102012027097B1 (en) * 2011-11-23 2022-01-04 United Technologies Corporation GAS TURBINE ENGINE
RU2659841C1 (en) * 2017-09-21 2018-07-04 Акционерное общество "Научно-производственный центр газотурбостроения "Салют" (АО НПЦ газотурбостроения "Салют") Birotary compressor of gas turbine engine

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