RU2000125037A - GAS TURBINE ENGINE COMPRESSOR STATOR - Google Patents

GAS TURBINE ENGINE COMPRESSOR STATOR

Info

Publication number
RU2000125037A
RU2000125037A RU2000125037/06A RU2000125037A RU2000125037A RU 2000125037 A RU2000125037 A RU 2000125037A RU 2000125037/06 A RU2000125037/06 A RU 2000125037/06A RU 2000125037 A RU2000125037 A RU 2000125037A RU 2000125037 A RU2000125037 A RU 2000125037A
Authority
RU
Russia
Prior art keywords
gas turbine
turbine engine
compressor stator
engine compressor
casing
Prior art date
Application number
RU2000125037/06A
Other languages
Russian (ru)
Other versions
RU2186257C2 (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 RU2000125037/06A priority Critical patent/RU2186257C2/en
Priority claimed from RU2000125037/06A external-priority patent/RU2186257C2/en
Application granted granted Critical
Publication of RU2186257C2 publication Critical patent/RU2186257C2/en
Publication of RU2000125037A publication Critical patent/RU2000125037A/en

Links

Claims (1)

Статор компрессора газотурбинного двигателя, включающий корпус компрессора и поворотные лопатки с наружными цапфами, отличающийся тем, что на внешней поверхности корпуса выполнено Г-образное кольцевое ребро, в цилиндрической части которого установлены цилиндрические втулки, в которых закреплены наружные цапфы лопаток, при этом l/h = 2,5 . . . 5, где l - длина пера поворотной лопатки, h - высота кольцевого Г-образного ребра.The compressor stator of a gas turbine engine, comprising a compressor casing and rotary blades with external pins, characterized in that on the outer surface of the casing a L-shaped annular rib is made, in the cylindrical part of which there are cylindrical bushings in which the outer pins of the blades are fixed, while l / h = 2.5. . . 5, where l is the length of the feather of the rotary blade, h is the height of the annular L-shaped rib.
RU2000125037/06A 2000-10-03 2000-10-03 Compressor stator of gas turbine engine RU2186257C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2000125037/06A RU2186257C2 (en) 2000-10-03 2000-10-03 Compressor stator of gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2000125037/06A RU2186257C2 (en) 2000-10-03 2000-10-03 Compressor stator of gas turbine engine

Publications (2)

Publication Number Publication Date
RU2186257C2 RU2186257C2 (en) 2002-07-27
RU2000125037A true RU2000125037A (en) 2002-09-10

Family

ID=20240636

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2000125037/06A RU2186257C2 (en) 2000-10-03 2000-10-03 Compressor stator of gas turbine engine

Country Status (1)

Country Link
RU (1) RU2186257C2 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2941018B1 (en) * 2009-01-09 2011-02-11 Snecma A VARIABLE CALIPER FOR A RECTIFIER STAGE, COMPRISING A NON-CIRCULAR INTERNAL PLATFORM
RU2600479C1 (en) * 2015-05-12 2016-10-20 Открытое акционерное общество "Авиадвигатель" High-pressure compressor of gas turbine engine

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