SU1590681A1 - Axial-flow compressor blade - Google Patents

Axial-flow compressor blade Download PDF

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Publication number
SU1590681A1
SU1590681A1 SU874325693A SU4325693A SU1590681A1 SU 1590681 A1 SU1590681 A1 SU 1590681A1 SU 874325693 A SU874325693 A SU 874325693A SU 4325693 A SU4325693 A SU 4325693A SU 1590681 A1 SU1590681 A1 SU 1590681A1
Authority
SU
USSR - Soviet Union
Prior art keywords
feather
plates
axial
blade
compressor blade
Prior art date
Application number
SU874325693A
Other languages
Russian (ru)
Inventor
Евгений Сергеевич Метелкин
Григорий Геннадиевич Белоусов
Original Assignee
Московский Институт Инженеров Гражданской Авиации
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Application filed by Московский Институт Инженеров Гражданской Авиации filed Critical Московский Институт Инженеров Гражданской Авиации
Priority to SU874325693A priority Critical patent/SU1590681A1/en
Application granted granted Critical
Publication of SU1590681A1 publication Critical patent/SU1590681A1/en

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Abstract

Изобретение позвол ет повысить надежность конструкции путем установки упругих демпфирующих пластин 2 в зоне максимального перемещени  пера при колебании лопатки. Пластины 2 выполнены упругими, изогнуты по профилю пера 1 и закреплены на пере при помощи заклепок 6, установленных в зоне узловых линий колебани  лопаток. 5 ил.The invention makes it possible to increase the reliability of the structure by installing elastic damping plates 2 in the zone of maximum movement of the pen when the blade is oscillating. The plates 2 are made resilient, bent along the profile of the feather 1 and fixed to the feather by means of rivets 6 installed in the zone of the nodal lines of oscillation of the blades. 5 il.

Description

Фиг.11

Фиг.ЗFig.Z

Фиг. 4FIG. four

фиг. 5FIG. five

Claims (1)

Формула изобретенияClaim Лопатка осевого компрессора, содержащая перо и демпфируемые пластины, изогнутые по профилю пера, заг крепленные на нем со стороны спинки и корыта, отличающаяся тем, что, с целью повышения надежности конструкции, пластины выполнены упругими, закреплены на пере в зонах максимального перемещения пера . при колебании лопатки при помощи заклепок, установленных в выполненных в пере и пластинах соосных сквозных отверстиях, при этом отверстия в пере выполнены в зоне узловых линий колебания лопатки.An axial compressor blade containing a feather and damped plates curved along the profile of the feather, fastened on it from the back and trough, characterized in that, in order to increase the reliability of the structure, the plates are made elastic, fixed on the feather in the areas of maximum movement of the feather. when the blade is vibrated with rivets installed in the coaxial through holes made in the feather and plates, the holes in the feather are made in the zone of the blade vibration nodal lines. Фиг.1Figure 1 Фиг.ЗFig.Z
SU874325693A 1987-11-11 1987-11-11 Axial-flow compressor blade SU1590681A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU874325693A SU1590681A1 (en) 1987-11-11 1987-11-11 Axial-flow compressor blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU874325693A SU1590681A1 (en) 1987-11-11 1987-11-11 Axial-flow compressor blade

Publications (1)

Publication Number Publication Date
SU1590681A1 true SU1590681A1 (en) 1990-09-07

Family

ID=21335271

Family Applications (1)

Application Number Title Priority Date Filing Date
SU874325693A SU1590681A1 (en) 1987-11-11 1987-11-11 Axial-flow compressor blade

Country Status (1)

Country Link
SU (1) SU1590681A1 (en)

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Патент US № 4118147, кл. F 01 D 5/16, опублик. 1978. .(54) ЛОПАТКА ОСЕВОГО КОМПРЕССОРА *

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