SU1073488A1 - Method of reducing unevenness of flow at outlet of turbomachine vane cascade - Google Patents

Method of reducing unevenness of flow at outlet of turbomachine vane cascade Download PDF

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Publication number
SU1073488A1
SU1073488A1 SU833532750A SU3532750A SU1073488A1 SU 1073488 A1 SU1073488 A1 SU 1073488A1 SU 833532750 A SU833532750 A SU 833532750A SU 3532750 A SU3532750 A SU 3532750A SU 1073488 A1 SU1073488 A1 SU 1073488A1
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SU
USSR - Soviet Union
Prior art keywords
flow
outlet
localization
turbomachine
reducing unevenness
Prior art date
Application number
SU833532750A
Other languages
Russian (ru)
Inventor
Владимир Николаевич Ершов
Василий Александрович Меньшиков
Иван Иванович Редин
Михаил Леонидович Угрюмов
Original Assignee
Харьковский Ордена Ленина Авиационный Институт Им.Жуковского
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Priority to SU833532750A priority Critical patent/SU1073488A1/en
Application granted granted Critical
Publication of SU1073488A1 publication Critical patent/SU1073488A1/en

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Abstract

СПОСОБ УМЕНЬШЕНИЯ НЕРАВНОМЕРНОСТИ ПОТОКА НА ВЫХОДЕ ИЗ ЛОПАТОЧНОЙ РЕШЕТКИ ТУРБОМАШИНЫ путем локализации входной неравномерности нотока и отбора пограничного сло  с ограничивающей торцевой гювер.чности , отличающийс  тем, что, с целью повышени  КПД турбомаишны, локализацию осуществл ют непрерывным перемещением входной части, по меньшей мере одной, ограничивающей поверхности вдоль фронта решетки в 1аправлении от стороны разрежени  к стороне давлени  межлопаточного канала.A method of reducing irregular stream OUTLET SCAPULA GRATING turbomachine by localization unevenness notok input and selection of the boundary layer from the confining end gyuver.chnosti, characterized in that, in order to increase efficiency turbomaishny, localization is carried out continuously by moving the inlet portion, at least one, the confining surface along the front of the grille in the direction from the vacuum side to the pressure side of the interscapular channel.

Description

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Claims (1)

СПОСОБ УМЕНЬШЕНИЯ НЕРАВНОМЕРНОСТИ ПОТОКА НА ВЫХОДЕ ИЗ ЛОПАТОЧНОЙ РЕШЕТКИ ТУРБОМАШИНЫ путем локализации входной неравномерности потока и отбора пограничного слоя с ограничивающей торцевой поверхности, отличающийся тем, что, с целью повышения КПД турбомашины, локализацию осуществляют непрерывным перемещением входной части, по меньшей мере одной, ограничивающей поверхности вдоль фронта решетки в направлении от стороны разрежения к стороне давления межлопаточного канала.METHOD FOR REDUCING FLOW UNEQUISITY AT THE EXIT OF A TURBO MACHINE BLADE LATTICE by localizing the input flow non-uniformity and selecting a boundary layer with a bounding end surface, characterized in that, in order to increase the turbomachine efficiency, localization is carried out by continuous movement of the inlet part, at least one limiting the front of the grating in the direction from the rarefaction side to the pressure side of the interscapular channel. SU .... 1073488 >SU .... 1073488>
SU833532750A 1983-01-06 1983-01-06 Method of reducing unevenness of flow at outlet of turbomachine vane cascade SU1073488A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU833532750A SU1073488A1 (en) 1983-01-06 1983-01-06 Method of reducing unevenness of flow at outlet of turbomachine vane cascade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU833532750A SU1073488A1 (en) 1983-01-06 1983-01-06 Method of reducing unevenness of flow at outlet of turbomachine vane cascade

Publications (1)

Publication Number Publication Date
SU1073488A1 true SU1073488A1 (en) 1984-02-15

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
SU833532750A SU1073488A1 (en) 1983-01-06 1983-01-06 Method of reducing unevenness of flow at outlet of turbomachine vane cascade

Country Status (1)

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SU (1) SU1073488A1 (en)

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
1. Aeronautical journal, may, 1973 p. 249-256. 2. Патент GB № 1119479 кл. FIT, опублик. 1966. *

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