SU1503485A1 - METHOD OF DIAGNOSTICS OF SPRING MODES IN THE COMPRESSOR - Google Patents

METHOD OF DIAGNOSTICS OF SPRING MODES IN THE COMPRESSOR

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Publication number
SU1503485A1
SU1503485A1 SU4190769/06A SU4190769A SU1503485A1 SU 1503485 A1 SU1503485 A1 SU 1503485A1 SU 4190769/06 A SU4190769/06 A SU 4190769/06A SU 4190769 A SU4190769 A SU 4190769A SU 1503485 A1 SU1503485 A1 SU 1503485A1
Authority
SU
USSR - Soviet Union
Prior art keywords
compressor
dynamic deformations
blades
outlet
diagnostics
Prior art date
Application number
SU4190769/06A
Other languages
Russian (ru)
Inventor
В.П. Максимов
В.А. Карасев
А.Я. Родов
К.В. Каховский
Original Assignee
В.П. Максимов
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.)
Filing date
Publication date
Application filed by В.П. Максимов filed Critical В.П. Максимов
Priority to SU4190769/06A priority Critical patent/SU1503485A1/en
Application granted granted Critical
Publication of SU1503485A1 publication Critical patent/SU1503485A1/en

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Abstract

Способ диагностики срывных режимов в компрессоре, включающий измерение пульсаций полного давления воздуха на входе и выходе компрессора, отличающийся тем, что, с целью повышения информативности, дополнительно измеряют динамические деформации статорных лопаток всех ступеней компрессора, определяют в диапазоне частот вращающегося срыва автоспектры сигналов измеренных параметров и взаимные спектры сигналов пульсации давления на входе компрессора и динамических деформаций лопаток первой ступени компрессора, динамических деформаций лопаток соседних ступеней, а также динамических деформаций лопаток последней ступени компрессора и пульсации давления на выходе компрессора, определяют также функцию когерентности и по значению последней в пределах 0,8...1,0 определяют частоту вращающегося срыва и ступени со срывным течением.A method for diagnosing stall modes in a compressor, including the measurement of total air pressure pulsations at the compressor inlet and outlet, characterized in that, in order to increase the information content, dynamic deformations of stator vanes of all compressor stages are measured, the autospectra of the measured parameters and mutual spectra of pressure pulsation signals at the compressor inlet and dynamic deformations of the blades of the first compressor stage, dynamic deformations l The coils of adjacent stages, as well as dynamic deformations of the blades of the last compressor stage and pressure pulsation at the compressor outlet, determine also the coherence function and determine the frequency of the rotating stall and the step with a sluggish current by the value of the latter within 0.8 ... 1.0.

SU4190769/06A 1987-02-02 1987-02-02 METHOD OF DIAGNOSTICS OF SPRING MODES IN THE COMPRESSOR SU1503485A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU4190769/06A SU1503485A1 (en) 1987-02-02 1987-02-02 METHOD OF DIAGNOSTICS OF SPRING MODES IN THE COMPRESSOR

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU4190769/06A SU1503485A1 (en) 1987-02-02 1987-02-02 METHOD OF DIAGNOSTICS OF SPRING MODES IN THE COMPRESSOR

Publications (1)

Publication Number Publication Date
SU1503485A1 true SU1503485A1 (en) 2004-08-20

Family

ID=60519602

Family Applications (1)

Application Number Title Priority Date Filing Date
SU4190769/06A SU1503485A1 (en) 1987-02-02 1987-02-02 METHOD OF DIAGNOSTICS OF SPRING MODES IN THE COMPRESSOR

Country Status (1)

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SU (1) SU1503485A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2577921C2 (en) * 2010-07-08 2016-03-20 Снекма Method and device to detect rotary flow breakaway in compressor of gas turbine engine and gas turbine engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2577921C2 (en) * 2010-07-08 2016-03-20 Снекма Method and device to detect rotary flow breakaway in compressor of gas turbine engine and gas turbine engine

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