Propagation of multiple short length-scale stall cells in an axial compressor rotor

M. Inoue, M. Kuroumaru, T. Tanino, Masato Furukawa

Research output: Chapter in Book/Report/Conference proceedingConference contribution

4 Citations (Scopus)

Abstract

Evolution and structure of multiple stall cells with short lengthscale in an axial compressor rotor have been investigated experimentally. In a low-speed research compressor rotor tested, a short lengthscale stall cell appeared at first, but did not grow rapidly in size unlike a so-called "spike-type stall inception" observed in many multi-stage compressors. Alternatively, the number of cells increased to a certain stable state (a mild stall state) under a fixed throttle condition. In the mild stall state the multiple stall cells, size of which was on the same order of the inception cell (a few blade spacings), were rotating at 72 % of rotor speed and at intervals of 4.8 blade spacings. With further throttling, a long length-scale wave appeared overlapping the multiple short length-scale waves, then developed to a deep stall state with a big cell. In order to capture the short length-scale cells in the mild stall state, a so-called 'double phase-locked averaging technique' has been developed, by which the flow field can be measured phase locked to both of the rotor and the stall cell rotation. Then, lime-dependent ensemble averages of the 3D velocity components upstream and downstream of the rotor have been obtained with a slanted hot-wire, and the pressure distributions on the casing wall with high response pressure transducers. By a physically plausible explanation for the experimental results, a model for the flow mechanism of the short length-scale stall cell has been presented. The distinctive feature of the stall cell structure is on the separation vortex bubble with a leg traveling ahead of the rotor, with changing the blade in turn on which the vortex leg stands.

Original languageEnglish
Title of host publicationAircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery
PublisherAmerican Society of Mechanical Engineers (ASME)
ISBN (Electronic)9780791878583
DOIs
Publication statusPublished - Jan 1 1999
EventASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1999 - Indianapolis, United States
Duration: Jun 7 1999Jun 10 1999

Publication series

NameProceedings of the ASME Turbo Expo
Volume1

Other

OtherASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1999
CountryUnited States
CityIndianapolis
Period6/7/996/10/99

Fingerprint

Compressors
Rotors
Turbomachine blades
Vortex flow
Pressure transducers
Lime
Pressure distribution
Flow fields
Wire

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Inoue, M., Kuroumaru, M., Tanino, T., & Furukawa, M. (1999). Propagation of multiple short length-scale stall cells in an axial compressor rotor. In Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery (Proceedings of the ASME Turbo Expo; Vol. 1). American Society of Mechanical Engineers (ASME). https://doi.org/10.1115/99-GT-097

Propagation of multiple short length-scale stall cells in an axial compressor rotor. / Inoue, M.; Kuroumaru, M.; Tanino, T.; Furukawa, Masato.

Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery. American Society of Mechanical Engineers (ASME), 1999. (Proceedings of the ASME Turbo Expo; Vol. 1).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Inoue, M, Kuroumaru, M, Tanino, T & Furukawa, M 1999, Propagation of multiple short length-scale stall cells in an axial compressor rotor. in Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery. Proceedings of the ASME Turbo Expo, vol. 1, American Society of Mechanical Engineers (ASME), ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1999, Indianapolis, United States, 6/7/99. https://doi.org/10.1115/99-GT-097
Inoue M, Kuroumaru M, Tanino T, Furukawa M. Propagation of multiple short length-scale stall cells in an axial compressor rotor. In Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery. American Society of Mechanical Engineers (ASME). 1999. (Proceedings of the ASME Turbo Expo). https://doi.org/10.1115/99-GT-097
Inoue, M. ; Kuroumaru, M. ; Tanino, T. ; Furukawa, Masato. / Propagation of multiple short length-scale stall cells in an axial compressor rotor. Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery. American Society of Mechanical Engineers (ASME), 1999. (Proceedings of the ASME Turbo Expo).
@inproceedings{64d1bf5668bd47d89790fcd85807bf6d,
title = "Propagation of multiple short length-scale stall cells in an axial compressor rotor",
abstract = "Evolution and structure of multiple stall cells with short lengthscale in an axial compressor rotor have been investigated experimentally. In a low-speed research compressor rotor tested, a short lengthscale stall cell appeared at first, but did not grow rapidly in size unlike a so-called {"}spike-type stall inception{"} observed in many multi-stage compressors. Alternatively, the number of cells increased to a certain stable state (a mild stall state) under a fixed throttle condition. In the mild stall state the multiple stall cells, size of which was on the same order of the inception cell (a few blade spacings), were rotating at 72 {\%} of rotor speed and at intervals of 4.8 blade spacings. With further throttling, a long length-scale wave appeared overlapping the multiple short length-scale waves, then developed to a deep stall state with a big cell. In order to capture the short length-scale cells in the mild stall state, a so-called 'double phase-locked averaging technique' has been developed, by which the flow field can be measured phase locked to both of the rotor and the stall cell rotation. Then, lime-dependent ensemble averages of the 3D velocity components upstream and downstream of the rotor have been obtained with a slanted hot-wire, and the pressure distributions on the casing wall with high response pressure transducers. By a physically plausible explanation for the experimental results, a model for the flow mechanism of the short length-scale stall cell has been presented. The distinctive feature of the stall cell structure is on the separation vortex bubble with a leg traveling ahead of the rotor, with changing the blade in turn on which the vortex leg stands.",
author = "M. Inoue and M. Kuroumaru and T. Tanino and Masato Furukawa",
year = "1999",
month = "1",
day = "1",
doi = "10.1115/99-GT-097",
language = "English",
series = "Proceedings of the ASME Turbo Expo",
publisher = "American Society of Mechanical Engineers (ASME)",
booktitle = "Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery",

}

TY - GEN

T1 - Propagation of multiple short length-scale stall cells in an axial compressor rotor

AU - Inoue, M.

AU - Kuroumaru, M.

AU - Tanino, T.

AU - Furukawa, Masato

PY - 1999/1/1

Y1 - 1999/1/1

N2 - Evolution and structure of multiple stall cells with short lengthscale in an axial compressor rotor have been investigated experimentally. In a low-speed research compressor rotor tested, a short lengthscale stall cell appeared at first, but did not grow rapidly in size unlike a so-called "spike-type stall inception" observed in many multi-stage compressors. Alternatively, the number of cells increased to a certain stable state (a mild stall state) under a fixed throttle condition. In the mild stall state the multiple stall cells, size of which was on the same order of the inception cell (a few blade spacings), were rotating at 72 % of rotor speed and at intervals of 4.8 blade spacings. With further throttling, a long length-scale wave appeared overlapping the multiple short length-scale waves, then developed to a deep stall state with a big cell. In order to capture the short length-scale cells in the mild stall state, a so-called 'double phase-locked averaging technique' has been developed, by which the flow field can be measured phase locked to both of the rotor and the stall cell rotation. Then, lime-dependent ensemble averages of the 3D velocity components upstream and downstream of the rotor have been obtained with a slanted hot-wire, and the pressure distributions on the casing wall with high response pressure transducers. By a physically plausible explanation for the experimental results, a model for the flow mechanism of the short length-scale stall cell has been presented. The distinctive feature of the stall cell structure is on the separation vortex bubble with a leg traveling ahead of the rotor, with changing the blade in turn on which the vortex leg stands.

AB - Evolution and structure of multiple stall cells with short lengthscale in an axial compressor rotor have been investigated experimentally. In a low-speed research compressor rotor tested, a short lengthscale stall cell appeared at first, but did not grow rapidly in size unlike a so-called "spike-type stall inception" observed in many multi-stage compressors. Alternatively, the number of cells increased to a certain stable state (a mild stall state) under a fixed throttle condition. In the mild stall state the multiple stall cells, size of which was on the same order of the inception cell (a few blade spacings), were rotating at 72 % of rotor speed and at intervals of 4.8 blade spacings. With further throttling, a long length-scale wave appeared overlapping the multiple short length-scale waves, then developed to a deep stall state with a big cell. In order to capture the short length-scale cells in the mild stall state, a so-called 'double phase-locked averaging technique' has been developed, by which the flow field can be measured phase locked to both of the rotor and the stall cell rotation. Then, lime-dependent ensemble averages of the 3D velocity components upstream and downstream of the rotor have been obtained with a slanted hot-wire, and the pressure distributions on the casing wall with high response pressure transducers. By a physically plausible explanation for the experimental results, a model for the flow mechanism of the short length-scale stall cell has been presented. The distinctive feature of the stall cell structure is on the separation vortex bubble with a leg traveling ahead of the rotor, with changing the blade in turn on which the vortex leg stands.

UR - http://www.scopus.com/inward/record.url?scp=84928578785&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84928578785&partnerID=8YFLogxK

U2 - 10.1115/99-GT-097

DO - 10.1115/99-GT-097

M3 - Conference contribution

AN - SCOPUS:84928578785

T3 - Proceedings of the ASME Turbo Expo

BT - Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery

PB - American Society of Mechanical Engineers (ASME)

ER -