Design principles and aerodynamics of low reynolds number multi-stage microturbomachinery

Changgu Lee; Selin Arslan; Luc G. Fréchette

doi:10.1115/IMECE2004-60703

Design principles and aerodynamics of low reynolds number multi-stage microturbomachinery

Changgu Lee
, Selin Arslan
, Luc G. Fréchette

Columbia University
Université de Sherbrooke

Research output: Contribution to journal › Conference article › peer-review

3 Scopus citations

Abstract

In this paper, the design process for multi-stage micro scale turbomachinery will be presented, along with CFD predictions of the key aerodynamic performance parameters required in this design process. This work focuses on the unique and unexplored design space defined by the small scale and planar geometries characteristic of MEMS turbopumps, compressors, gas turbines, steam turbines, or other turbomachinery-based microsystems. Correlations are proposed for the loss coefficient, based on laminar flow theory. A critical Reynolds number is also identified (Re _crit=200-300), below which adjacent boundary layers merge, inducing a sharp increase in loss and deviation. This imposes practical limits on the miniaturization of such microturbomachinery.

Original language	English
Article number	IMECE2004-60703
Pages (from-to)	325-331
Number of pages	7
Journal	American Society of Mechanical Engineers, Fluids Engineering Division (Publication) FED
Volume	260
DOIs	https://doi.org/10.1115/IMECE2004-60703
State	Published - 2004
Externally published	Yes
Event	2004 ASME International Mechanical Engineering Congress and Exposition, IMECE 2004 - Anaheim, CA, United States Duration: 13 Nov 2004 → 19 Nov 2004

Keywords

Aerodynamics
Low Reynolds number
MEMS
Turbomachinery

Access to Document

10.1115/IMECE2004-60703

Cite this

@article{a03e64022890496b9c0cc1f36e164eec,

title = "Design principles and aerodynamics of low reynolds number multi-stage microturbomachinery",

abstract = "In this paper, the design process for multi-stage micro scale turbomachinery will be presented, along with CFD predictions of the key aerodynamic performance parameters required in this design process. This work focuses on the unique and unexplored design space defined by the small scale and planar geometries characteristic of MEMS turbopumps, compressors, gas turbines, steam turbines, or other turbomachinery-based microsystems. Correlations are proposed for the loss coefficient, based on laminar flow theory. A critical Reynolds number is also identified (Re crit=200-300), below which adjacent boundary layers merge, inducing a sharp increase in loss and deviation. This imposes practical limits on the miniaturization of such microturbomachinery.",

keywords = "Aerodynamics, Low Reynolds number, MEMS, Turbomachinery",

author = "Changgu Lee and Selin Arslan and Fr{\'e}chette, \{Luc G.\}",

year = "2004",

doi = "10.1115/IMECE2004-60703",

language = "English",

volume = "260",

pages = "325--331",

journal = "American Society of Mechanical Engineers, Fluids Engineering Division (Publication) FED",

issn = "0888-8116",

publisher = "American Society of Mechanical Engineers (ASME)",

note = "2004 ASME International Mechanical Engineering Congress and Exposition, IMECE 2004 ; Conference date: 13-11-2004 Through 19-11-2004",

}

TY - JOUR

T1 - Design principles and aerodynamics of low reynolds number multi-stage microturbomachinery

AU - Lee, Changgu

AU - Arslan, Selin

AU - Fréchette, Luc G.

PY - 2004

Y1 - 2004

N2 - In this paper, the design process for multi-stage micro scale turbomachinery will be presented, along with CFD predictions of the key aerodynamic performance parameters required in this design process. This work focuses on the unique and unexplored design space defined by the small scale and planar geometries characteristic of MEMS turbopumps, compressors, gas turbines, steam turbines, or other turbomachinery-based microsystems. Correlations are proposed for the loss coefficient, based on laminar flow theory. A critical Reynolds number is also identified (Re crit=200-300), below which adjacent boundary layers merge, inducing a sharp increase in loss and deviation. This imposes practical limits on the miniaturization of such microturbomachinery.

AB - In this paper, the design process for multi-stage micro scale turbomachinery will be presented, along with CFD predictions of the key aerodynamic performance parameters required in this design process. This work focuses on the unique and unexplored design space defined by the small scale and planar geometries characteristic of MEMS turbopumps, compressors, gas turbines, steam turbines, or other turbomachinery-based microsystems. Correlations are proposed for the loss coefficient, based on laminar flow theory. A critical Reynolds number is also identified (Re crit=200-300), below which adjacent boundary layers merge, inducing a sharp increase in loss and deviation. This imposes practical limits on the miniaturization of such microturbomachinery.

KW - Aerodynamics

KW - Low Reynolds number

KW - MEMS

KW - Turbomachinery

UR - https://www.scopus.com/pages/publications/21444441082

U2 - 10.1115/IMECE2004-60703

DO - 10.1115/IMECE2004-60703

M3 - Conference article

AN - SCOPUS:21444441082

SN - 0888-8116

VL - 260

SP - 325

EP - 331

JO - American Society of Mechanical Engineers, Fluids Engineering Division (Publication) FED

JF - American Society of Mechanical Engineers, Fluids Engineering Division (Publication) FED

M1 - IMECE2004-60703

T2 - 2004 ASME International Mechanical Engineering Congress and Exposition, IMECE 2004

Y2 - 13 November 2004 through 19 November 2004

ER -

Design principles and aerodynamics of low reynolds number multi-stage microturbomachinery

Abstract

Keywords

Access to Document

Other files and links

Fingerprint

Cite this