Characterization of Tandem Airfoil Configurations of Axial Compressors

Manas M P; Shine S R

doi:10.1515/tjj-2018-0018

Article

Characterization of Tandem Airfoil Configurations of Axial Compressors

Manas M P and Shine S R

Published/Copyright: July 12, 2018

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From the journal International Journal of Turbo & Jet-Engines Volume 39 Issue 2

Abstract

The objective of the current study is to investigate the effects of geometric parameters on the fluid flow patterns, diffusion factor, load-split, and off-design performance of the tandem configuration under subsonic, rectilinear, cascade flow. A 2-D computational model using finite volume formulation has been developed and validated against available experimental data. The obtained data is presented in a format involving loss parameter and loading and will help the designer to have sufficient number of combinations within the useful range of application. It is observed that general performance behavior of tandem cascade is similar to a single airfoil data. Load shifting from the front airfoil to the rear airfoil is noted at positive axial overlaps and higher camber ratios. An optimum gap ratio of around 2 is observed for the range of configurations investigated. Contrary to the previous literature, the present study indicates higher loading of the front airfoil for the best overall loading-to-loss ratio of the tandem configuration.

Keywords: tandem blade; diffusion factor; load split; axial compressor; numerical analysis

PACS: (2010); 88.50.gj

Nomenclature

a: overlap, axial distance between FA TE and AA LE
AO: a/CAX, axial overlap between the two blades
AR: ratio of gap distance at the inlet and outlet of the gap nozzle formed between the two airfoils
C: chord
CAX: axial distance between AA TE and FA LE
Cp: coefficient of pressure
Cp,i: ideal static pressure rise coefficient
CR: camber ratio
DF: Lieblein diffusion factor
DP: Lei’s diffusion parameter
AA: aft airfoil
FA: forward airfoil
LE: leading edge
LS: load split
P: static pressure
PP: percentage pitch, t/s in percentage
s: pitch wise spacing between blade rows
t: pitch wise spacing between FA TE and AA LE
TE: trailing edge
w: velocity in cascade frame of reference
x: axial distance
Greek
β: flow angle relative to axial coordinate
△ε: total flow turning
γ: stagger angle
θ^*: boundary layer momentum thickness at TE
ρ: density, kg/m³
σ: solidity, C/s
φ: camber ratio, CR
ωc: stagnation pressure loss coefficient
ωp: momentum thickness loss parameter
Subscripts
eff: effective
l: local
0: stagnation conditions
11: FA inlet station
12: FA exit station
21: AA inlet station
22: AA exit station
θ: pitch wise direction

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Received: 2018-05-16

Accepted: 2018-07-05

Published Online: 2018-07-12

Published in Print: 2022-05-25

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Articles in the same Issue

https://doi.org/10.1515/tjj-2018-0018

Keywords for this article

tandem blade; diffusion factor; load split; axial compressor; numerical analysis