Blade solidity

For blade configuration in general, see airfoil. For how it is linked to turbomachinery application see, see Turbomachinery.

Blade solidity is an important design parameter for the axial flow impeller and is defined as the ratio of blade chord length to pitch.

Airfoil nomenclature

Blade Solidity = c/s

Where

$s=2 \pi r_{m}/ Z_{b}$
$r_{m}$ is the mean radius
$Z_{b}$ is blade number
Cord length c is the length of the chord line
s is pitch

In case of an axial flow impeller mean radius is defined in terms of hub ( $r_h$ ,inner radius) and tip radius ( $r_t$ ,outer radius) as :

$r_{m}= [(r_{t}^2 + r_{h}^2)/2]^{0.5}$

Blade solidity affects various turbomachinery parameters. So to vary those parameters one needs to vary blade solidity but there are some limitations imposed by Aspect ratio (wing) (span/chord), pitch. If an impeller has few blades i.e high pitch it will result in less lift force and in a similar manner for more blades i.e. very low pitch, there will be high drag force.

Blade solidity should not be confused with rotor solidity, which is the ratio of the total area of the rotor blades to the swept area of the rotor.

Flow over isolated airfoil

Blade solidity is an important parameter that inter relates turbomachine parameter to airfoil parameter .Lift and drag coefficient for an airfoil is inter related to blade solidity as shown :

$C_L = 2(s/c)(\tan\beta_1 - \tan \beta_2)cos\beta_m$
$C_d = \left( \frac{s} {c}\right) \left(\frac{\Delta p_0} {\rho W_{1}^2 /2}\right)$

where

$C_L$ is lift coefficient
$C_d$ is the drag coefficient
$\beta_1$ is the inlet flow angle on the airfoil
$\beta_2$ is the outlet flow angle on the airfoil
$\beta_m$ is the mean flow angle
$W_1$ is inlet flow velocity i.e relative to airfoil
$W_m$ is mean flow velocity
$\Delta p_0$ is the pressure loss
$\tan \beta_m = \frac {1} {2} (\tan\beta_1 + \tan\beta_2)$

In an airfoil the mean line curvature is designed to change the flow direction ,the vane thickness is for strength and the streamlined shape is to delay the onset of boundary layer separation, taking all the design factors of an airfoil resulting forces of lift and drag can be expressed in terms of lift and drag coefficient.

$F_L = C_Lbc \left(\frac {1} {2}\rho W_m^2\right)$
$F_d = C_dbc \left(\frac {1} {2}\rho W_m^2\right)$

b is the wingspan

c is the chord length

Preliminary design procedure

Design of the impeller depends on specific speed, hub-tip ratio and solidity ratio. To illustrate the dependence, an expression for axial flow pump and fan is shown

\frac {c}{s}= \frac {10} {(D_h/D_t)(N_s/1000)^{1.5}}

where

$\frac {D_h}{D_t}$ is ratio of hub to tip diameter
$N_s$ is the specific speed

Cordier diagram can be used to determine specific speed and impeller tip diameter $D_t$ . Accordingly solidity ratio and hub-tip ratio (range 0.3-0.7) can be adjusted.

Solidity ratio generally falls in the range of 0.4-1.1

References

Peng, William W. (2008), Fundamentals of Turbomachinery, Wiley, ISBN 978-0-470-12422-2
Venkanna, B.K. (2009), Fundamentals of Turbomachinery, PHI learning private limited, ISBN 978-81-203-3775-6
Turton, R.K. (1995), Principles of turbomachinery, Springer (New Delhi), ISBN 8184896042
Rama, S.R. Gorla (2003), Turbomachinery Design and Theory, Marcel Dekker ,Inc., ISBN 0-8247-0980-2
Yahya, S.M. (2002), Turbines, compressors and fans, TMH, ISBN 0070707022

Blade solidity

Flow over isolated airfoil

Preliminary design procedure

See also

References