EDIT: when I answered, the question consisted only in the very first paragraph so I didn't know yet it was actually a nautical question.
On fixed-wing aircraft twist is mainly used, together with chord variation, to obtain a lift distribution as elliptical as possible, in order to minimise induced drag.
Moving along the wingspan, everywhere lift changes a so called trailing-vortex is shed backward and contributes to the formation of the wake. This vortex is correlated to the bent of the flow on the upper and lower wing’s surface as visible in this picture:
Spanwise flow distortion. Source: https://cdn-images-1.medium.com/max/1600/0\*2gL-QOXqx51qNdAE.jpg
To simply summarise: lift changes spanwise $\Rightarrow$ trailing-vortex is shed in the wake $\Leftrightarrow$ flow on the wing bends.
So, does twist increase spanwise flow? It depends on if and how much this twist makes the lift change.
For example, on a rectangular wing with no twist, the lift changing is concentrated toward the tip and therefore the biggest spanwise flow has to be expected there. On a jetliner’s wing, the spanwise lift is more uniformly distributed and so is the spanwise flow.
The following picture shows a sample of different lift distributions:
Several spanwise lift distribution. Source: https://1.bp.blogspot.com/-e8479jPK0N0/U28fSOl8nrI/AAAAAAAASkM/35wCfWrvFq4/s1600/lift_distribution.jpg
The red line is for a rectangular wing; the target lift distribution is the elliptical one; and $\lambda=0$ denotes a delta wing.
From the picture it can also be understood how twist works: twisting the wing so that its tip has less incidence makes lift diminish there and a more ideal distribution is achieved. As pointed out by @RobertDiGiovanni this has also a relieving structural effect.
Sweep angle generates spanwise flow too: with a swept wing, the approaching speed can be decomposed in a component perpendicular to the leading edge plus a component parallel to it. This latter (called $V_n$ in the following picture) is completely spanwise flow:
Speed decomposition. Source: this answer
Twist is used also on rotary-wing aircrafts but whit the double effect of both optimising the bladewise lift distribution to minimise induced drag and to compensate for the rotating speed becoming smaller and smaller (until null) toward the root. So, also in this case everywhere the lift changes spanwise a trailing-vortex is shed in the wake and the flow on the blades's surface bends, just like in the first picture.
When the helicopter is flying forward and the blade, during its rotation, is passing over the nose or over the tailboom, the freestream flow is also investing the blade completely spanwise.