Delta-v (more known as "change in velocity"), symbolized as Δ
v and pronounced delta-vee, as used in spacecraft flight dynamics, is a measure of the impulse per unit of spacecraft mass that is needed to perform a manoeuvre such as launching from or landing on a planet or moon, or an in-space orbital manoeuvre. It is a scalar that has the units of speed.
As used in this context, it is not the same as the physical change in velocity of said spacecraft.
Delta-v - Wikipedia
Delta-v can be applied over a short or long period, but the time taken will affect the trajectory. Applying acceleration or deceleration too rapidly will turn a human into jam, and they'd be dead, Jim.
Say you attempt to decelerate from 3,200 m/s to 0 m/s at xg (where 1g = 9.81 m/s^2; acceleration due to gravity at the surface of the earth) takes 326/x seconds, so 326 seconds at a deceleration of 1g. The fully fuelled Apollo CSM had a thrust of ~90,000 N and a mass of ~30,000 kg, unfuelled mass was ~12,000 kg, so the acceleration was 3 to 7.5 m/s^2 or about 0.3g to 0.75g. The maximum burn time was 750 seconds. If thrusting in the direction of travel, deceleration lowers the perigee until it intersects the earth. The trajectory remains an ellipse, however - it doesn't become a straight line. While thrusting lowers the altitude, the orbital velocity goes as roughly 1/√r, where r is the distance from the centre of the earth, so it increases. Counterintuitively, you actually speed up because you lose potential energy and gain kinetic energy.
The radial velocity on entering the Earth's atmosphere when merely falling from GEO can be calculated from the formula I gave previously. The geocentric gravitational constant GM = 3.986x10^14 m^3/s^2; GEO is 42,164 km from centre of mass; top of atmosphere is 6,378 + 100 km (Kármán line) = 6,478 km from centre of mass, so the inward radial speed is 3.25 km/s or 11,710 km/hour at the Kármán line. However, there is also tangential velocity and as you're not actively braking the whole way down, you're really on an orbit that now intercepts the atmosphere of a rotating Earth. Re-entry velocity from LEO is typically 7.8 km/s, from the Moon, 11 km/s. You'd need more thermal protection than returning from LEO.