They typically use non-afterburning versions of fighter jet turbofans on these. It’s a bit hard to say “typical” given we only really have 2 examples (YB-35 and 49 don’t really count). The B-2 uses non-afterburning F-118s.
The B-21 is going to use a non-afterburning version of something very close to a F-135. This is probably as high a bypass as you would get, otherwise you’d end up with a flying block. For VLO stealth bombers the engines need to be deeply embedded with fan blades concealed and IR reduction at the exhaust end. Trying to do this with high bypass engines will begin to impede the design and aerodynamics. In any case, flying wings already produce a lot of lift, are fuel efficient and have internal space/volume for a lot of fuel to be stored already.
I was talking about 'higher bypass' not 'high bypass'. Not sure if the widely cited figure of 0.25 bypass ratio for WS-15 is accurate, but the figure seems reasonable for an engine designed for a supercruising fighter jet, but likely not ideal for H-20 if it's a subsonic bomber.
Let's disregard fluid dynamics and speak purely in terms of the geometry of cross-sections. To increase cross-section area ratio from 0.25 to 0.5 requires a less than 10% increase in diameter. Not unreasonable for a stealth bomber.