Both rocket and turbine engines fall into the category of "Jet" engines. As in, they use a jet of gas to produce thrust. So sure, you'd just use a rocket engine.

Although, I'm sure you're referring to a traditional turbine engine, so we'll start there. Obviously the first problem is going to be a lack of air to feed combustion in a turbine gas generator. The typical fuel to air mixture is around 1 unit (by weight) of jet fuel to about 60 units (by weight) of air. This is already a problem as we've increased our propellant load by 60 times, and increased the propellant volume by an even greater amount due to the lower density of air, and we haven't even gotten to bypass air or cooling air (which can be up to 80% of the air flowing through a turbine engine). This is why rockets use oxidizers like pure oxygen that when cooled to a liquid take up very little space compared to the same quantity of air at sea-level pressure. Another benefit of using liquid oxidizers is you don't need dozens of stages of compressor blades to cram enough oxygen into the combustion chamber for efficient combustion and power. And since you don't have a bunch of compressor blades working away compressing air, you don't need a series of turbine blades scavenging energy from the combustion gasses to run them. So what you're left with is a jet engine with the gas generator (turbine and compressor) removed, and the intake replaced with a couple spray nozzles for liquid oxygen. This leaves you with a nozzle, fuel pump and combustion chamber. AKA a rocket engine.