For lower thrust rocket engine designs, either a Gas Generator (GG) cycle or a Dual Expander (DE) cycle can be considered, among others. While each of these cycles has its inherent advantages and disadvantages in an overall sense, each cycle requires a different approach to the turbopump assembly (TPA) design. This blog presents a general summary of advantages and disadvantages of each of these cycles, and obviously applies when the engine thrust level is low enough that a DE cycle can even be considered (less than about 50,000 lbf of thrust). This summary is not exhaustive and focuses primarily on the TPA, but provides information to help decide which cycle to use.