The function of the engine is to supply the thrust for aircraft movement and air for the environmental and ice protection systems. It also supplies electrical and hydraulic power through the two main generators (these are variable frequency generators) and one hydraulic pump. The main generators and the hydraulic pump are on the accessory gearbox.

The engine is a high bypass ratio turbo-fan with low pressure (LP) and high pressure (HP) compressors. The compressors are connected to turbines through co-axial shafts. As the LP compressor turns, it pulls air into the engine and compresses it. This air then divides into two flows, the bypass (cold) flow and the core (hot) flow. The bypass air goes through the LP compressor outlet guide vanes (OGVs) and bypass duct to the exhaust nozzle. The HP compressor increases the pressure of the core air which then goes into the combustion chamber.

In the combustion chamber, the compressed air is mixed with fuel (supplied through spray nozzles) and ignited. The subsequent increase in temperature causes the gases to expand and accelerate rearwards. The hot gases go through the turbines to the exhaust nozzle. The HP and LP turbines use the energy in the gas flow to turn the HP and LP compressors. The exhaust nozzle mixes the core air with the bypass air. The air then accelerates through the nozzle to the atmosphere.

The BR710 engine contains two main rotating assemblies (spools): a single-stage LP compressor (fan) driven by a two-stage LP turbine, and a ten-stage HP compressor, driven by a two-stage HP turbine. In addition, the HP spool provides an external drive for the engine-driven accessories mounted on the Accessory Gearbox (AGB).

There are 5 main bearings (numbered 1 to 5 from the front) contained in two bearing chambers. Bearings 1, 2 and 3 are in the front bearing chamber (FBC). Bearings 4 and 5 are in the rear bearing chamber (RBC).

Each rotating assembly is supported at the front by a ball bearing, which also transmits axial loads, and at the rear by a roller bearing. The LP spool has an additional roller bearing (No. 2) for support.

Each bearing chamber is supported by the fixed structure of the engine, which passes all loads (thrust, weight etc.) into the airframe pylon via the engine mounts. Engine rigidity is enhanced by use of a structural bypass duct attached to the forward and rear fixed structures, at the front and rear of the engine.