US 4,827,712 A · Turbofan gas turbine engine

Abstract

A turbofan gas turbine engine comprising in axial flow series a fan, a booster compressor and a core engine is provided with a diffuser. The diffuser is positioned axially between the booster compressor and the compressor of the core engine to efficiently diffuse the air from the fan to the compressor of the core engine. The diffuser comprises a plurality of circumferentially arranged geodesic pipe diffusers, the pipe diffusers extend axially and radially and the outlets of the pipe diffusers are displaced circumferentially by an angle of between 20.degree. and 60.degree. with respect to the inlets of the pipe diffusers. The geodesic pipe diffusers allows the airflow between the fan and the core engine to be diffused adequately without compromising the efficiency of the core engine, or the high mass flow rate of the fan and also minimizes the length, weight and drag of the gas turbine engine.

Claims19

Dependent claims

A turbofan gas turbine engine comprising in axial flow series a fan, a booster compressor means, a compressor means, a combustor means, a first turbine means and a second turbine means,

the first turbine means being arranged to drive the compressor means,
the second turbine means being arranged to drive the fan and the booster compressor means,
a diffuser means being positioned axially between the booster compressor means and the compressor means, the diffuser means comprising a plurality of circumferentially arranged geodesic pipe diffusers, each geodesic pipe diffuser having an inlet at the upstream end and an outlet at the downstream end, the outlet of each geodesic pipe diffuser being displaced circumferentially by an angle with respect to the inlet thereof, each geodesic pipe diffuser following substantially the shortest path between the inlet and the outlet thereof;
said geodesic diffusers extending both axially and radially inwardly and each following substantially a straight line path between said respective inlet and outlet thereof.

1 more element

A turbofan gas turbine engine comprising in axial flow series a fan, a booster compressor means, diffuser means, compressor means, combustor means, first turbine means and a second turbine means,

a first shaft means to drivingly connect the first turbine means and the compressor means, the first turbine means being arranged to drive the compress means via the first shaft means,
a second shaft means to drivingly connect the second turbine means and the booster compressor means, the second turbine means being arranged to drive the booster compressor means via the second shaft means,
a gear means to drivingly connect the second shaft and the fan, the second turbine being arranged to drive the fan via the second shaft means and the gear means,
the booster compressor means comprising a booster rotor and a plurality of wide chord blades, the wide chord blades being arranged circumferentially on the booster rotor in at least one stage,
the diffuser means comprising a plurality of circumferentially arranged geodesic pipe diffusers, each geodesic pipe diffuser having an inlet at the upstream end and an outlet at the downstream end, the outlet of each geodesic pipe diffuser being displaced circumferentially by an angle with respect to the inlet thereof, each geodesic pipe diffuser following substantially the shortest path between the inlet and the outlet thereof;
said geodesic pipe diffusers extending axially and radially inwardly and each following substantially a straight line path between said respective inlet and outlet thereof.

3 more elements

Dependencies are inferred from the claim text.

Turbofan gas turbine engine

Life of this patent

Turbofan gas turbine engine

Life of this patent

Abstract

Claims19