Gas turbine engine and method for cooling the compressor of a gas turbine engine

摘要

A gas turbine engine includes a compressor with rotor blades having roots connected into seats of a compressor drum. The rotor blade roots and/or the compressor drum have longitudinal passages for a cooling fluid, connecting higher pressure areas to lower pressure areas of the gas turbine engine.

主权项

1. A gas turbine engine, comprising:
a compressor including a compressor drum and rotor blades having roots connected into seats of the compressor drum, wherein at least one of the rotor blade roots and the compressor drum include longitudinal passages for a cooling fluid, the longitudinal passages connecting higher pressure areas to lower pressure areas of the gas turbine engine; a gap downstream of the compressor drum for separating the compressor drum from a combustion chamber; and a protrusion provided within the gap to close a compressed air path, wherein the higher pressure areas are defined between the protrusion and the compressed air path.