Patent ID: 9657593
Date: 2017-05-23
CPC Classifications: F01D,F02C,F05D,Y02T

Claim:
1. An aircraft gas turbine comprising: a core engine casing for a core engine, the core engine casing including: a turbine section, each of the compressor section, combustion chamber section and turbine section being separate components and each including an outer wall, a plurality of circumferentially extending flanges connecting the compressor section, combustion chamber section and turbine section together in axial succession to form the core engine casing having an overall outer wall assembled from the outer walls of each of the compressor section, combustion chamber section and turbine section, a plurality of cooling-air tubes each having part sections integrally provided as one piece with the outer wall of each of the compressor section, combustion chamber section and turbine section, respectively, the respective part sections separably connected to one another at joints between the compressor section, combustion chamber section and turbine section, with the plurality of cooling air tubes extending through the circumferentially extending flanges the plurality of cooling-air tubes each extending in an axial direction relative to an engine axis, the cooling-air tubes each providing outwardly closed air paths in the axial direction along the overall outer wall, with circumferential portions of the overall outer wall between adjacent ones of the axially extending cooling-air tubes being externally exposed.