Angled cooling divider wall in blade attachment

[0018] A turbofan engine illustrated schematically in FIG. 1, presented as an example of the application of the present invention, includes a housing or nacelle 10, a low pressure spool assembly seen generally at 12 which includes a fan 14, a low pressure compressor 16 and a low pressure turbine 18, a high pressure spool assembly seen generally at 20 which includes a high pressure compressor 22 and a high pressure turbine 24. A core casing 28 surrounds the low and high pressure spool assemblies 12 and 20 to define a main fluid path (not indicated) therethrough. In the main fluid path there is provide a combustor seen generally at 26 with fuel injecting means (not indicated) to constitute a gas generator section. The compressors 16 and 22 drive a main airflow (not indicated) along the main fluid path and provide bleed airflow as a cooling air source for cooling the combustor 26 as well as the turbines 18 and 24.

[0019] It should be noted that similar components of the different embodime