HB 20086-2012
Test methods of compositive cooling effectiveness of turbine blade for aircraft gas turbine engine (English Version)

Standard No.

HB 20086-2012

Language

Chinese, Available in English version

Release Date

2013

Published By

Professional Standard - Aviation

Latest

HB 20086-2012

Scope

This standard specifies the general requirements, test procedures, data processing and result evaluation for the comprehensive cooling effect test of turbine blades of aviation gas turbine engines. This standard is applicable to the cooling effect test of turbine blades using medium-temperature and medium-pressure gas or heated air as the medium and a fan-shaped test section composed of more than three real turbine blades.

HB 20086-2012 history

• 2013 HB 20086-2012 Test methods of compositive cooling effectiveness of turbine blade for aircraft gas turbine engine