| 摘要 |
<p>Disclosed is an aircraft gas turbine comprising a compressor (14), a combustor (15) and a turbine (16) housed in a cylindrical main body casing (12). The main body causing (12) is provided with a thick walled section (52) on its peripheral edge on the side of the moving blades (34), where compressed air compressed by the compressor (14) is circulated inside the thick walled section (52) which is provided with a cooling passage (53) for cooling and also an exhaust passage (55) which discharges the compressed air circulated in the cooling passage (53) through the combustion gas passage A. Accordingly, construction is simplified and loss of efficiency is prevented, while the structural strength of the thick walled sections is ensured by appropriate cooling provided by the thick walled sections in the casing, and efficient containment properties as well as sufficient clearance for the moving blades is also ensured.</p> |
