| 摘要 |
PROBLEM TO BE SOLVED: To provide a gas turbine improving performance and reliability by reducing turbulence and pressure loss in air flow from a compressor to a combustor with a simple structure. SOLUTION: In a diffuser 2, an air passage from an air outlet 1c of the compressor 1 to an air inlet of the combustor 3a is constructed to gradually change from a turbine shaft direction to a radial direction. With this structure, air delivered from the compressor 1 flows obliquely outward of a gas turbine as indicated with an arrow A and is supplied to the combustor 3. Consequently, pressure loss from a compressor to the combustor is reduced and turbulence of air flow is reduced, and layout and connection structure of the diffuser is made easy. COPYRIGHT: (C)2006,JPO&NCIPI
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