发明名称 GAS TURBINE COMBUSTOR COOLING STRUCTURE
摘要 PURPOSE:To reduce or eliminate problems such as heat exposure damage, cracks, shorter life, etc. of a combustor by forming axially parallel inner channels on the inner wall of the outer cylinder, and disposing communicating holes which have a diameter larger than the inner channel width, near the outer cylinder upstream end and the inner cylinder downstream end coaxially with the inner channels. CONSTITUTION:Each of multiple cylinders 3-6 having an increasingly larger diameter has a double structure in which an outer cylinder 12 and an inner cylinder 13 are overlapped. Multiple inner channels 14 having a rectangular section are formed on the inner wall of the outer cylinder in parallel with the combustor axis. Further, multiple cooling air communicating holes 15, 16 having a diameter larger than the width of the inner channels 14 are drilled in a staggered manner circumferentially near the upstream end of the outer cylinder 12 and the downstream end of the inner cylinder 13 coaxially with the inner channels 14. Because of this, a uniform cooling can be performed over the entire axial length of the combustor inner cylinder 13 by means of air cooling or film cooling. Therefore, problems of heat exposure damage, crack, shorter life, etc., of the combustor due to the increased output and temperature can be reduced or eliminated.
申请公布号 JPS63243631(A) 申请公布日期 1988.10.11
申请号 JP19870074502 申请日期 1987.03.30
申请人 MITSUBISHI HEAVY IND LTD 发明人 UCHIMI ISAMU;AOYAMA KUNIAKI
分类号 F23R3/06;F23R3/42 主分类号 F23R3/06
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