发明名称 |
Hole pattern for gas turbine combustor |
摘要 |
A combustor for a turbine engine includes an outer liner (34) having a row of circumferentially distributed outer combustion air holes and an inner liner (32) circumscribed by the outer liner (34) and having a row of circumferentially distributed inner combustion air holes. The inner and outer liners (32, 34) each include at least a major air hole (104) having a first hole size, an intermediate air hole (108) having a second hole size, and a minor air hole (106) having a third hole size. The first, second, and third hole sizes are all different from each other. |
申请公布号 |
EP2133628(A3) |
申请公布日期 |
2012.08.29 |
申请号 |
EP20090250924 |
申请日期 |
2009.03.30 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
SHELLEY, JONATHAN K.;BURD, STEVEN W.;CHEUNG, ALBERT K.;KOZOLA, STUART L. |
分类号 |
F23R3/06 |
主分类号 |
F23R3/06 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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