- 专利标题： Gas turbine engine quench pattern for gas turbine engine combustor
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申请号： US15025808申请日： 2014-10-20
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公开(公告)号： US10816206B2公开(公告)日： 2020-10-27
- 发明人: Dennis M. Moura, III , Reza Rezvani
- 申请人： United Technologies Corporation
- 申请人地址： US CT Farmington
- 专利权人： Raytheon Technologies Corporation
- 当前专利权人： Raytheon Technologies Corporation
- 当前专利权人地址： US CT Farmington
- 代理机构： Getz Balich LLC
- 国际申请： PCT/US2014/613710 WO 20141020
- 国际公布： WO2015/102736 WO 20150709
- 主分类号： F23R3/14
- IPC分类号： F23R3/14 ; F23R3/50 ; F23R3/06 ; F02C3/00 ; F23R3/28
摘要：
A combustor for a turbine engine includes an inner liner panel with a multiple of inner dilution passages. The multiple of dilution passages includes a repeating pattern of a first major inner air passage, a minor inner air passage, and a second major inner air passage. A combustor for a turbine engine includes an outer liner panel with a multiple of outer dilution passages. The multiple of outer dilution passages includes a repeating pattern of a first major outer air passage, a first minor outer air passage, a second major outer air passage, and a second minor outer air passage.
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