发明名称 |
Combustor panel arrangement |
摘要 |
A combustor module (18) for a gas turbine engine is provided that includes a first annular liner assembly (26) extending along a longitudinal axis of the engine. The first annular liner assembly (26) includes a first annular support shell (52) and a plurality of first heat shield panels (48,50) coupled to the first annular support shell (52). The first heat shield panels (48,50) form a segmented ring defining a plurality of first axial seams (54) therebetween. The combustor module (18) further includes a bulkhead (30) coupled to the first annular liner assembly (26). The bulkhead (30) provides a plurality of fuel nozzles (38) for passing a first mass flow comprising fuel and air. The combustor module (18) further includes a second annular liner assembly (28) coupled to the bulkhead (30). The second annular liner assembly (28) is in spaced-apart generally coaxial relationship from the first annular liner assembly (26) by a channel height H. The second annular liner assembly (28) includes an air admittance hole (78) having a mean diameter D extending along a hole axis (80). The hole axis (80) is offset from the first axial seam (54) defined by the first heat shield panels (48,50). |
申请公布号 |
EP2333416(A3) |
申请公布日期 |
2014.02.12 |
申请号 |
EP20100252019 |
申请日期 |
2010.11.29 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
KIRSOPP, PHILIP J.;DORNBACK, AARON J.;HOKE, JAMES B. |
分类号 |
F23R3/00 |
主分类号 |
F23R3/00 |
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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