| 摘要 |
An annular one-piece liner (32) for a combustor of a gas turbine engine, including a first end (42) adjacent to an upstream end of the combustor, a second end (50) adjacent to a downstream end of the combustor (16), and a plurality of corrugations (68,64,74) between the first and second ends (42,50), the corrugations having an amplitude (56) and a wavelength (58) between adjacent corrugations, wherein at least one of the amplitude (56) and/or the wavelength (58) between adjacent corrugations is variable from the first end (42) to the second end (50). <IMAGE> <IMAGE>
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