| 摘要 |
<p>A can-annular gas turbine engine combustion arrangement (10), comprising: an outer casing (24) and a rotor casing (26) defining a plenum (22) there between; a diffuser configured to exhaust compressed air into the plenum (22); a turbine; a combustor can (12) comprising a combustor inlet (38); baffles disposed in the plenum (22), configured to divide the plenum (22) into radial sectors, and effective to inhibit circumferential motion of the compressed air within the plenum (22), adjacent radial baffles defining a radial sector there between; and hot gas transition ducts (40) each configured to guide hot gases from a respective combustor can (12) to a turbine inlet (42) and each spanning at least two radial sectors. Each baffle comprises a duct-aperture to accommodate the spanning hot gas transition duct (40).</p> |
