发明名称 Can annular combustion arrangement with flow tripping device
摘要 A can annular combustion arrangement (12) for a gas turbine engine (10), including: a combustor can (14) having an inlet (46) at a head end (62); an annular chamber (30) surrounding the combustor can (14) for delivering a flow of compressed air from a plenum (18) to the inlet (46); a fuel injector (49) configured to inject a flow of fuel into the flow of compressed air; and a flow tripping device (60) surrounding the combustor can (14) and disposed in the annular chamber (30) downstream of the fuel injector (49).
申请公布号 US9297532(B2) 申请公布日期 2016.03.29
申请号 US201213691947 申请日期 2012.12.03
申请人 Siemens Aktiengesellschaft 发明人 Wasif Samer P.;Meisl Juergen;Janus Bertram;Koch Andreas
分类号 F23R3/02;F23R3/26;F23R3/54;F23R3/00;F23R3/46 主分类号 F23R3/02
代理机构 代理人
主权项 1. A can annular combustion arrangement for a gas turbine engine, comprising: a combustor can comprising a combustor can inlet and a burner, the combustor can defining a combustion zone therein downstream of a burner outlet; an annular chamber surrounding the combustor can and comprising an inner dimension defined in part by an exterior surface of the combustor can for delivering a flow of compressed air from a plenum to the combustor can inlet; a fuel injector disposed within the annular chamber and configured to inject a flow of fuel into the flow of compressed air; and a circumferentially continuous, ring shaped flow tripping device extending radially outward with respect to a combustor can longitudinal axis from the combustor can into the annular chamber transverse to a direction of the flow of compressed air, surrounding the combustor can, and disposed axially downstream of the fuel injector and along the combustor can longitudinal axis in a region bounded at one end by the burner outlet and at another end by the combustor can inlet, wherein the flow tripping device defines a narrowest gap between the flow tripping device and a second surface that defines a radially outward boundary of the annular chamber, and wherein at least a portion of an axial length along the combustor can longitudinal axis of the exterior surface of the combustor can between the combustor can inlet and the flow tripping device is characterized by a constant diameter.
地址 München DE