STEPPED HEAT SHIELD FOR A TURBINE ENGINE COMBUSTOR,申请号US201515113536-传众专利搜索

STEPPED HEAT SHIELD FOR A TURBINE ENGINE COMBUSTOR

申请公布号：US2017009987(A1)

申请号：US201515113536

申请日期：2015.02.03

申请公布日期：2017.01.12

申请人：

UNITED TECHNOLOGIES CORPORATION

发明人：McKinney Randal G.;Cunha Frank J.;Kostka, JR. Stanislav

分类号：F23R3/00;F02C7/24;F23R3/06

主分类号：F23R3/00

地址：Hartford CT US

摘要：An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall with a shell and a heat shield. The combustor wall defines a quench aperture therethrough. The combustor wall also defines a cavity between the shell and the heat shield. The shell defines a first aperture through which air is directed into the cavity. The heat shield includes a rail that at least partially defines a second aperture configured to direct at least some of the air within the cavity out of the combustor wall and towards the quench aperture.

主权项：1. An assembly for a turbine engine, the assembly comprising: a combustor wall including a shell and a heat shield, the combustor wall defining a quench aperture therethrough and defining a cavity between the shell and the heat shield; the shell defining a first aperture through which air is directed into the cavity; and the heat shield including a rail that at least partially defines a second aperture configured to direct at least some of the air within the cavity out of the combustor wall and towards the quench aperture.