Casing for e.g. turbojet engine, of aircraft, has annular combustion chamber delimited by internal and external platforms that are made of metal and formed from single piece with walls of chamber, where platforms are welded onto walls,申请号FR20120055637-传众专利搜索

Casing for e.g. turbojet engine, of aircraft, has annular combustion chamber delimited by internal and external platforms that are made of metal and formed from single piece with walls of chamber, where platforms are welded onto walls

申请公布号：FR2992018(A1)

申请号：FR20120055637

申请日期：2012.06.15

申请公布日期：2013.12.20

申请人：

SNECMA

发明人：LUNEL ROMAIN;CAZALENS MICHEL;COMMARET PATRICE

分类号：F01D9/04;F23R3/50

主分类号：F01D9/04

摘要：<p>The casing (30) has an annular combustion chamber (10) delimited by metallic annular walls e.g. internal and external revolution walls (12, 14) and a high-pressure turbine dispenser (20) including annular internal and external platforms (22, 24) secured to a downstream end of the walls. The platforms are made of metal and are formed from a single piece with the walls. The platforms are welded onto the walls of the combustion chamber. The dispenser has a set of guide blades (26) extending radially between the platforms, where the blades are spaced circumferentially with respect to each other.</p>