公开(公告)号：US20150192020A1

公开(公告)日：2015-07-09

申请号：US14150190

申请日：2014-01-08

Applicant: General Electric Company

Inventor： Anshuman Singh ,  Joe Timothy Brown ,  Ravi Meenaksh ,  Ibrahim Sezer

IPC: F01D5/18

CPC classification number: F01D11/24 ,  F01D5/187 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2250/294 ,  F05D2260/202 ,  F05D2260/204 ,  Y02T50/676

Abstract: A turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, and a shroud mounted in one of the compressor portion and the turbine portion. The shroud includes a radial outer side, and a plurality of side surfaces. The radial outer side includes a recessed portion. A trench is formed in the recessed portion, and a cooling passage extends between the trench and at least one of the plurality of side surfaces. An airfoil component is arranged in the one of the compressor portion and the turbine portion. The airfoil component includes an airfoil portion having at least one mounting member. The at least one mounting member includes an internal cavity. A trench element is formed in the internal cavity, and a cooling passage element extends between the trench element and an external surface of the nozzle.

Abstract translation: 涡轮机包括压缩机部分，可操作地连接到压缩机部分的涡轮机部分和安装在压缩机部分和涡轮机部分之一中的护罩。 护罩包括径向外侧和多个侧表面。 径向外侧包括凹部。 在凹部中形成沟槽，并且冷却通道在沟槽和多个侧表面中的至少一个之间延伸。 在压缩机部分和涡轮部分中的一个中布置有翼型部件。 机翼部件包括具有至少一个安装部件的翼型部分。 所述至少一个安装构件包括内部空腔。 沟槽元件形成在内腔中，冷却通道元件在沟槽元件和喷嘴的外表面之间延伸。