公开(公告)号：US20130287563A1

公开(公告)日：2013-10-31

申请号：US13863685

申请日：2013-04-16

Applicant: ALSTOM TECHNOLOGY LTD

Inventor： Angus Robert Brummitt-Brown ,  Kanu Mistry ,  Adrian Clifford Lord

IPC: F01D9/04

CPC classification number: F01D9/042 ,  F01D25/246 ,  F05D2220/31 ,  F05D2240/80 ,  F05D2250/314 ,  Y10T29/49236

Abstract: An axial flow turbine diaphragm is constructed without welding or other metal fusion or melting techniques. Static blade units are attached to inner and outer diaphragm rings by radially inner platform portions that engage the radially inner ring, and radially outer platform portion s that engage the radially outer ring, the inner platform portions being elongate in the circumferential direction of the turbine diaphragm and the outer platform portions being elongate in a direction compatible with the stagger angle of the aerofoils. The outer circumference of the radially inner ring has a blade unit retaining feature of complementary shape and orientation to the inner platform portions of the static blade units, and the inner circumference of the radially outer ring is provided with a plurality of blade unit retaining features of complementary shape and orientation to corresponding outer platform portions of the static blade units.

Abstract translation: 在没有焊接或其他金属熔化或熔化技术的情况下构造轴流涡轮隔膜。 静态叶片单元通过接合径向内环的径向内平台部分和与径向外环接合的径向外平台部分s附接到内隔膜环和外隔膜环，内平台部分在涡轮隔膜的圆周方向上是细长的 并且所述外平台部分在与所述机翼的交错角度相适应的方向上是细长的。 径向内环的外周具有与静态叶片单元的内平台部分互补形状和取向的刀片单元保持特征，并且径向外环的内周设置有多个刀片单元，其保持特征 与静态叶片单元的对应的外平台部分的互补形状和取向。

公开(公告)号：US09840928B2

公开(公告)日：2017-12-12

申请号：US13863685

申请日：2013-04-16

Applicant: ALSTOM Technology Ltd

Inventor： Angus Robert Brummitt-Brown ,  Kanu Mistry ,  Adrian Clifford Lord

IPC: F01D9/04 ,  F01D25/24

CPC classification number: F01D9/042 ,  F01D25/246 ,  F05D2220/31 ,  F05D2240/80 ,  F05D2250/314 ,  Y10T29/49236

Abstract: An axial flow turbine diaphragm is constructed without welding or other metal fusion or melting techniques. Static blade units are attached to inner and outer diaphragm rings by radially inner platform portions that engage the radially inner ring, and radially outer platform portions that engage the radially outer ring, the inner platform portions being elongate in the circumferential direction of the turbine diaphragm and the outer platform portions being elongate in a direction compatible with the stagger angle of the aerofoils. The outer circumference of the radially inner ring has a blade unit retaining feature of complementary shape and orientation to the inner platform portions of the static blade units, and the inner circumference of the radially outer ring is provided with a plurality of blade unit retaining features of complementary shape and orientation to corresponding outer platform portions of the static blade units.