Invention Application
WO2013135319A1 GAS TURBINE ARRANGEMENT ALLEVIATING STRESSES AT TURBINE DISCS AND CORRESPONDING GAS TURBINE
审中-公开
在涡轮盘和相应气体涡轮机上的气体涡轮机布置应力
- Patent Title: GAS TURBINE ARRANGEMENT ALLEVIATING STRESSES AT TURBINE DISCS AND CORRESPONDING GAS TURBINE
- Patent Title (中): 在涡轮盘和相应气体涡轮机上的气体涡轮机布置应力
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Application No.: PCT/EP2012/073354Application Date: 2012-11-22
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Publication No.: WO2013135319A1Publication Date: 2013-09-19
- Inventor: BLUCK, Richard , HUGHES, Martin
- Applicant: SIEMENS AKTIENGESELLSCHAFT
- Applicant Address: Wittelsbacherplatz 2 80333 München DE
- Assignee: SIEMENS AKTIENGESELLSCHAFT
- Current Assignee: SIEMENS AKTIENGESELLSCHAFT
- Current Assignee Address: Wittelsbacherplatz 2 80333 München DE
- Priority: EP12159202.6 20120313
- Main IPC: F01D5/30
- IPC: F01D5/30 ; F01D5/08
Abstract:
In accordance with the invention there is provided turbine arrangement, particularly a gas turbine arrangement, comprising at least one rotor blade (2) and a turbine disc (5), the rotor blade (2) comprising a root portion (1), the turbine disc (5) comprising at least one slot (40) in which the root portion (1) of the rotor blade (2) is secured. The slot (40) comprises a plurality of opposite pairs of slot lobes (100) and a plurality of opposite pairs of slot fillets (101), and a slot bottom (105) of the slot (40). The slot bottom (105) is arranged to comprise a first convex surface section (102). Furthermore the root portion (1) of the rotor blade (2) comprises a root bottom (50) comprising a first concave surface section (51) corresponding to the first convex surface section (102) of the slot bottom (105). Additionally, the first convex surface section (102) is pierced by an outlet (44) of a cooling duct (42) through the turbine disc (5).
Information query
