Title:
流れ押退け特徴を備える内部で冷却されるタービン翼
Document Type and Number:
Japanese Patent JP6602957
Kind Code:
B2
Abstract:
A turbine airfoil (10) includes a flow displacement element (26) occupying a space between a pair of adjacent partition walls (24) in an interior portion (11) of a generally hollow airfoil body (12). The flow displacement element (26) includes an elongated main body (28) extending lengthwise in a radial direction and a pair of connector ribs (32, 34) respectively connecting the main body (28) to pressure and suction sides (16, 18) of the airfoil (10). A pair of adjacent radial flow passes (43-44, 45-46) of symmetrically opposed flow cross-sections are defined on chordally opposite sides of the flow displacement element (26). The radial flow passes (43-44, 45-46) conduct cooling fluid in opposite radial directions and are connected in series via a chordal passage (50a, 50c) defined in the interior portion (11) between the flow displacement element (26) and a radial end face (52) of the airfoil body (12), to form a serpentine cooling path (60a, 60b).
Inventors:
Evansie. Landrum
Jean H. Marsh
Paul A. Thunders
Jean H. Marsh
Paul A. Thunders
Application Number:
JP2018510947A
Publication Date:
November 06, 2019
Filing Date:
August 28, 2015
Export Citation:
Assignee:
Siemens Aktiengesellschaft
International Classes:
F01D5/18; F01D9/02; F02C7/18
Domestic Patent References:
| JP60135605A | ||||
| JP50036817A | ||||
| JP10231703A | ||||
| JP8028205A |
Foreign References:
| WO2010131385A1 |
Attorney, Agent or Firm:
Einzel Felix-Reinhard
Morita Taku
Junichi Maekawa
Hiroyasu Ninomiya
Ueshima
Morita Taku
Junichi Maekawa
Hiroyasu Ninomiya
Ueshima