Shroud seal segments arrangement in a gas turbine
US8353663B2 · kind B2 · utility
17Cited by
2References
13Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 21, 2011 |
| Grant date | Jan 15, 2013 |
| Priority date | — |
| Expiry date | Jan 21, 2031 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/205
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine is provided that includes a rotor which is rotatable around an axis and equipped with rotor blades, and which is concentrically enclosed at a distance by a casing, which is equipped with stator blades, forming an annular hot gas passage. Rings with stator blades and rotor blades are arranged in a manner alternating in the axial direction. Between adjacent stator blades, heat shield segments are arranged, which delimit the hot gas passage on the outside in a region of the rotor blades and are cooled by impingement cooling where a cooling medium from an outer annular cavity flows into the heat shield segment.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.