Heat shield for a gas turbine combustion chamber
US5918467A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Jul 28, 1997 |
| Grant date | Jul 6, 1999 |
| Priority date | — |
| Expiry date | Jul 28, 2017 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03042
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A heat shield for a gas turbine annular combustion chamber having a plurality of effusion holes (5), the central axes of which are inclined towards the heat shield surface and over which cooling air can penetrate from the rear to apply a film of cooling air to the hot surface. The surface is subdivided into sectors (7) and transition areas (10) between the sectors, the central axes of the effusion holes essentially being arranged in parallel to each other in a given sector or transition area. In addition, the central axes (6) of the effusion holes (5) located in each surfaces sector (7) are parallel to one another and extend substantially toward the associated corner area (8) and, in sections, extending approximately in a direction the same as the fuel combustion air swirl (4) in this sector (7).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.