Cooling system for a gas turbine engine compressor
US5297386A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Jul 29, 1993 |
| Grant date | Mar 29, 1994 |
| Priority date | — |
| Expiry date | Jul 29, 2013 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A cooling system for an axial flow compressor of a gas turbine engine is disclosed having a device to tap a portion of air from the primary air flow flowing through the axial compressor and a control device associated with the tap to control the amount of air tapped from the primary air flow. The system also includes a cooling device to cool the portion of air tapped from the primary air flow, which cooled air is directed into a cooling air chamber. The cooling air chamber is located between the last rotor stage of the compressor and a cone attached to the last stage and extending downstream from the rotor wheel. Nozzles associated with the cooling air chamber direct cooling air from the chamber onto the rotating rotor wheel such that a portion of the cooling air passes into the peripheral groove defined by the rotor wheel between the wheel and the blade root, while another portion of the cooling air from the nozzles is directed onto the surface of the cone in order to cool the blades and the cone.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.