Compressor bleed cooling system for mid-frame torque discs downstream from a compressor assembly in a gas turbine engine
US10830146B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 1, 2016 |
| Grant date | Nov 10, 2020 |
| Priority date | — |
| Expiry date | Jun 21, 2036 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/22141
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A cooling system configured to cool aspects of the turbine engine between a compressor and a turbine assembly is disclosed. In at least one embodiment, the cooling system may include one or more mid-frame cooling channels extending from an inlet through one or more mid-frame torque discs positioned downstream of the compressor and upstream of the turbine assembly. The inlet may be positioned to receive compressor bleed air. The mid-frame cooling channel may be positioned in a radially outer portion of the mid-frame torque disc to provide cooling to outer aspects of the mid-frame torque disc such that conventional, low cost materials may be used to form the mid-frame torque disc rather than high cost materials with capacity to withstand higher temperatures. The cooling fluid routed through the mid-frame cooling channel in the mid-frame torque disc may be exhausted into a cooling system (10) for the downstream turbine assembly.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.