High pressure compressor thermal management
US9816963B2 · kind B2 · utility
5Cited by
22References
20Claims
0Family size
Assignees
Inventors
Key dates
| Filing date | Dec 27, 2013 |
| Grant date | Nov 14, 2017 |
| Priority date | — |
| Expiry date | Jan 5, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49229
- WIPO fieldMeasurement
- WIPO sectorInstruments
Abstract
A gas turbine engine includes an inner shaft extending axially along the gas turbine engine, a plurality of disks extending radially inwardly and toward the inner shaft, at least one hole in at least one of the plurality of disks, and an obstruction positioned between the inner shaft and an end of the disk having the at least one hole, such that a bore flow that flows along an axial length of the inner shaft is obstructed from flowing along the shaft by the obstruction, and forced to flow radially outward from the obstruction, through the at least one hole, and radially inward toward the inner shaft.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.