Turbine balance arrangement with integral air passage
US4898514A · kind A · utility
16Cited by
8References
10Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Oct 27, 1987 |
| Grant date | Feb 6, 1990 |
| Priority date | — |
| Expiry date | Oct 27, 2007 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF16F15/32
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine rotor includes a disk (50) with axial dovetail slots (64) and air cooled blades (52) having mating, but shortened dovetails (66). The axial flow path (68) so formed is blocked at the far end and is in fluid communication with the blade cooling passages. Balance weights (70) fit within the openings in a manner which does not interfere with the cooling airflow.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.