Reduction of equally spaced turbine nozzle vane excitation
US9963974B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 23, 2012 |
| Grant date | May 8, 2018 |
| Priority date | — |
| Expiry date | Dec 12, 2035 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49318
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A reduction in excitation amplitudes affecting turbine blade durability in a turbine nozzle assembly having a plurality of vanes and turbine blades, includes: identifying a turbine blade design of the turbine nozzle assembly; performing a modal model analysis of at least one of the turbine blades in the turbine blade design; reducing aerodynamic impact by ensuring that each of the turbine blades is free of aero-excitation from an upstream flow at the vanes in an operating speed range; identifying blade natural frequencies with respect to the nozzle vanes; and modifying a trailing edge of at least one of the vanes to reduce the excitation amplitudes.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.